Fast response active gap control system with piezoelectric actuator

Abstract

Certain examples disclose and describe apparatus and methods for providing a fast response active clearance control system with a piezoelectric actuator. In some examples, the apparatus includes a housing surrounding at least a portion of a turbine engine, the at least a portion of the turbine engine including at least one of a shroud or a suspension to accommodate airflow in at least a portion of the turbine engine. The apparatus further includes an actuator to control the clearance between the blades and at least one of the shroud or the suspension, the actuator including a multi-layer stack of materials, and wherein the actuator is located outside the housing. The apparatus also includes a rod portion, the rod portion being coupled to the actuator and at least one of the shroud or the suspension through an opening in the housing, the rod portion moving at least one of the shroud or the suspension based on the actuator.

Description

Technical Field

[0001] The present disclosure relates generally to a gas turbine engine and, more particularly, to a fast response active clearance control system having a piezoelectric actuator. Background Art

[0002] A gas turbine engine generally includes an inlet section, a compressor section, a combustion section, a turbine section, and an exhaust section in a serial flow order. In operation, air enters the inlet section and flows to the compressor section, where one or more axial flow compressors gradually compress the air until the air reaches the combustion section. Fuel is mixed with the compressed air and combusted in the combustion section, thereby producing combustion gases. The combustion gases flow from the combustion section through a hot gas path, which is defined in the turbine section, and then exit the turbine section via the exhaust section.

[0003] Generally, with respect to gas turbine engines, it is desirable to maintain a clearance between the blade tips in the gas turbine engine and fixed portions of the gas turbine engine (e.g., gas turbine engine casing, stator, etc.). During operation, the gas turbine engine is exposed to thermal loads (e.g., hot and cold air pumped into the gas turbine engine, etc.) and mechanical loads (e.g., centrifugal forces on the blades on the gas turbine engine, etc.), which can cause the gas turbine engine casing and rotor to expand and contract. The expansion and contraction of the gas turbine engine casing can change the clearance between the blade tips and the fixed portions of the gas turbine engine. There is a constant need to control the clearance between the blade tips and the engine casing, which fluctuates during normal operation of the gas turbine engine, to avoid damage to the gas turbine engine (e.g., wear, breakage, etc. due to unexpected friction, etc.). Summary of the invention

[0004] Methods, apparatus, systems, and articles of manufacture are disclosed for providing fast response active gap control using piezoelectric actuators.

[0005] Certain examples provide an apparatus comprising: a housing surrounding at least a portion of a turbine engine, the at least a portion of the turbine engine including at least one of a shroud or a suspension to accommodate airflow in at least a portion of the turbine engine; an actuator controlling a clearance between a blade and at least one of the shroud or the suspension, the actuator comprising a multi-layer stack of materials, and wherein the actuator is located outside the housing; and a stem coupled to the actuator and at least one of the shroud or the suspension through an opening in the housing, the stem moving at least one of the shroud or the suspension based on the actuator.

[0006] Certain examples provide an apparatus comprising: a housing surrounding at least a portion of a turbine engine, the at least a portion of the turbine engine including at least one of a shroud or a suspension to contain airflow in at least a portion of the turbine engine; a first actuator that controls a clearance between a blade and at least one of the shroud or the suspension, the first actuator comprising a first multi-layer stack of material and wherein the first actuator is coupled to at least one of a first hook of the shroud or the suspension; and a second actuator that controls a clearance between the blade and at least one of the shroud or the suspension, the second actuator comprising a second multi-layer stack of material and wherein the second actuator is coupled to at least one of a second hook of the shroud or the suspension.

[0007] Certain examples provide a non-transitory computer-readable medium comprising instructions that, when executed, cause at least one processor to at least: monitor a condition parameter from a sensor device in a turbine engine; determine when the turbine engine condition indicates that a casing is expanding or is contracting, wherein the turbine engine condition is based on the condition parameter and the casing surrounds at least a portion of the turbine engine; in response to determining that the turbine engine condition indicates that the casing is expanding, transmit a first current to a multi-layer stack of materials, and in response to determining that the turbine engine condition indicates that the casing is contracting, transmit a second current to the multi-layer stack of materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] Figure 1 is a schematic cross-sectional view of an exemplary gas turbine engine according to the disclosure herein.

[0009] Figure 2 is a schematic cross-sectional view of an exemplary gas turbine engine having a conventional active clearance control (ACC) system.

[0010] FIG. 3 is a schematic cross-sectional view of a conventional ACC system for a gas turbine engine.

[0011] Figure 4A and 4B is a schematic cross-sectional illustration of a first exemplary ACC system according to the teachings disclosed herein.

[0012] Figure 5A and 5B is a schematic cross-sectional illustration of a second exemplary ACC system according to the teachings disclosed herein.

[0013] Fig. 6A and 6B is a schematic cross-sectional illustration of a third exemplary ACC system according to the teachings disclosed herein.

[0014] Figure 7 yes Figure 4A ,4B , 5A, 5B, 6A and 6B are block diagrams of example controllers of example ACC systems.

[0015] Figure 8 is a representative flow chart of machine readable instructions that are executed to combine Figure 4A , 4B An exemplary ACC system implementation of Figure 7 An exemplary controller of .

[0016] Fig. 9 is a representative flow chart of machine readable instructions that are executed to combine Figure 5A , 5B An exemplary ACC system implementation of Figure 7 An exemplary controller of .

[0017] Fig.10 is a representative flow chart of machine readable instructions that are executed to combine Fig. 6A , 6B An exemplary ACC system implementation of Figure 7 An exemplary controller of .

[0018] Fig.11 is constructed to execute Figure 8 , 9 , 10 instructions to achieve Figure 7 A block diagram of an exemplary processing platform of an exemplary controller.

[0019] The drawings are not drawn to scale. Instead, the thickness of each layer or each region is exaggerated in the drawings. Although the layers and regions shown in the drawings have clear lines and boundaries, some or all of the lines and / or boundaries may be idealized. In fact, the boundaries and / or lines may be imperceptible, mixed and / or irregular. In general, the same reference numerals are used throughout the drawings and the written descriptions accompanying the drawings to refer to the same or similar parts. As described herein, unless otherwise specified, the word "above" describes the relationship between the two parts relative to the ground. If the second part has at least one part between the ground and the first part, the first part is above the second part. Similarly, as used herein, when the first part is closer to the ground than the second part, the first part is "below" the second part. As described above, the first part can be above or below the second part, with one or more: other parts between the first part and the second part, no other parts are in contact with the first part and the second part, or no first part and second part are in direct contact with each other. As used in this patent, a statement that any part (e.g., a layer, film, zone, region, or plate) is in any way located on (e.g., positioned on, located at, disposed on, or formed on, etc.) another part indicates that the referenced part is in contact with the other part, or that the referenced part is located above the other part and one or more intermediate parts are located therebetween. As used herein, unless otherwise indicated, connection references (e.g., attachment, connection, connection, and engagement) may include intermediate members between the elements referenced by the connection reference and / or relative movement between these elements. Therefore, a connection reference does not necessarily infer that two elements are directly connected and / or connected to each other in a fixed relationship. As described herein, a definition stating that any part is "in contact" with another part means that there are no intermediate parts between the two parts.

[0020] Unless otherwise expressly stated, descriptors such as "first," "second," "third," and the like are used herein without inferring or otherwise indicating any meaning of priority, physical order, arrangement in a list, and / or ordering in any manner, but are used merely as labels and / or arbitrary names to distinguish elements for ease of understanding the disclosed examples. In some examples, the description "first" may be used to refer to an element in a specific embodiment, while the same element may be referred to by a different description (e.g., "second" or "third") in the claims. In this context, it should be understood that such descriptions are only used to clearly identify elements that may (for example) otherwise share the same name. As used herein, "approximately" and "approximately" refer to dimensions that may not be accurate due to manufacturing tolerances and / or other practical defects. DETAILED DESCRIPTION

[0021] In the following detailed description, reference is made to the accompanying drawings which form a part of this specification, in which specific examples that can be implemented are shown in a diagrammatic manner. These embodiments are described in sufficient detail to enable those skilled in the art to practice the subject matter, and it should be understood that other embodiments may be used. Therefore, the following detailed description is provided to describe example implementations, rather than to limit the scope of the subject matter described in this disclosure. Certain features of the different aspects described below may be combined to form new aspects of the subject matter discussed below.

[0022] When introducing elements of various embodiments of the present disclosure, the text "a", "an", "the", and "above" means that there are one or more elements. The terms "first", "second", etc. are not intended to indicate the position or importance of a single component, but are used to distinguish one element from another. The terms "including", "comprising", and "having" are intended to be inclusive and mean that there may be other elements besides the listed elements. Because the terms "connected to", "coupled to", etc. are used herein, an object (e.g., a material, element, structure, component, etc.) can be connected to another object or coupled to another object, regardless of whether one object is directly connected or coupled to another object, or whether there are one or more intervening objects between one object and another object.

[0023] As used herein, the terms "system," "unit," "module," "engine," and the like may include hardware and / or software systems for performing one or more functions. For example, a module, unit, or system may include a computer processor, controller, and / or other logic-based device that performs operations based on instructions stored on, for example, a temporary and non-temporary computer-readable storage medium, such as a computer memory. Alternatively, a module, unit, engine, or system may include a hard-wired device that performs operations based on the hard-wired logic of the device. The various modules, units, engines, and / or systems shown in the accompanying drawings may represent hardware that operates based on software or hard-wired instructions, software that directs hardware to perform operations, or a combination thereof.

[0024] The terms "upstream" and "downstream" refer to relative directions with respect to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction to which the fluid is flowing. As used herein, "vertical" refers to a direction perpendicular to the ground. As used herein, "horizontal" refers to a direction parallel to the centerline of the gas turbine engine 100. As used herein, "lateral" refers to a direction perpendicular to the axial and vertical directions (e.g., entering and leaving the engine). Figure 1 , 2 etc. plane).

[0025] In some examples used in this document, the term "substantially" is used to describe a relationship between two parts that is within three degrees of the relationship (e.g., a substantially collinear relationship is within three degrees of linearity, a substantially perpendicular relationship is within three degrees of perpendicularity, a substantially parallel relationship is within three degrees of parallelism, etc.).

[0026] A turbine engine, also known as a combustion turbine or gas turbine, is an internal combustion engine. Turbine engines are commonly used in aircraft and power generation applications. As used herein, the terms "advantage", "aircraft turbine engine", "gas turbine", "land turbine engine", and "turbine engine" are used interchangeably. The basic operation of a turbine engine includes an inlet of fresh atmospheric airflow through the front of the turbine engine with a fan. In some examples, the airflow passes through an intermediate pressure compressor or boost compressor located between the fan and the high pressure compressor. The turbine engine also includes a turbine with a complex array of alternating rotating and fixed airfoil blades. As the hot combustion gases pass through the turbine, the hot combustion gases expand, causing the rotating blades to rotate.

[0027] Components of a turbine engine (e.g., fan, boost compressor, high pressure compressor, high pressure turbine, low pressure turbine, etc.) can degrade over time due to harsh operating conditions such as extreme temperatures and vibrations. During operation, turbine engine components are exposed to thermal loads (e.g., hot and cold air pumped to the turbine engine, etc.) and mechanical loads (e.g., centrifugal forces on blades on the turbine engine, etc.), which can cause the turbine engine casing and / or the compressor casing within the turbine engine and other components of the turbine engine and / or its compressor to expand and contract. The expansion and contraction of the turbine engine casing and / or the compressor casing within the turbine engine can change the clearance between the blade tip and the stationary components of the turbine engine. In some examples, if the clearance between the blade tip and the stationary components is not controlled, the blade tip and the stationary components may collide during operation, causing further degradation of the components of the turbine engine.

[0028] Active Clearance Control (ACC) systems are designed to optimize blade tip clearance to improve engine performance without undesirable detrimental friction events during flight and landing operations. Conventional ACC systems include using cooling air from a fan or compressor to control the clearance between the blade tip and contracting engine components (e.g., stator, casing, etc.). Conventional ACC systems are limited to clearance being adjusted in only one direction (e.g., engine component contraction). For hot rotor conditions (e.g., engine component expansion), conventional ACC systems must wait for rotor-stator thermal / mechanical growth matching to escape the hot rotor conditions (e.g., adjust blade tip clearance).

[0029] The examples disclosed herein optimize and / or otherwise use piezoelectric actuators to improve the ACC system, providing fast response gap control without the mechanical delays seen in conventional ACC systems. The examples disclosed herein maintain the desired gap between the blade tips and other engine components without creating additional margins under various operating conditions, which will result in improved performance and provide better exhaust gas temperature (EGT) control capabilities. In some examples, the piezoelectric material produces a linear displacement when an electric field is applied. The linear displacement can have a force, and the examples disclosed herein apply the linear force of the piezoelectric material to the ACC system to achieve fast response gap control. The examples disclosed herein apply the mechanical force from the linear displacement of the piezoelectric material to adjust the ACC system. The examples disclosed herein may include other materials that produce linear displacement, such as shape memory alloys (SMA), etc. Increasing the displacement range by adding layers of piezoelectric material or SMA is called a multilayer stack, where more layers in the stack provide more radial range of movement and provide more muscle capabilities for the ACC system.

[0030] The examples disclosed herein use actuators to accommodate piezoelectric materials. The actuators achieve clearance in two directions (e.g., inward and outward). The examples disclosed herein do not require additional clearance margin to achieve maximum instantaneous closure or hot rotor conditions like traditional ACC systems. Because there is no additional margin for instantaneous closure or hot rotor conditions, the examples disclosed herein provide significant specific fuel consumption (SFC) improvements for tighter clearances and better EGT control.

[0031] In the examples disclosed herein, actuators for piezoelectric materials can provide various design spaces with compact and simple piezoelectric stacks while providing the same high mechanical force as conventional ACCs. The examples disclosed herein propose three different mechanical design configurations for how to stack and position piezoelectric materials: (1) outside of a high pressure turbine (HPT) housing or a compressor housing; (2) inside a suspension hook; and (3) inside a suspension hook with a spring. An exemplary first mechanical design configuration includes an externally stacked piezoelectric actuator that generates a linear displacement due to an applied electric field. Since the piezoelectric actuator is located outside the housing (e.g., an HPT housing, a compressor housing, etc.), the first mechanical design configuration has the advantage of being easy to maintain and replace components, however, it also includes the sealing problem of the housing. Since the piezoelectric stack is located outside the housing, the first mechanical design configuration protects the piezoelectric material under low temperature conditions, thereby reducing considerations of temperature limitations of the piezoelectric material.

[0032] An exemplary second mechanical design configuration includes an internal stack of piezoelectric actuators, with two actuators applied on a suspension hook below the housing. The piezoelectric stack is positioned on the upper and lower surfaces of the suspension hook to achieve more precise adjustment, and the second mechanical design configuration relatively reduces the consideration of resealing in the first mechanical design configuration. However, compared with the first mechanical design configuration, the second mechanical design configuration is not convenient for maintenance or replacement of parts. A third mechanical design configuration includes two actuators on a suspension hook below the housing. The actuator includes an internal stack of piezoelectric material on the upper surface of the suspension hook and a spring on the lower surface of the suspension hook. Except for including the spring, the third mechanical design configuration is similar to the second mechanical design configuration. The cost of the piezoelectric material stack required for the third mechanical design configuration is lower, but may result in uncertainty in the adjustment accuracy. Compared with the first mechanical design configuration, the third mechanical design configuration also has disadvantages in terms of maintenance or replacement of parts.

[0033] Some examples provide an engine controller, called a full authority digital engine (or electronic equipment) control (FADEC). The FADEC includes a digital computer, called an electronic engine controller (EEC) or engine control unit (ECU), and related accessories that control aspects of aircraft engine performance. The FADEC can be used for a variety of engines, such as piston engines, jet engines, other aircraft engines, etc. In some examples, the EEC / ECU is provided separately from the FADEC, allowing the pilot and / or other operator to manually override or intervene.

[0034] In examples disclosed herein, an engine controller receives values ​​for a plurality of input variables related to flight conditions (e.g., air density, throttle stem position, engine temperature, engine pressure, etc.) The engine controller uses the flight condition data to calculate engine operating parameters, such as fuel flow, stator vane position, exhaust valve position, etc. The engine operating parameters may be used by the engine controller to control operation of a piezoelectric actuator to adjust blade tip clearance in a turbine engine.

[0035] Reference will now be made in detail to embodiments of the present invention, one or more examples of which are shown in the accompanying drawings. Each example is provided by way of explanation of the present invention rather than limitation thereof. In fact, it will be apparent to those skilled in the art that various modifications and variations may be made to the present invention without departing from the scope or spirit of the present invention. For example, a feature shown or described as part of one embodiment may be used together with another embodiment to produce yet another embodiment. Therefore, the present invention is intended to encompass these modifications and variations within the scope of the appended claims and their equivalents.

[0036] Figure 1 is a schematic cross-sectional view of a conventional turbofan gas turbine engine 100 (“turbofan 100”). Figure 1As shown, turbofan 100 defines a longitudinal or axial centerline axis 102 extending therethrough, for reference. Generally speaking, turbofan 100 may include a core turbine or gas turbine engine 104 disposed downstream of a fan section 106 .

[0037] The core turbine 104 generally includes a substantially tubular casing 108 that defines an annular inlet 110. The casing 108 may be formed by a single shell or multiple shells. The casing 108 surrounds a compressor section having a supercharger or low-pressure compressor 112 ("LP compressor 112") and a high-pressure compressor 114 ("HP compressor 114"), a combustion section 116, a turbine section having a high-pressure turbine 118 ("HP turbine 118") and a low-pressure turbine 120 ("LP turbine 120"), and an exhaust section 122 in a serial flow relationship. A high-pressure shaft or spool 124 ("HP shaft 124") is drivingly connected to the HP turbine 118 and the HO compressor 114. A low-pressure shaft or spool 126 ("LP shaft 126") is drivingly connected to the LP turbine 120 and the LP compressor 112. The LP shaft 126 may also be coupled to a fan spool or shaft 128 of the fan section 106. In some examples, LP shaft 126 may be directly coupled to fan shaft 128 (ie, a direct drive configuration). In an alternative configuration, LP shaft 126 may be coupled to fan shaft 128 via reduction gear 130 (ie, an indirect drive or gear drive configuration).

[0038] like Figure 1 As shown, fan section 106 includes a plurality of fan blades 132 coupled to and extending radially outward from fan shaft 128. An annular fan casing or nacelle 134 circumferentially surrounds fan section 106 and / or at least a portion of core turbine 104. Nacelle 134 is supported relative to core turbine 104 by a plurality of circumferentially spaced outlet guide vanes 136. In addition, a downstream section 138 of nacelle 134 can surround an exterior of core turbine 104 to define a bypass airflow passage 140 therebetween.

[0039] like Figure 1As shown, air 142 enters an inlet portion 144 of the turbofan 100 during operation of the turbofan 100. A first portion 146 of the air 142 flows into the bypass airflow passage 140, while a second portion 148 of the air 142 flows into the inlet 110 of the LP compressor 112. One or more sequential stages of LP compressor stator blades 150 and LP compressor rotor blades 152 connected to the LP shaft 126 progressively compress the second portion 148 of the air 142 flowing through the LP compressor 112 on the way to the HP compressor 114. Next, one or more sequential stages of HP compressor stator blades 154 and HP compressor rotor blades 156 connected to the HP shaft 124 further compress the second portion 148 of the air 142 flowing through the HP compressor 114. This provides compressed air 158 to the combustion section 116, wherein the compressed air 158 is mixed with fuel and combusted in the combustion section 116 to provide combustion gases 160.

[0040] The combustion gases 160 flow through the HP turbine 118, wherein one or more sequential stages of HP turbine stator blades 162 and HP turbine rotor blades 164 coupled to the HP shaft 124 extract a first portion of kinetic and / or thermal energy from the combustion gases 160. This energy extraction supports the operation of the HP compressor 114. The combustion gases 160 then flow through the LP turbine 120, wherein one or more sequential stages of LP turbine stator blades 166 and LP turbine rotor blades 168 coupled to the LP shaft 126 extract a second portion of thermal and / or kinetic energy therefrom. This energy extraction rotates the LP shaft 126, thereby supporting the operation of the LP compressor 112 and / or the rotation of the fan shaft 128. The combustion gases 160 then exit the core turbine 104 through the exhaust section 122 of the core turbine 104.

[0041] Together with the turbofan 100, the core turbine 104 is used for similar purposes and similar environments in land-based gas turbines, turbojets, where the ratio of the first portion 146 of the air 142 to the second portion 148 of the air 142 is less than that in the turbofan, and in the non-ducted fan engine, the fan section 106 does not have a nacelle 134. In each turbofan, turbojet, and non-ducted engine, a speed reduction device (e.g., a speed reduction gearbox 130) may be included between any shaft and the spool. For example, the speed reduction gearbox 130 may be provided between the LP shaft 126 and the fan shaft 128 of the fan section 106.

[0042] Figure 22 is a schematic cross-sectional view of an exemplary gas turbine engine having a conventional ACC system 200. The ACC system 200 includes an exemplary main pipe 205, an exemplary high pressure turbine 210, an exemplary low pressure turbine 215, exemplary manifolds 220A, 220B, 220C, exemplary flanges 225A, 225B, and exemplary intermediate rings 230A, 230B. Figure 2 In the example shown, air from a fan (eg, from fan section 106) enters a main tube 205, wherein the airflow in the main tube 205 is as follows: Figure 2 In some examples, the inlet of the main pipe 205 is located at the fan for the high pressure turbine 210 (e.g., Figure 1 of the fan section 106) or compressor (e.g., Figure 1 In some examples, the ACC system 200 may be applied to a compressor (e.g., Figure 1 The HP compressor 114 and the LP compressor 112) and the low-pressure turbine 215. The main pipe 205 delivers air from the fan to the manifolds 220A, 220B, 220C. The manifolds 220A, 220B, 220C evenly distribute the air from the fan to the high-pressure turbine 210 and the low-pressure turbine 215. In some examples, the high-pressure turbine 210 is substantially similar to the HP turbine 118, and the low-pressure turbine 215 is substantially similar to the LP turbine 120. Flanges 225A, 225B and intermediate rings 230A, 230B are connected to the outer surfaces of the high-pressure turbine 210 housing and the low-pressure turbine 215 housing. The flanges 225A, 225B and the intermediate rings 230A, 230B are configured to contract radially inwardly and / or expand radially outwardly in response to changes in temperature (e.g., changes in temperature caused by air from the manifolds 220A, 220B, 220C). In some examples, at least some of the air is directed to impact the surfaces of flanges 225A, 225B and intermediate rings 230A, 230B. In some examples, the inward contraction and outward expansion of flanges 225A, 225B and intermediate rings 230A, 230B can change the blade tip clearances in high pressure turbine 210 and low pressure turbine 215.

[0043] Figure 3 is used for Figure 1 3 is a schematic cross-sectional view of an existing ACC system 300 of an exemplary gas turbine engine 100. The existing ACC system 300 includes a casing 305, guide hooks 310A, 310B, a suspension 315, a shroud 320, and blades 325. In the example shown in FIG. 3, the casing 305 is a casing that surrounds the HP turbine 118, the LP turbine 120, and / or the compressor (e.g., Figure 1The housing 305 includes guide hooks 310A, 310B, wherein the guide hooks 310A, 310B connect the housing 305 to the suspension 315. The suspension 315 is connected to the shroud 320.

[0044] In the example shown in FIG3 , the prior art ACC system 300 determines the clearance between the shroud 320 and the blade 325. Arrows 330A-330D in the prior art ACC system 300 represent the clearance between the shroud 320 and the blade 325. Figure 2 The cooling airflow of the main pipe 205 and the manifolds 220A, 220B, 220C of the example. The existing ACC system 300 controls the movement of the shroud 320 in only one direction (e.g., inward toward the blade 325). The existing ACC system 300 uses the cooling airflow from the compressor or fan to cool the housing 305. The housing 305 contracts (e.g., moves inward) when cooled by the airflow. The housing 305 moves the suspension 315 and the passport 320 inward toward the blade 325. The existing ACC system 300 cannot move the housing 305, the suspension 315, and the shroud 320 for expansion. For example, the ACC system 300 cannot expand the housing 305 (e.g., move outward) to increase the gap between the shroud 320 and the blade 325. In these examples, the existing ACC system 300 waits for the gap between the shroud 320 and the blade 325 to open (e.g., increase). The existing ACC system 300 does not provide two-way control of the gap between the shroud 320 and the blade 325.

[0045] In some examples (e.g., the existing ACC system 300 of FIG. 3 ), the ACC system guides the airflow around the engine casing to control the gap between the casing and the blade tip. For example, the ACC system controls the cooling airflow from the compressor or fan to the casing 305 (indicated by arrows 330A-330D in FIG. 3 ). In some examples, the ACC system mixes the cold and hot air from the compressor and the bypass duct (including the turbofan airflow that bypasses the engine core) to the desired temperature. In some examples, the ACC system helps to maintain and adjust the gap between the engine casing and the blade tip in the existing ACC system. In the existing ACC system (e.g., the existing ACC system 300 of FIG. 3 ), the cooling airflow around the engine casing (e.g., casing 305) adjusts the gap by controlling the thermal expansion and contraction of the casing. In some examples, the ACC system controls the cooling airflow to shrink or expand the turbine engine casing. For example, the existing ACC system 300 guides the cooling airflow to the casing 305 to shrink the casing 305, and restricts the cooling airflow to the casing 305 to expand the casing 305. The ACC system controls the cooling airflow to adjust the gap, thereby compensating for any changes in the blades of the turbine engine. In some examples, the ACC system is controlled by a controller (e.g., FADEC) in the turbine engine. The FADEC sends an electrical control signal to the ACC system to send a signal to the ACC system to adjust the airflow to control the casing thermal expansion. The ACC system ultimately controls the amount of cooling airflow to manage the turbine engine casing temperature to adjust the blade tip clearance.

[0046] Figure 4A and 4B is a schematic cross-sectional view of an example of an ACC system 400 according to the teachings disclosed herein. Figure 4A The exemplary ACC system 400 includes an actuator 405, a stem 410, a seal 415, a housing 420, a suspension 430, a shroud 435, and a vane 440. For example, the actuator 405 includes a multi-layer piezoelectric stack 450. Figure 4A The exemplary ACC system 400 includes an open gap 455 between the shroud 435 and the blades 440 .

[0047] Figure 4B An alternative embodiment of an ACC system 460 is shown. Figure 4B An example ACC system 460 includes Figure 4A The actuator 405, the rod 410, the seal 415, the housing 420, the suspension 430, the shroud 435 and the blade 440. Figure 4B The actuator 405 includes a multi-layer piezoelectric stack 450 that expands (or elongates) in the radial direction and contracts in the axial direction. Figure 4BThe ACC system 460 includes a close clearance 465 between the shroud 435 and the blade 440 . In the example disclosed herein, the housing 420 includes guide hooks 425A, 425B, wherein the guide hooks 425A, 425B connect the housing 420 to the suspension 430 . The suspension 430 is connected to the shroud 435 .

[0048] exist Figure 4A and 4B In the example shown, the actuator 405 is located outside the housing 420. In some examples, the housing 420 is a housing surrounding a high pressure turbine (e.g., Figure 1 HP turbine 118), low pressure turbine (e.g. Figure 1 LP turbine 120) and / or compressor (e.g., Figure 1 In some examples, actuator 405 is positioned outside of casing 420 to prevent material temperature limitations from affecting actuator 405. For example, if actuator 405 is located inside casing 420, then in a high pressure turbine (such as Figure 1 The hot gas temperatures in the HP turbine 118) may cause material limitations of the actuator 405. In the exemplary ACC systems 400 and 460, the actuator 405 includes a multi-layer stack of piezoelectric material 450. In some examples, the piezoelectric material of the multi-layer stack of piezoelectric material 450 includes quartz, topaz, etc. However, other piezoelectric materials or other materials that produce linear displacement, such as shape memory alloy (SMA) materials, etc., may be additionally and / or optionally included. In some examples, positioning the actuator 405 and the multi-layer stack of piezoelectric material 450 outside the housing 420 helps to maintain the piezoelectric material in cold conditions without considering temperature limitations. For example, the location of the actuator 405 and the multi-layer stack of piezoelectric material 450 provides the advantage of easy maintenance and component replacement.

[0049] exist Figure 4A and 4B In the example shown, the multi-layer stack of piezoelectric material 450 is connected to the rod 410. The rod 410 is connected to the suspension 430 through the housing 420. Since the actuator 405 and the multi-layer stack of piezoelectric material 450 are positioned outside the housing 420, the rod 410 is inserted into the housing to connect to the multi-layer stack of piezoelectric material 450 and the suspension 430. In some examples, the opening in the housing 420 for the rod 410 to be inserted through may introduce possible leakage through the housing 420. In such an example, the rod 410 is surrounded by a seal 415 to seal the opening in the housing 420 through which the rod 410 is inserted.

[0050] exist Figure 4A and 4BIn the example shown, a multi-layer stack of piezoelectric material 450 generates a linear displacement of the rod 410 in response to an electrical signal generated by an exemplary controller. Figure 7 An exemplary embodiment of a controller that generates an electrical signal is shown in , which will be described in further detail below. In some examples, the rod 410 uses a linear displacement generated by a multi-layer stack of piezoelectric material 450 to move the suspension 430. In the example shown, the suspension 430 and the shield 435 are connected and move together. Therefore, in the example shown, the rod 410 uses a linear displacement generated by a multi-layer stack of piezoelectric material 450 to move the suspension 430 and the shield 435. In some examples, the ACC system 400 includes a shield 435 without a suspension 430. In such an example, the rod 410 uses a linear displacement generated by a multi-layer stack of piezoelectric material 450 to move the shield 435. In some examples, the range of linear displacement is increased by adding more layers of piezoelectric material in the multi-layer stack of piezoelectric material 450. For example, adding layers in the multi-layer stack of piezoelectric material 450 can increase the radial range of movement and muscle capacity of the ACC system.

[0051] exist Figure 4A In the example shown, the ACC system 400 has an open gap, represented by an open gap 455 between the shroud 435 and the blade 440. The multi-layer stack of piezoelectric material 450 included in the actuator 405 controls the open gap 455. In the ACC system 400, the actuator 405 receives a first electrical signal from the example controller, and the actuator 405 provides the first electrical signal to the multi-layer stack of piezoelectric material 450. The first electrical signal causes a linear displacement of the multi-layer stack of piezoelectric material 450 (e.g., as in Figure 4A In the example shown, each of the multi-layer stacks of piezoelectric material 450 is long and thin. The linear displacement of the multi-layer stack of piezoelectric material 450 moves the stem 410 upward (e.g., away from the blade 440). The stem 410 moves the suspension 430 and the shield 435 upward (e.g., away from the blade 440), which increases the opening gap 455.

[0052] The exemplary ACC system 460 includes a tight clearance, Figure 4B 465 between the shroud 435 and the blades 440. The multi-layer stack of piezoelectric material 450 included in the actuator 405 controls the tight gap 465. In the ACC system 460, the actuator 405 receives a second electrical signal from the exemplary controller, and the actuator 405 provides the second electrical signal to the multi-layer stack of piezoelectric material 450. The second electrical signal causes a linear displacement of the multi-layer stack of piezoelectric material 450 (e.g., as in Figure 4BIn the example shown, each stack of the multi-layer stack of piezoelectric material 450 is short and thick. The linear displacement of the multi-layer stack of piezoelectric material 450 moves the stem 410 downward (e.g., toward the blade 440). The stem 410 moves the suspension 430 and the shield 435 downward (e.g., toward the blade 440), which reduces the tight gap 465.

[0053] exist Figure 4A and 4B In the example shown, the actuator 405 adjusts the clearance in two directions (e.g., contraction and expansion). The actuator 405 can be installed for a single shroud (e.g., shroud 435), a partial shroud set (e.g., a three shroud set, a five shroud set, etc.), or an entire shroud set in a turbine (e.g., a shroud around the 360 ​​degree inner surface of the casing 420).

[0054] Figure 5A and 5B is a schematic cross-sectional illustration of a second exemplary embodiment of an ACC system 500 according to the teachings disclosed herein. Figure 5A The exemplary ACC system 500 includes a housing 505, guide hooks 510A, 510B, an actuator 515, an actuator 520, a suspension 525, a shroud 530, and a blade 535. The actuator 515 includes a multi-layer stack of piezoelectric material 540 and a multi-layer stack of piezoelectric material 545. The actuator 520 includes a multi-layer stack of piezoelectric material 550 and a multi-layer stack of piezoelectric material 555. The ACC system 500 includes an open gap 560 between the shroud 530 and the blade 535. Figure 5B An exemplary ACC system 570 includes Figure 5A The housing 505 , the guide hooks 510A, 510B, the actuator 515 , the actuator 520 , the suspension 525 , the shield 530 , and the blade 535 . Figure 5B Actuator 515 includes a multi-layer stack of piezoelectric material 540 and a multi-layer stack of piezoelectric material 545 . Figure 5B The actuator 520 includes a multi-layer stack of piezoelectric material 550 and a multi-layer stack of piezoelectric material 555. The exemplary ACC system 570 includes a close gap 575 between the shroud 530 and the blade 535. The housing 505 includes guide hooks 510A, 510B, wherein the guide hooks 510A, 510B connect the actuator 515 and the actuator 520 to the suspension 525. The suspension 525 is connected to the shroud 530.

[0055] exist Figure 5A and 5B In the example shown, the actuator 515 is located below the housing 505 on the guide hook 510A, and the actuator 520 is located below the housing 505 on the guide hook 510B. In some examples, the housing 505 is a housing surrounding a high pressure turbine (e.g., Figure 1HP turbine 118), low pressure turbine (e.g. Figure 1 LP turbine 120) or compressor (e.g., Figure 1 In some examples, positioning actuator 515 and actuator 520 below housing 505 reduces the need for the actuator 515 and actuator 520 to move the actuator 515 and actuator 520 below housing 505, respectively. Figure 4A and 4B The sealing problem that is prevalent in the exemplary ACC systems 400 and 460 of the present invention is solved. However, the location of actuator 515 and actuator 520 hinders the ease of maintenance and component replacement. In the exemplary ACC system 500 and ACC system 570 shown, actuator 515 includes a multi-layer stack of piezoelectric material 540 and a multi-layer stack of piezoelectric material 545. In the exemplary ACC system 500 and ACC system 570 shown, actuator 520 includes a multi-layer stack of piezoelectric material 550 and a multi-layer stack of piezoelectric material 555. In some examples, the piezoelectric material of the multi-layer stack of piezoelectric materials 540, 545, 550, 555 may include quartz, topaz, etc. However, other piezoelectric materials or other materials that produce linear displacement, such as shape memory alloy (SMA) materials, etc., may be additionally and / or optionally included.

[0056] exist Figure 5A and 5B In the example shown, the suspension 525 extends into the actuator 515 and the actuator 520. Multiple layers of stacks of piezoelectric materials 540, 545, 550, 555 are connected to the suspension 525 extensions. Multiple layers of stacks of piezoelectric material 540 are connected to the top surface of the suspension 525 extension in the actuator 515. Multiple layers of stacks of piezoelectric material 545 are connected to the bottom surface of the suspension 525 extension in the actuator 515. Multiple layers of stacks of piezoelectric material 550 are connected to the top surface of the suspension 525 extension in the actuator 520. Multiple layers of stacks of piezoelectric material 555 are connected to the bottom surface of the suspension 525 extension in the actuator 520.

[0057] exist Figure 5A and 5B In the example shown, a multi-layer stack of piezoelectric materials 540, 545, 550, 555 generates a linear displacement of the suspension 525 by an electrical signal generated by an exemplary controller. Figure 7 An exemplary controller for generating an electrical signal is shown in FIG. 1 and described in further detail below. Figure 5A and 5BIn some examples, the suspension 525 and the shield 530 are connected and move together. Therefore, the suspension 525 uses the linear displacement generated by the multi-layer stack of piezoelectric materials 540, 545, 550, 555 to move the shield 530. In some examples, the ACC system 500 includes the shield 530 without the suspension 525. In such an example, the shield 530 moves using the linear displacement generated by the multi-layer stack of piezoelectric materials 540, 545, 550, 555. The multi-layer stack of piezoelectric materials 540, 545, 550, 555 is positioned on the top and bottom surfaces of the extension of the suspension 525 in the actuator 515 and the actuator 520 to precisely adjust the linear displacement. In some examples, the range of linear displacement is increased by adding more layers of piezoelectric material to the multi-layer stack of piezoelectric materials 540, 545, 550, 555. For example, the more layers that are added in the multi-layer stack of piezoelectric materials 540, 545, 550, 555, the greater the radial range of motion and muscle capacity of the ACC system.

[0058] The exemplary ACC system 500 has an open gap, represented by an open gap 560 between the shroud 530 and the blades 535. The multi-layer stack of piezoelectric materials 540, 545, 550, 555 controls the open gap 560. In the ACC system 500, the actuator 515 and the actuator 520 receive a first electrical signal from the exemplary controller. The actuator 515 provides the first electrical signal to the multi-layer stack of piezoelectric material 540, and the actuator 520 provides the first electrical signal to the multi-layer stack of piezoelectric material 550. The first electrical signal causes a linear displacement of the multi-layer stack of piezoelectric material 540 (e.g., as in Figure 5A In the example shown, each of the multi-layer stacks of piezoelectric material 540 is long and thin) and the multi-layer stacks of piezoelectric material 550 (e.g., as in Figure 5A In the example shown, each of the multi-layer stacks of piezoelectric material 550 is long and thin).

[0059] In ACC system 500, actuator 515 and actuator 520 receive a second electrical signal from an exemplary controller. In some examples, actuator 515 receives the first electrical signal and the second electrical signal at the same time or substantially at the same time (e.g., in parallel) with a given transmission delay. Actuator 515 provides the second electrical signal to the multi-layer stack of piezoelectric material 545, and actuator 520 provides the second electrical signal to the multi-layer stack of piezoelectric material 555. The second electrical signal causes a linear displacement of the multi-layer stack of piezoelectric material 545 (e.g., as in Figure 5A In the example shown, each stack of the multilayer stack of piezoelectric material 545 is short and thick) and the multilayer stack of piezoelectric material 555 (e.g., as shown in Figure 5AIn the example shown, each of the multi-layer stacks of piezoelectric material 555 is short and thick.) Linear displacement of the multi-layer stack of piezoelectric material 540 , 545 , 550 , 555 moves the suspension 525 and shield 530 upward (eg, away from the blades 535 ), which increases the opening gap 560 .

[0060] exist Figure 5B In the example, ACC system 570 has a tight gap, represented by tight gap 575 between shroud 530 and blade 535. The multi-layer stack of piezoelectric materials 540, 545, 550, 555 controls the tight gap 575. In ACC system 570, actuator 515 and actuator 520 receive a third electrical signal from the example controller. Actuator 515 provides the third electrical signal to the multi-layer stack of piezoelectric material 540, and actuator 520 provides the third electrical signal to the multi-layer stack of piezoelectric material 550. The third electrical signal causes a linear displacement of the multi-layer stack of piezoelectric material 540 (e.g., as in Figure 5B In the example shown, each stack of the multilayer stack of piezoelectric material 540 is short and thick) and the multilayer stack of piezoelectric material 550 (e.g., as in Figure 5B In the example shown, each stack of the multi-layer stack of piezoelectric material 550 is short and thick).

[0061] In ACC system 570, actuator 515 and actuator 520 receive a fourth electrical signal from an exemplary controller. In some examples, actuator 520 receives the third electrical signal and the fourth electrical signal at the same time or substantially at the same time (e.g., in parallel) with a given transmission delay. Actuator 515 provides the fourth electrical signal to the multi-layer stack of piezoelectric material 545, and actuator 520 provides the fourth electrical signal to the multi-layer stack of piezoelectric material 555. The fourth electrical signal causes a linear displacement of the multi-layer stack of piezoelectric material 545 (e.g., as in Figure 5B In the example shown, each stack of the multilayer stack of piezoelectric material 545 is long and thin) and the multilayer stack of piezoelectric material 555 (e.g., as in Figure 5B In the example shown, each of the multi-layer stacks of piezoelectric material 555 is long and thin.) Linear displacement of the multi-layer stacks of piezoelectric material 540 , 545 , 550 , 555 moves the suspension 525 and shroud 530 downward (eg, toward the blades 535 ), which reduces the tight gap 575 .

[0062] exist Figure 5A and 5BIn the example shown, actuators 515 and 520 adjust the gap between shroud 530 and blades 535 in two directions (e.g., contraction and expansion). Actuators 515 and 520 can be installed for a single shroud (e.g., shroud 530), a partial shroud set (e.g., a set of three shrouds, a set of five shrouds, etc.), or an entire shroud set in a turbine (e.g., a shroud surrounding 360 degrees of the inner surface of the casing 505).

[0063] Fig. 6A and 6B is a schematic cross-sectional view of a third exemplary embodiment of an ACC system 600 , 670 according to the teachings disclosed herein. Fig. 6A The exemplary ACC system 600 includes an exemplary housing 605, exemplary guide hooks 610A, 610B, an exemplary actuator 615, an exemplary actuator 620, an exemplary suspension 625, an exemplary shield 630, and an exemplary blade 635. The actuator 615 includes an exemplary piezoelectric stack 640 and an exemplary spring 645. The actuator 620 includes an exemplary piezoelectric stack 650 and an exemplary spring 655. The ACC system 600 includes an exemplary gap 660 between the shield 630 and the blade 635. Figure 6B An exemplary ACC system 670 includes Fig. 6A The housing 605 , the guide hooks 610A, 610B, the actuator 615 , the actuator 620 , the suspension 625 , the shield 630 and the blade 635 . Figure 6B The actuator 615 includes a piezoelectric stack 640 and a spring 645 . Figure 6B The exemplary actuator 620 includes a piezoelectric stack 650 and a spring 655 . The ACC system 670 includes an exemplary gap 675 between the shroud 630 and the blade 635 .

[0064] exist Fig. 6A and 6B In the example shown, the actuator 615 is located below the housing 605 on the guide hook 610A, and the actuator 620 is located below the housing 605 on the guide hook 610B. In some examples, the housing 605 is a housing surrounding a high pressure turbine (e.g., Figure 1 HP turbine 118), LP turbine (e.g., Figure 1 LP turbine 120) or compressor (e.g., Figure 1 In some examples, positioning actuator 615 and actuator 620 below housing 605 reduces the need for the actuator 615 and actuator 620 to move the actuator 615 and actuator 620 below housing 605, respectively. Figure 4A and 4BThe sealing problem that is prevalent in the exemplary ACC systems 400 and 460 is solved. However, the location of the actuator 615 and the actuator 620 hinders the ease of maintenance and component replacement. In the exemplary ACC systems 600 and 670, the actuator 615 includes a multi-layer stack of piezoelectric material 640 and a spring 645. In the exemplary ACC systems 600 and 670, the actuator 620 includes a multi-layer stack of piezoelectric material 650 and a spring 655. In some examples, the piezoelectric material of the multi-layer stack of piezoelectric materials 640 and 650 may include quartz, topaz, etc. However, other piezoelectric materials or other materials that produce linear displacement, such as shape memory alloy (SMA) materials, etc., may be additionally and / or optionally included. The multi-layer stack of piezoelectric material 640 and the multi-layer stack of piezoelectric material 650 each receive a control electrical signal to operate in the ACC systems 600 and 670. Actuators 615 and 620 include springs 645 and 655 without additional multi-layer stacks of piezoelectric material because the springs reduce the control complexity of actuators 615 and 620 (e.g., including springs 645 and 655 allows actuators 615 and 620 to each only need to receive one electrical control signal). However, compared to exemplary ACC systems 500 and 570, springs 645 and 655 in exemplary ACC systems 600 and 670 may cause uncertainty in linear displacement regulation.

[0065] exist Fig. 6A and 6B In the example shown, the suspension 625 extends into the actuator 615 and the actuator 620. Multiple layers of stacks of piezoelectric materials 640, 650 and springs 645, 655 are connected to the suspension 625 extension. The multiple layers of stacks of piezoelectric material 640 are connected to the top surface of the suspension 625 extension in the actuator 615. The spring 645 is connected to the bottom surface of the suspension 625 extension in the actuator 615. The multiple layers of stacks of piezoelectric material 650 are connected to the top surface of the suspension 625 extension in the actuator 620. The spring 655 is connected to the bottom surface of the suspension 625 extension in the actuator 620.

[0066] exist Fig. 6A and 6B In the example shown, a multi-layer stack of piezoelectric materials 640, 650 generates a linear displacement of the suspension 625 by an electrical signal generated by an exemplary controller. Figure 7 An exemplary controller for generating an electrical signal is shown in FIG. 6 and is described in further detail below. Springs 645, 655 provide a load to the bottom surface of the extension of suspension 625 based on the linear displacement of the multi-layer stack of piezoelectric materials 640, 650. Fig. 6A and 6BIn the example shown, the suspension 625 and the shield 630 are connected and move together. Therefore, the suspension 625 uses the linear displacement generated by the multi-layer stack of piezoelectric materials 640, 650 to move the shield 630. In some examples, the ACC system 600 includes the shield 630 without the suspension 625. In such an example, the shield 630 moves using the linear displacement generated by the multi-layer stack of piezoelectric materials 640, 650. The multi-layer stack of piezoelectric materials 640, 650 is positioned on the top surface of the extension of the suspension 625 in the actuator 615 and the actuator 620 to precisely adjust the linear displacement. The springs 645, 655 are positioned on the bottom surface of the extension of the suspension 625 in the actuator 615 and the actuator 620 to provide a spring load to the suspension 625 based on the linear displacement generated by the multi-layer stack of piezoelectric materials 640, 650. In some examples, the range of linear displacement is increased by adding more layers of piezoelectric material in the multilayer stack of piezoelectric material 640, 650. For example, the more layers added to the multilayer stack of piezoelectric material 640, 650, the greater the radial range of motion and muscle capacity of the ACC system.

[0067] exist Fig. 6A In the example shown, the ACC system 600 has an open gap, represented by an open gap 660 between the shroud 630 and the blade 635. The multi-layer stack of piezoelectric materials 640, 650 controls the open gap 660. In the ACC system 600, the actuator 615 and the actuator 620 receive a first electrical signal from the exemplary controller. The actuator 615 provides the first electrical signal to the multi-layer stack of piezoelectric material 640, and the actuator 620 provides the first electrical signal to the multi-layer stack of piezoelectric material 650. The first electrical signal causes a linear displacement (e.g., Fig. 6A In the example shown, each stack of the multilayer stack of piezoelectric material 640 is long and thin) and the multilayer stack of piezoelectric material 650 (as in Fig. 6A In the example shown, each stack of the multilayer stack of piezoelectric material 650 is long and thin. The springs 645, 655 provide a spring load to match the linear displacement of the multilayer stack of piezoelectric material 640, 650. For example, the springs 645, 655 extend to provide a load that matches the change in the linear displacement of the multilayer stack of piezoelectric material 640, 650. The linear displacement of the multilayer stack of piezoelectric material 640, 650 and the load from the springs 645, 655 move the suspension 625 and the shield 630 upward (e.g., away from the blade 635), which increases the opening gap 660.

[0068] exist Figure 6BIn the example shown, the ACC system 670 has a tight gap, represented by a tight gap 675 between the shroud 630 and the blade 635. The multi-layer stack of piezoelectric materials 640, 650 and the springs 645, 655 control the tight gap 675. In the ACC system 670, the actuator 615 and the actuator 620 receive a second electrical signal from the example controller. The actuator 615 provides the second electrical signal to the multi-layer stack of piezoelectric material 640, and the actuator 620 provides the second electrical signal to the multi-layer stack of piezoelectric material 650. The second electrical signal causes a linear displacement of the multi-layer stack of piezoelectric material 640 (e.g., as in Figure 6B In the example shown, each of the multiple stacks of piezoelectric material 640 is short and thick) and the multiple stacks of piezoelectric material 650 (e.g., as in Figure 6B In the example shown, each stack of the multi-layer stack of piezoelectric material 650 is short and thick. The springs 645, 655 provide a spring load to match the linear displacement of the multi-layer stack of piezoelectric material 640, 650. For example, the springs 645, 655 compress to provide a load that matches the change in the linear displacement of the multi-layer stack of piezoelectric material 640, 650. The linear displacement of the multi-layer stack of piezoelectric material 640, 650 and the load from the springs 645, 655 move the suspension 625 and the shield 630 downward (e.g., toward the blade 635), which reduces the tight gap 675.

[0069] exist Fig. 6A and 6B In the example shown, actuators 615 and 620 adjust the gap between shroud 630 and blades 635 in two directions (e.g., contraction and expansion). Actuators 615 and 620 can be installed for a single shroud (e.g., shroud 630), a partial shroud set (e.g., a set of three shrouds, a set of five shrouds, etc.), or an entire shroud set in a turbine (e.g., a shroud surrounding 360 degrees of the inner surface of casing 605).

[0070] Figure 7 is a block diagram of an exemplary controller 700 according to an exemplary ACC system 400-670 disclosed herein. Figure 7 , the controller 700 may be a full authority digital engine control (FADEC) unit, an engine control unit (ECU), an electronic engine control (EEC) unit, etc., or any other type of data acquisition and / or control computing device, a processor platform (e.g., a processor-based computing platform), etc. The controller 700 communicates with an exemplary engine sensor 710. The controller 700 includes an exemplary sensor processor 720 and an exemplary actuator controller 730.

[0071] exist Figure 7In the example shown, the controller 700 receives values ​​of a plurality of input variables related to flight conditions (e.g., air density, throttle stem position, engine temperature, engine pressure, direct clearance measurements, indirect clearance measurements, etc.). The controller 700 receives flight condition data from engine sensors 710. The engine sensors 710 may be mounted on the gas turbine engine 100 and / or positioned at other locations of the aircraft (e.g., on a wing, in a cockpit, in a main cabin, in an engine compartment, in cargo, etc.). The communication between the controller 700 and the engine sensors 710 may be, for example, one-way communication and / or two-way communication. The controller 700 uses the flight condition data to calculate engine operating parameters, such as fuel flow, stator vane position, exhaust valve position, etc.

[0072] exist Figure 7 In the example shown, the sensor processor 720 obtains sensor data from an exemplary engine sensor 710. The sensor data includes flight condition data obtained from the gas turbine engine 100. The sensor processor 720 monitors engine conditions based on the sensor data from the engine sensor 710. For example, the sensor processor 720 can calculate and monitor fuel flow, stator vane position, exhaust valve position, etc. In some examples, the sensor processor 720 determines whether the turbine casing is expanding or contracting based on the engine conditions determined by the obtained flight condition data. Figure 7 In the example shown, the actuator controller 730 generates electrical signals to the actuators of the ACC system. In some examples, the actuator controller 730 generates electrical control signals to the actuators of the ACC system 400 - 670 based on the results from the sensor processor 720 .

[0073] for Figure 4A and 4B In each of the exemplary ACC systems 400 and 460, the actuator controller 730 generates a first current and sends the first current to the multi-layer stack of piezoelectric material 450 located in the actuator 405 via a first electrical signal. In some examples, when the sensor processor 720 determines that the turbine casing is expanding, the actuator controller 730 sends the first current to the actuator 405. In some examples, the first current causes a linear displacement of the multi-layer stack of piezoelectric material 450, which moves the shroud 435 toward the blade 440 (similar to Figure 4B460 ). However, for additional and / or alternative flight conditions determined by the sensor processor 720 (e.g., flight conditions other than those indicating turbine casing expansion), the actuator controller 730 may send the first current to the actuator 405. In other examples, the actuator controller 730 generates a second current and sends the second current to the multi-layer stack of piezoelectric material 450 located in the actuator 405 via a second electrical signal. In some examples, when the sensor processor 720 determines that the turbine casing is contracting, the actuator controller 730 sends the second current to the actuator 405. In some examples, the second current causes a linear displacement of the multi-layer stack of piezoelectric material 450 that moves the shroud 435 away from the blades 440 (similar to Figure 4A However, for additional and / or alternative flight conditions determined by sensor processor 720 (e.g., flight conditions other than those indicating turbine case retraction), actuator controller 730 may send a second current to actuator 405.

[0074] for Figure 5A and 5B In the respective exemplary ACC systems 500 and 570 of FIG. 5 , the actuator controller 730 generates a first current and sends the first current to the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550 located in the actuator 515 and the actuator 520 via a first electrical signal, respectively. The actuator controller 730 also generates a second current and sends the second current to the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555 located in the actuator 515 and the actuator 520 via a second electrical signal, respectively. In some examples, when the sensor processor 720 determines that the turbine casing is expanding, the actuator controller sends the first current and the second current to the actuator 515 and the actuator 520. In some examples, the first current causes a first linear displacement of the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550. In some examples, the second current causes a second linear displacement of the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555. In some examples, the second linear displacement is opposite to the first linear displacement. For example, if the first linear displacement is an increase in length and a decrease in thickness of the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550, the second linear displacement is a decrease in length and an increase in thickness of the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555. The first linear displacement and the second linear displacement move shield 530 toward blade 535 (similar to Figure 5BHowever, for additional and / or alternative flight conditions determined by sensor processor 720 (e.g., flight conditions other than those indicating housing retraction), actuator controller 730 may send the first current and the second current to actuator 515 and actuator 520.

[0075] In other examples, the actuator controller 730 generates a third current and sends the third current to the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550 via a third electrical signal. The actuator controller 730 also generates a fourth current and sends the fourth current to the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555 via a fourth electrical signal. In some examples, when the sensor processor 720 determines that the housing is contracting, the actuator controller sends the third current and the fourth current to the actuator 515 and the actuator 520. In some examples, the third current causes a third linear displacement of the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550. In some examples, the fourth current causes a fourth linear displacement of the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555. In some examples, the fourth linear displacement is opposite to the third linear displacement. For example, if the third linear displacement is a decrease in length and an increase in thickness of the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550, the fourth linear displacement is an increase in length and a decrease in thickness of the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555. The third linear displacement and the fourth linear displacement cause shield 530 to move toward blade 535 (similar to Figure 5A However, for additional and / or alternative flight conditions determined by sensor processor 720 (e.g., flight conditions other than those indicating housing retraction), actuator controller 730 may send third and fourth currents to actuator 515 and actuator 520.

[0076] for Fig. 6A and 6B In the exemplary ACC systems 600 and 670 of the present invention, the actuator controller 730 generates a first current and sends the first current to the multi-layer stack of piezoelectric material 640 and the multi-layer stack of piezoelectric material 650 located in the actuator 615 and the actuator 620, respectively, via a first electrical signal. In some examples, when the sensor processor 720 determines that the housing is expanding, the actuator controller 730 sends the first current to the actuator 615 and the actuator 620. In some examples, the first current causes a linear displacement of the multi-layer stack of piezoelectric material 640 and the multi-layer stack of piezoelectric material 650, and the piezoelectric material 650 causes the shield 630 to move toward the blade 635 (similar to Figure 6B670 ). However, for additional and / or optional flight conditions determined by the sensor processor 720 (e.g., flight conditions other than those indicating shell expansion), the actuator controller 730 may send the first current to the actuator 615 and the actuator 620. In some examples, the actuator controller 730 generates a second current and sends the second current to the multi-layer stack of piezoelectric material 640 and the multi-layer stack of piezoelectric material 650 located in the actuator 615 and the actuator 620, respectively, via a second electrical signal. In some examples, when the sensor processor 720 determines that the shell is contracting, the actuator controller 730 sends the second current to the actuator 615 and the actuator 620. In some examples, the second current causes a linear displacement of the multi-layer stack of piezoelectric material 640 and the multi-layer stack of piezoelectric material 650, which causes the shield 630 to move away from the blade 635 (similar to Fig. 6A However, for additional and / or alternative flight conditions determined by sensor processor 720 (e.g., flight conditions other than those indicating turbine casing retraction), actuator controller 730 may send a second current to actuator 615 and actuator 620.

[0077] Although the implementation Figure 7 An exemplary embodiment of the controller 700 is shown in FIG. Figure 8 , 9 and 10, but Figure 8 , 9 One or more of the elements, processes and / or devices shown in and 10 may be combined, split, rearranged, omitted, eliminated and / or implemented in any other manner. In addition, the exemplary sensor processor 720, the exemplary actuator controller 725 and / or more generally, Figure 7 The exemplary controller 700 may be implemented by hardware, software, firmware, and / or any combination of hardware, software, and / or firmware. Thus, for example, any of the exemplary sensor processors 720, the exemplary actuator controllers 725, and / or more generally, the exemplary controller 700 may be implemented by one or more of analog or digital circuits, logic circuits, programmable processors, programmable controllers, graphics processing units (GPUs), digital signal processors (DSPs), application specific integrated circuits (ASICs), programmable logic devices (PLDs), and / or field programmable logic devices (FPLDs). When any device or system claim of this patent is read to cover pure software and / or firmware implementations, at least one of the exemplary sensor processor 720 and / or the exemplary actuator controller 725 is hereby expressly defined as comprising a non-transitory computer-readable storage device or storage disk, such as a memory, a compressed disk, etc., including software and / or firmware. Furthermore, in addition to or in lieu of Figure 8 ,9 and those elements, processes and / or devices shown in 10, Figure 7 The exemplary controller 700 may include one or more elements, processes and / or devices, and / or include more than one of any or all of the elements, processes and devices shown. As used herein, the phrase "communication" (including variations thereof) includes direct communication and / or indirect communication through one or more intermediate components, and does not require direct physical (e.g., wired) communication and / or fixed communication, but additionally includes selective communication at periodic intervals, predetermined intervals, non-periodic intervals and / or one-time events.

[0078] Figure 8 , 9 and 10 show the method for implementing Figure 7 700 is a flowchart representing exemplary hardware logic, machine readable instructions, hardware implemented state machines, and / or any combination thereof. The machine readable instructions may be executed by a computer processor and / or processor circuit (such as the following in combination with Fig.11 The exemplary processor platform 1200 discussed herein may be implemented as one or more executable programs or portions of executable programs executed by the processor 1212 shown in the exemplary processor platform 1200. The programs may be implemented in software stored on a non-transitory computer-readable storage medium such as a CD-ROM, floppy disk, hard drive, or memory associated with the processor 1212, but the entire program and / or portions thereof may alternatively be executed by a device other than the processor 1212 and / or implemented in firmware or dedicated hardware. In addition, although reference is made to Figure 8 , 9 , and the flowcharts shown in 10 describe an exemplary program. Many other methods of implementing the exemplary controller 700 may also be used. For example, the execution order of the boxes may be changed, and / or some of the boxes described may be changed, eliminated, or combined. Additionally or alternatively, any or all of the boxes may be implemented by one or more hardware circuits (e.g., discrete and / or integrated analog and / or digital circuits, FPGAs, ASICs, comparators, operational amplifiers (op-amps), logic circuits, etc.), which are configured to perform corresponding operations without executing software or firmware. The processor circuits may be distributed in different network locations and / or local one or more devices (e.g., a multi-core processor in a single machine, multiple processors distributed on a server architecture, etc.).

[0079] The machine-readable instructions described herein may be stored in one or more of a compressed format, an encrypted format, a segmented format, a compiled format, an executable format, an encapsulated format, and the like. The machine-readable instructions as described herein may be stored as data or a data structure (e.g., a portion of an instruction, a code, a code representation, and the like) that may be used to create, manufacture, and / or generate machine-executable instructions. For example, the machine-readable instructions may be segmented and stored on one or more storage devices and / or computing devices (e.g., servers) located at the same or different locations of a network or a collection of networks (e.g., in the cloud, in an edge device, and the like). The machine-readable instructions may require one or more of installation, modification, adaptation, update, combination, supplementation, configuration, decryption, decompression, unpacking, distribution, redistribution, compilation, and the like so that they are directly readable, parsable, and / or executable by a computing device and / or other machine. For example, the machine-readable instructions may be stored in multiple parts that are individually compressed, encrypted, and stored on separate computing devices, where when decrypted, decompressed, and combined, the parts form a set of executable instructions that implement one or more functions that may together form a program such as described herein.

[0080] In another example, the machine-readable instructions may be stored in a state where they are readable by processor circuitry, but require the addition of a library (e.g., a dynamic link library (DLL)), a software development kit (SDK), an application programming interface (API), etc., in order to execute the instructions on a particular computing device or other device. In another example, the machine-readable instructions may need to be configured (e.g., stored settings, data inputs, recorded network addresses, etc.) before the machine-readable instructions and / or corresponding programs can be executed in whole or in part. Thus, as used herein, a machine-readable medium may include machine-readable instructions and / or programs regardless of the particular format or state of the machine-readable instructions and / or programs when stored or otherwise at rest or in transmission.

[0081] The machine-readable instructions described herein may be represented by any past, present or future instruction language, scripting language, programming language, etc. For example, the machine-readable instructions may be represented using any of the following languages: C, C++, Java, C#, Perl, Python, JavaScript, HyperText Markup Language (HTML), Structured Query Language (SQL), Swift, etc.

[0082] As mentioned above, Figure 8 , 9and 10 may be implemented using executable instructions (e.g., computer and / or machine readable instructions) stored on a non-transitory computer and / or machine readable medium, such as a hard drive, flash memory, read-only memory, compact disk, digital versatile disk, cache, random access memory, and / or any other storage device or storage disk in which information is stored for any duration (e.g., longer periods of time, permanent, transient, temporary buffering and / or caching information). As used herein, the term non-transitory computer readable medium is expressly defined to include any type of computer readable storage device and / or storage disk, and does not include propagating signals and does not include transmission media.

[0083] "Include" and "comprising" (and all their forms and tenses) are used herein as open-ended terms. Thus, whenever a claim employs any form of "include" or "comprising" (e.g., includes, comprises, having, etc.) as a preamble or within any kind of claim recitation, it should be understood that additional elements, terms, etc. may be present without falling outside the scope of the corresponding claim or recitation. As used herein, when the phrase "at least" is used as a transitional term, such as in the preamble of a claim, it is open-ended in the same manner as the terms "include" and "comprising." When used in the form of, for example, A, B, and / or C, the term "and / or" refers to any combination or subset of A, B, and C, such as (1) only A, (2) only B, (3) only C, (4) A and B, (5) A and C, (6) B and C, and (7) A and B and C. As used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A and B" is intended to refer to embodiments that include any of (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A or B" is intended to refer to embodiments that include any of (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. As used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A or B" is intended to refer to embodiments that include any of (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A or B" is intended to refer to embodiments that include any of (1) at least one A, (2) at least one B, and (3) at least one A and at least one B.

[0084] As used herein, singular references (e.g., "a," "an," "first," "second," etc.) do not exclude the plural. The term "a" or "an" entity as used herein refers to one or more of that entity. The terms "a" (or "an"), "one or more," and "at least one" are used interchangeably herein. In addition, although listed separately, multiple devices, elements, or method actions may be implemented by, for example, a single unit or processor. In addition, although independent features may be included in different examples or claims, these may be combined, and the inclusion in different examples or claims does not mean that the combination of features is not feasible and / or advantageous.

[0085] Figure 8 is a flowchart representing machine readable instructions that are executed to combine Figure 4A , Figure 4B An exemplary ACC system is implemented Figure 7 At block 810, Figure 8 Execution of the routine 800 begins, wherein the example sensor processor 720 obtains sensor data from the example engine sensor 710. In some examples, the sensor data includes information obtained by the engine sensor 710 from the engine (e.g., Figure 1 In some examples, the flight condition data of the sensor data includes values ​​of multiple input variables related to flight conditions (e.g., air density, throttle stem position, engine temperature, engine pressure, etc.).

[0086] At block 815, the example sensor processor 720 monitors engine conditions based on the sensor data from the engine sensors 710. For example, the sensor processor 720 can use the flight condition data included in the sensor data to calculate and monitor fuel flow, stator vane position, exhaust valve position, etc. At block 820, the example sensor processor 720 determines whether the casing is expanding. In some examples, the casing is a part of a turbine engine that surrounds a high pressure turbine (e.g., Figure 1 HP turbine 118), low pressure turbine (e.g. Figure 1 LP turbine 120) and / or compressor (e.g., Figure 1In some examples, the sensor processor 720 determines whether the housing is expanding based on engine conditions determined by the obtained flight condition data. If the example sensor processor 720 determines that the housing is expanding, the example routine 800 continues to box 830, where the example actuator controller 730 sends a first current to the multi-layer stack of piezoelectric materials. If the example sensor processor 720 determines that the housing is not expanding, the example routine 800 continues to box 825, where the example sensor processor 720 determines whether the housing is contracting.

[0087] At block 825, the example sensor processor 720 determines whether the housing is contracting. In some examples, the sensor processor 720 determines whether the housing is contracting based on engine conditions determined by the obtained flight condition data. If the example sensor processor 720 determines that the housing is contracting, the example routine 800 continues to block 835 where the example actuator controller 730 sends a second current to the multi-layer stack of piezoelectric material. If the example sensor processor 720 determines that the housing is not contracting, the example routine 800 returns to block 810 where the example sensor processor 720 obtains sensor data.

[0088] At block 830, the example actuator controller 730 sends a first current to the multilayer stack of piezoelectric materials. In some examples, the actuator controller 730 generates the first current and sends the first current to the multilayer stack of piezoelectric materials via a first electrical signal. Figure 4A and 4B The first current causes a linear displacement of the multilayer stack of piezoelectric material 450 in the actuator 405. In some examples, the first current causes a linear displacement of the multilayer stack of piezoelectric material 450, which causes the shield 435 to move toward the blade 440 (similar to Figure 4B After the example actuator controller 730 sends the first current, routine 800 ends.

[0089] At block 835, the example actuator controller 730 sends a second current to the multilayer stack of piezoelectric material. In some examples, the multilayer stack of piezoelectric material is Figure 4A , 4B In some examples, actuator controller 730 generates a second current and sends the second current to the multi-layer stack of piezoelectric material 450 located in actuator 405 via a second electrical signal. In some examples, the second current causes a linear displacement of the multi-layer stack of piezoelectric material 450, which moves shield 435 away from blade 440 (similar to Figure 4AAfter the example actuator controller 730 sends the second current, routine 800 ends.

[0090] Fig. 9 is a flowchart representing machine readable instructions that are executed to combine Figure 5A , Figure 5B An exemplary ACC system is implemented Figure 7 The example controller 700 of FIG. 900 begins execution at block 910, where the example sensor processor 720 obtains sensor data from the example engine sensor 710. In some examples, the sensor data includes information from the engine sensor 710 (e.g., Figure 1 In some examples, the flight condition data of the sensor data includes values ​​of multiple input variables related to flight conditions (e.g., air density, throttle stem position, engine temperature, engine pressure, etc.).

[0091] At block 915, the example sensor processor 720 monitors engine conditions based on the sensor data from the engine sensors 710. For example, the sensor processor 720 can use the flight condition data included in the sensor data to calculate and monitor fuel flow, stator vane position, exhaust valve position, etc. At block 920, the example sensor processor 720 determines whether the casing is expanding. In some examples, the casing is a casing surrounding a high pressure turbine (e.g., Figure 1 HP turbine 118), low pressure turbine (e.g. Figure 1 LP turbine 120) or compressor (e.g., Figure 1 In some examples, the sensor processor 720 determines whether the casing is expanding based on engine conditions determined by the obtained flight condition data. If the example sensor processor 720 determines that the turbine casing is expanding, the example routine 900 continues to box 930, where the example actuator controller 730 sends a first current to the first multi-layer stack of piezoelectric material and the second multi-layer stack of piezoelectric material. If the example sensor processor 720 determines that the casing is not expanding, the example routine 900 continues to box 925, where the example sensor processor 720 determines whether the casing is contracting.

[0092] At block 925, the example sensor processor 720 determines whether the housing is contracting. In some examples, the sensor processor 720 determines whether the housing is contracting based on engine conditions determined by the obtained flight condition data. If the example sensor processor 720 determines that the housing is contracting, the example routine 900 continues to block 940 where the example actuator controller 730 sends a third current to the first multi-layer stack of piezoelectric material and the second multi-layer stack of piezoelectric material. If the example sensor processor 720 determines that the housing is not contracting, the example routine 900 returns to block 910 where the example sensor processor 720 obtains sensor data.

[0093] At block 930, the example actuator controller 730 sends a first current to the first multi-layer stack of piezoelectric material and the second multi-layer stack of piezoelectric material. In some examples, the first multi-layer stack of piezoelectric material is substantially similar to the multi-layer stack of piezoelectric material 540, and the second multi-layer stack of piezoelectric material is substantially similar to the multi-layer stack of piezoelectric material 550. In some examples, the actuator controller 730 generates the first current and sends the first current to the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550 located in actuator 515 and actuator 520, respectively, via a first electrical signal. In some examples, the first current causes a first linear displacement of the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550.

[0094] At block 935, the example actuator controller 730 sends a second current to the third multi-layer stack of piezoelectric material and the fourth multi-layer stack of piezoelectric material. In some examples, the third multi-layer stack of piezoelectric material is substantially similar to the multi-layer stack of piezoelectric material 545, and the fourth multi-layer stack of piezoelectric material is substantially similar to the multi-layer stack of piezoelectric material 555. In some examples, the actuator controller 730 generates a second current and sends the second current to the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555 located in the actuator 515 and the actuator 520, respectively, via a second electrical signal. In some examples, the second current causes a second linear displacement of the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555. In some examples, the second linear displacement is opposite to the first linear displacement. For example, if the first linear displacement is an increase in length and a decrease in thickness of the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550, the second linear displacement is a decrease in length and an increase in thickness of the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555. Although blocks 930 and 935 are shown sequentially, they may be performed in parallel. After the example actuator controller 730 sends the second current to the third multi-layer stack of piezoelectric material and the fourth multi-layer stack of piezoelectric material, the routine 900 ends.

[0095] At block 940, the example actuator controller 730 sends a third current to the first multi-layer stack of piezoelectric material and the second multi-layer stack of piezoelectric material. In some examples, the actuator controller 730 generates the third current and sends the third current to the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550 via a third electrical signal. In some examples, the third current causes a third linear displacement of the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550.

[0096] At box 945, the exemplary actuator controller 730 sends a fourth current to the third multi-layer stack of piezoelectric material and the fourth multi-layer stack of piezoelectric material. In some examples, the actuator controller 730 generates a fourth current and sends the fourth current to the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555 via a fourth electrical signal. In some examples, the fourth current causes a fourth linear displacement of the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555. In some examples, the fourth linear displacement is opposite to the third linear displacement. For example, if the third linear displacement is a decrease in length and an increase in thickness of the multi-layer stack of piezoelectric material 540 and the multi-layer stack of piezoelectric material 550, the fourth linear displacement is an increase in length and a decrease in thickness of the multi-layer stack of piezoelectric material 545 and the multi-layer stack of piezoelectric material 555. Although boxes 940 and 945 are not described in detail, the fourth linear displacement is not described in detail. Fig. 9 In the example of FIG. 9 , the routine 900 is shown sequentially, but in some examples, they may be performed in parallel. After the example actuator controller 730 sends the fourth current to the third multilayer stack of piezoelectric material and the fourth multilayer stack of piezoelectric material, the routine 900 ends.

[0097] Fig.10 is a flowchart representing machine readable instructions that are executed to combine Fig. 6A , Figure 6B The exemplary ACC systems 600 and 670 are implemented Figure 7 The exemplary controller 700 of FIG. 1000 includes a first controller 700 and a second controller 700. At block 1010, Fig.10 Execution of routine 1000 begins, where the example sensor processor 720 obtains sensor data from the example engine sensor 710. In some examples, the sensor data includes information obtained by the engine sensor 710 from the engine (e.g., Figure 1 In some examples, the flight condition data of the sensor data includes values ​​of multiple input variables related to flight conditions (e.g., air density, throttle stem position, engine temperature, engine pressure, etc.).

[0098] At block 1015, the example sensor processor 720 monitors engine conditions based on the sensor data from the engine sensors 710. For example, the sensor processor 720 can use the flight condition data included in the sensor data to calculate and monitor fuel flow, stator vane position, exhaust valve position, etc. At block 1020, the example sensor processor 720 determines whether the casing is expanding. In some examples, the casing is a portion of the turbine engine surrounding a high pressure turbine (e.g., Figure 1 HP turbine 118), low pressure turbine (e.g. Figure 1 LP turbine 120) or compressor (e.g., Figure 1 In some examples, the sensor processor 720 determines whether the housing is expanding based on engine conditions determined by the obtained flight condition data. If the example sensor processor 720 determines that the housing is expanding, the example routine 1000 continues to box 1030, where the example actuator controller 730 sends a first current to the first multi-layer stack of piezoelectric material and the second multi-layer stack of piezoelectric material. If the example sensor processor 720 determines that the housing is not expanding, the example routine 1000 continues to box 1025, where the example sensor processor 720 determines whether the housing is contracting.

[0099] At block 1025, the example sensor processor 720 determines whether the housing is contracting. In some examples, the sensor processor 720 determines whether the housing is contracting based on engine conditions determined by the obtained flight condition data. If the example sensor processor 720 determines that the housing is contracting, the example routine 1000 continues to block 1035 where the example actuator controller 730 sends a second current to the first multi-layer stack of piezoelectric material and the second multi-layer stack of piezoelectric material. If the example sensor processor 720 determines that the housing is not contracting, the example routine 1000 returns to block 1010 where the example sensor processor 720 obtains sensor data.

[0100] At block 1030, the example actuator controller 730 sends a first current to the first multi-layer stack of piezoelectric material and the second multi-layer stack of piezoelectric material. In some examples, the first multi-layer stack of piezoelectric material is substantially similar to the multi-layer stack of piezoelectric material 640, and the second multi-layer stack of piezoelectric material is substantially similar to the multi-layer stack of piezoelectric material 650. In some examples, the actuator controller 730 generates a first current and sends the first current to the multi-layer stack of piezoelectric material 640 and the multi-layer stack of piezoelectric material 650 located in the actuator 615 and the actuator 620, respectively, via a first electrical signal. In some examples, the first current causes a linear displacement of the multi-layer stack of piezoelectric material 640 and the multi-layer stack of piezoelectric material 650, which causes the shield 630 to move toward the blade 635 (similar to Figure 6B After the example actuator controller 730 sends the first current, routine 1000 ends.

[0101] At block 1035, the example actuator controller 730 sends a second current to the first multi-layer stack of piezoelectric material and the second multi-layer stack of piezoelectric material. In some examples, the actuator controller 730 generates the second current and sends the second current to the multi-layer stack of piezoelectric material 640 and the multi-layer stack of piezoelectric material 650 located in the actuator 615 and the actuator 620, respectively, via a second electrical signal. In some examples, the second current causes a linear displacement of the multi-layer stack of piezoelectric material 640 and the multi-layer stack of piezoelectric material 650, which moves the shield 630 away from the blade 635 (similar to Fig. 6A 1000 ). Although blocks 1030 and 1035 are shown in sequence, they may be performed in parallel. After the example actuator controller 730 sends the second current, routine 1000 ends.

[0102] Fig.11 is constructed to execute Figure 8 , 9 And 10 instructions to achieve Figure 7 The processor platform 1100 can be, for example, a server, a personal computer, a workstation, a self-learning machine (e.g., a neural network), a mobile device (e.g., an iPad, etc.). TM tablet computer) or any other type of computing device.

[0103] The processor platform 1100 of the illustrated example includes a processor 1112. The processor 1112 of the illustrated example is hardware. For example, the processor 1112 can be implemented by one or more integrated circuits, logic circuits, microprocessors, GPUs, DSPs, or controllers of any desired family or manufacturer. The hardware processor can be a semiconductor-based (e.g., silicon-based) device. In this example, the processor implements the exemplary sensor processor 720 and the exemplary actuator controller 730.

[0104] The processor 1112 of the illustrated example includes a local memory 1113 (e.g., a cache). The processor 1112 of the illustrated example communicates with a main memory including a volatile memory 1114 and a non-volatile memory 1116 via a bus 1118. The volatile memory 1114 may be a synchronous dynamic random access memory (SDRAM), a dynamic random access memory (DRAM), Dynamic Random Access Memory The main memory 1114 and 1116 may be implemented by a memory controller.

[0105] The processor platform 1100 of the illustrated example also includes an interface circuit 1120. The interface circuit 1120 may be implemented by any type of interface standard, such as an Ethernet interface, a universal serial bus (USB), a Bluetooth interface, a near field communication interface (NFC), and / or a PCI Express interface.

[0106] In the example shown, one or more input devices 1122 are connected to the interface circuit 1120. The input devices 1122 allow a user to enter data and / or commands into the processor 1112. The input devices may be implemented by, for example, an audio sensor, a microphone, a camera (still or video), a keyboard, buttons, a mouse, a touch screen, a trackpad, a trackball, an isopoint, and / or a voice recognition system.

[0107] One or more output devices 1124 are also connected to the interface circuit 1120 of the illustrated example. For example, the output device 1124 may be implemented by a display device (e.g., a light emitting diode (LED), an organic light emitting diode (OLED), a liquid crystal display (LCD), a cathode ray tube display (CRT), an in-place switching (IPS) display, a touch screen, etc.), a tactile output device, a printer, and / or a speaker. Therefore, the interface circuit 1120 of the illustrated example typically includes a graphics driver card, a graphics driver chip, and / or a graphics driver processor.

[0108] The interface circuitry 1120 of the illustrated example also includes communication devices, such as transmitters, receivers, transceivers, modems, residential gateways, wireless access points, and / or network interfaces, to facilitate the exchange of data with external machines (e.g., any type of computing device) via the network 1126. Communications may be via, for example, an Ethernet connection, a digital subscriber line (DSL) connection, a telephone line connection, a coaxial cable system, a satellite system, a field wireless system, a cellular telephone system, etc.

[0109] The processor platform 1100 of the illustrated example also includes one or more mass storage devices 1128 for storing software and / or data. Examples of such mass storage devices 1128 include floppy disk drives, hard disk drives, optical disk drives, and redundant array of independent disks (RAID) systems.

[0110] Figure 8 , 9 The machine-executable instructions 1132 of and 10 may be stored in the mass storage device 1128, in the volatile memory 1114, in the non-volatile memory 1116, and / or on a removable, non-transitory computer-readable storage medium such as a CD or DVD.

[0111] In light of the foregoing, it should be understood that exemplary methods, apparatus, and articles of manufacture for improving clearance control in a gas turbine engine have been disclosed. The disclosed examples present an improved ACC design using a piezoelectric actuator to achieve tighter clearances under any operating conditions through rapid mechanical ACC adjustments. The disclosed examples use piezoelectric materials to generate high mechanical power and provide fast response clearance control in two directions (inward and outward) without time delay. The disclosed examples use multi-layer stacks of piezoelectric materials to manage the range of displacement, which affects the range of ACC system muscle capabilities. The disclosed examples present a simpler ACC design, reducing weight and increasing underhood space to allow for freer installation of other components of the gas turbine engine. The disclosed examples improve engine performance and EGT control capabilities, with the additional advantage of SFC because the mechanical ACC system does not require cooling airflow, thereby saving airflow.

[0112] Disclosed herein are exemplary methods, apparatus, systems, and articles of manufacture for providing a fast response active gap control system with a piezoelectric actuator. Other examples and combinations thereof include:

[0113] Example 1 includes an apparatus for controlling clearance of a turbine engine, the apparatus comprising: a casing surrounding at least a portion of the turbine engine, the at least a portion of the turbine engine including at least one of a shroud or a suspension to accommodate airflow in at least a portion of the turbine engine; an actuator controlling a clearance between a blade and at least one of the shroud or the suspension, the actuator comprising a multi-layer stack of material, and wherein the actuator is external to the casing; and a rod coupled to the actuator and at least one of the shroud or the suspension through an opening in the casing, the rod moving at least one of the shroud or the suspension based on the multi-layer stack of material.

[0114] Example 2 includes the apparatus of any preceding clause, wherein at least a portion of the turbine engine includes a turbine or a compressor.

[0115] Example 3 includes the apparatus of any preceding clause, wherein the actuator controls the clearance for a shroud set in at least a portion of the turbine engine or for a portion of a shroud set in at least a portion of the turbine engine.

[0116] Example 4 includes the apparatus of any of the preceding clauses, the apparatus further comprising a seal coupled to the stem, the seal preventing leakage through the opening in the housing.

[0117] Example 5 includes the apparatus of any of the preceding clauses, wherein the housing is coupled to at least one of the shroud or the suspension using a guide hook.

[0118] Example 6 includes the device of any of the preceding clauses, wherein the multilayer stack of material includes at least one of a piezoelectric material or a shape memory alloy.

[0119] Example 7 includes the apparatus of any preceding clause, the apparatus further comprising a controller operably coupled to the actuator, the controller providing current to the multilayer stack of materials in the actuator.

[0120] Example 8 includes the apparatus of any preceding clause, wherein the multilayer stack of materials is displaced by an electric current.

[0121] Example 9 includes the apparatus of any preceding clause, wherein the actuator uses displacement of a multi-layer stack of materials to control a clearance between the blade and at least one of the shroud or the suspension.

[0122] Example 10 includes an apparatus for controlling clearance of a turbine engine, the apparatus comprising: a housing surrounding at least a portion of the turbine engine, the at least a portion of the turbine engine including at least one of a shroud or a suspension to contain airflow in the turbine engine; a first actuator controlling a clearance between a blade and at least one of the shroud or the suspension, the first actuator comprising a first multi-layer stack of material, and wherein the first actuator is coupled to at least one of a first hook of the shroud or the suspension; and a second actuator controlling a clearance between the blade and at least one of the shroud or the suspension, the second actuator comprising a second multi-layer stack of material, and wherein the second actuator is coupled to at least one of a second hook of the shroud or the suspension.

[0123] Example 11 includes the apparatus of any preceding clause, wherein at least a portion of the turbine engine includes a turbine or a compressor.

[0124] Example 12 includes the apparatus of any preceding clause, wherein the first actuator and the second actuator control clearance for a shroud set in at least a portion of the turbine engine or for a partial shroud set in at least a portion of the turbine engine.

[0125] Example 13 includes the device of any of the preceding clauses, wherein the first multi-layer stack of material and the second multi-layer stack of material include at least one of a piezoelectric material or a shape memory alloy.

[0126] Example 14 includes the apparatus of any of the preceding clauses, the first actuator further comprising a third multi-layer stack of material, and the second actuator further comprising a fourth multi-layer stack of material.

[0127] Example 15 includes an apparatus of any of the preceding clauses, wherein a first multilayer stack of material is coupled to a top surface of at least one of a shield or a first hook of a suspension and a bottom surface of a housing, and wherein a third multilayer stack of material is coupled to a bottom surface of at least one of a shield or a first hook of a suspension.

[0128] Example 16 includes an apparatus of any of the foregoing clauses, wherein a third multilayer stack of material is connected to a top surface of at least one of the second hooks of the shield or suspension and a bottom surface of the shell, and wherein a fourth multilayer stack of material is connected to a bottom surface of at least one of the second hooks of the shield or suspension.

[0129] Example 17 includes the apparatus of any of the preceding clauses, the first actuator further comprising a first spring, and the second actuator further comprising a second spring.

[0130] Example 18 includes the apparatus of any of the preceding clauses, wherein the first multilayer stack of material is coupled to a top surface of at least one of the first hooks of the shield or suspension and a bottom surface of the housing, and wherein the first spring is coupled to a bottom surface of at least one of the first hooks of the shield or suspension.

[0131] Example 19 includes the apparatus of any of the preceding clauses, wherein a second multilayer stack of material is coupled to a top surface of at least one of the second hooks of the shield or suspension and a bottom surface of the housing, and wherein a second spring is coupled to a bottom surface of at least one of the second hooks of the shield or suspension.

[0132] Example 20 includes the apparatus of any of the preceding clauses, the apparatus further comprising a controller operably coupled to the first actuator and the second actuator, the controller providing a first current to the first multi-layer stack of material and the second multi-layer stack of material.

[0133] Example 21 includes the apparatus of any of the preceding clauses, wherein the controller provides the second current to the third multilayer stack of material and the fourth multilayer stack of material.

[0134] Example 22 includes the apparatus of any of the preceding clauses, wherein the first multilayer stack of material and the third multilayer stack of material are displaced by a first current, and the third multilayer stack of material and the fourth multilayer stack of material are displaced by a second current.

[0135] Example 23 includes an apparatus of any of the preceding clauses, wherein the first actuator and the second actuator use displacement of a first multi-layer stack of material, a second multi-layer stack of material, a third multi-layer stack of material, and a fourth multi-layer stack of material to control a gap between at least one of the shroud or suspension and the blade.

[0136] Example 24 includes the apparatus of any of the preceding clauses, the apparatus further comprising a controller operably coupled to the first actuator and the second actuator, the controller providing current to the first multi-layer stack of material and the second multi-layer stack of material.

[0137] Example 25 includes the apparatus of any of the preceding clauses, wherein the first multilayer stack of material and the second multilayer stack of material are displaced by an electric current.

[0138] Example 26 includes an apparatus of any of the preceding clauses, wherein the first actuator and the second actuator use displacement of a first multi-layer stack of material and a second multi-layer stack of material to control a gap between the blade and at least one of the shroud or the suspension, and wherein the first spring supports the displacement of the first multi-layer stack of material, and the second spring supports the displacement of the second multi-layer stack of material.

[0139] Example 27 includes a non-transitory computer-readable medium comprising instructions that, when executed, cause at least one processor to at least: monitor a condition parameter from a sensor device in a turbine engine; determine when the turbine engine condition indicates that a casing is expanding or is contracting, wherein the turbine engine condition is based on the condition parameter and the casing surrounds at least a portion of the turbine engine; in response to determining that the turbine engine condition indicates that the casing is expanding, transmit a first current to a multi-layer stack of materials; and in response to determining that the turbine engine condition indicates that the casing is contracting, transmit a second current to the multi-layer stack of materials.

[0140] Example 28 includes the non-transitory computer readable medium of any preceding clause, wherein at least a portion of the turbine engine comprises a turbine or a compressor.

[0141] Example 29 includes the non-transitory computer-readable medium of any preceding clause, wherein the condition parameter comprises a temperature measurement, a pressure measurement, or an air density measurement.

[0142] Example 30 includes the non-transitory computer readable medium of any preceding clause, wherein the multilayer stack of material includes at least one of a piezoelectric material or a shape memory alloy.

[0143] Example 31 includes a non-transitory computer-readable medium of any of the foregoing clauses, wherein the multi-layer stack of material is a first multi-layer stack of material, and wherein when the instructions are executed, causes at least one processor to: in response to determining that a turbine engine condition indicates that the casing is expanding, transmit a first current to a second multi-layer stack of material, and transmit a second current to a third multi-layer stack of material and a fourth multi-layer stack of material; and in response to determining that the turbine engine condition indicates that the casing is contracting, transmit a third current to the first multi-layer stack of material and the second multi-layer stack of material; and transmit a fourth current to the third multi-layer stack of material and the fourth multi-layer stack of material.

[0144] Example 32 includes a non-transitory computer-readable medium of any of the foregoing clauses, wherein the multi-layer stack of material is a first multi-layer stack of material, and wherein when the instructions are executed, causes at least one processor to: in response to determining that a turbine engine condition indicates that the casing is expanding, transmit a first current to a second multi-layer stack of material; and in response to determining that the turbine engine condition indicates that the casing is contracting, transmit a second current to the first multi-layer stack of material and the second multi-layer stack of material.

[0145] Although certain exemplary methods, apparatus, and articles are disclosed herein, the scope of coverage of this patent is not limited thereto. For example, the disclosed exemplary methods, apparatus, and articles are implemented in conjunction with a gas turbine engine, whereas the disclosed examples may be implemented in conjunction with a compressor. Instead, this patent covers all methods, apparatus, and articles that fall within the scope of the claims of this patent.

[0146] The claims are hereby incorporated into the Detailed Description by reference, with each claim standing on its own as a separate embodiment of the disclosure.

Claims

1. A device for controlling clearance of a turbine engine, characterized in that: The device comprises: a casing surrounding at least a portion of the turbine engine, the at least a portion of the turbine engine including at least one of a shroud or a suspension to contain airflow in the at least a portion of the turbine engine; an actuator that controls a clearance between a blade and said at least one of said shroud or said suspension, said actuator comprising a multi-layer stack of materials, and wherein said actuator is external to said housing; a stem coupled to the actuator and the at least one of the shroud or the suspension through an opening in the housing, the stem moving the at least one of the shroud or the suspension based on the multi-layer stack of materials; and A controller, the controller being used to: monitoring condition parameters from sensor devices in the turbine engine; determining when a turbine engine condition indicates that a casing is expanding or contracting, wherein the turbine engine condition is based on the condition parameter, the casing surrounding at least a portion of the turbine engine, the at least a portion of the turbine engine including a turbine or a compressor; In response to determining that the turbine engine condition indicates that the casing is expanding, transmitting a first electrical current to the multi-layer stack of materials; and In response to determining that the turbine engine condition indicates that the casing is shrinking, a second electrical current is transmitted to the multi-layer stack of materials.

2. The device according to claim 1, characterized in that The at least one portion of the turbine engine includes a turbine or a compressor.

3. The device according to claim 1, characterized in that The actuator controls a clearance for a set of shrouds in the at least a portion of the turbine engine or for a partial set of shrouds in the at least a portion of the turbine engine.

4. The device according to claim 1, characterized in that The multi-layer stack of materials includes at least one of a piezoelectric material or a shape memory alloy.

5. The device according to claim 4, characterized in that The apparatus further includes a controller operably coupled to the actuator, the controller providing an electric current to the multi-layer stack of material in the actuator, the multi-layer stack of material being displaced by the electric current.

6. The device according to claim 5, characterized in that The actuator uses displacement of the multi-layer stack of materials to control a clearance between the blade and the at least one of the shroud or the suspension.

7. A device for controlling clearance of a turbine engine, characterized in that: The device comprises: a casing surrounding at least a portion of the turbine engine, the at least a portion of the turbine engine including at least one of a shroud or a suspension to contain airflow in the turbine engine; a first actuator that controls a clearance between a blade and the at least one of the shroud or the suspension, the first actuator comprising a first multi-layer stack of material, and wherein the first actuator is coupled to the at least one of the first hook of the shroud or the suspension; a second actuator that controls a clearance between the blade and the at least one of the shroud or the suspension, the second actuator comprising a second multi-layer stack of material, and wherein the second actuator is coupled to the at least one of the second hooks of the shroud or the suspension; and A controller, the controller being used to: monitoring condition parameters from sensor devices in the turbine engine; determining when a turbine engine condition indicates that a casing is expanding or contracting, wherein the turbine engine condition is based on the condition parameter, the casing surrounding at least a portion of the turbine engine, the at least a portion of the turbine engine including a turbine or a compressor; In response to determining that the turbine engine condition indicates that the casing is expanding, transmitting a first electrical current to the first multi-layer stack of material and the second multi-layer stack of material; and In response to determining that the turbine engine condition indicates that the casing is shrinking, a second electrical current is transmitted to the first multi-layer stack of material and the second multi-layer stack of material.

8. The device according to claim 7, characterized in that The at least one portion of the turbine engine includes a turbine or a compressor.

9. The device according to claim 7, characterized in that The first multi-layer stack of materials and the second multi-layer stack of materials include at least one of a piezoelectric material or a shape memory alloy.

10. The device according to claim 9, characterized in that The first actuator further comprises a third multi-layer stack of material and the second actuator further comprises a fourth multi-layer stack of material.

11. The device according to claim 7, characterized in that The first actuator further includes a first spring, and the second actuator further includes a second spring.

12. The device according to claim 10, characterized in that The device further includes a controller, which is operably connected to the first actuator and the second actuator, and the controller provides a first current to the first multi-layer stack of the material and the second multi-layer stack of the material, and the controller provides a second current to the third multi-layer stack of the material and the fourth multi-layer stack of the material.

13. The device according to claim 12, characterized in that The first multilayer stack of material and the third multilayer stack of material are displaced by the first current, and the third multilayer stack of material and the fourth multilayer stack of material are displaced by the second current.

14. The device according to claim 13, characterized in that The first actuator and the second actuator control a clearance between the blade and the at least one of the shroud or the suspension using displacement of the first multi-layer stack of material, the second multi-layer stack of material, the third multi-layer stack of material, and the fourth multi-layer stack of material.

15. The device according to claim 11, characterized in that The device further includes a controller, which is operably connected to the first actuator and the second actuator, and the controller provides an electric current to the first multi-layer stack of material and the second multi-layer stack of material, and the first multi-layer stack of material and the second multi-layer stack of material are displaced by the electric current.

16. The device according to claim 15, characterized in that The first actuator and the second actuator use displacement of the first multi-layer stack of material and the second multi-layer stack of material to control the gap between the blade and at least one of the shroud or the suspension, and wherein the first spring supports the displacement of the first multi-layer stack of material and the second spring supports the displacement of the second multi-layer stack of material.

17. A non-transitory computer-readable medium comprising instructions, characterized in that: When the instructions are executed, at least one processor is caused to at least: monitoring condition parameters from sensor devices in the turbine engine; determining when a turbine engine condition indicates that a casing is expanding or contracting, wherein the turbine engine condition is based on the condition parameter, the casing surrounding at least a portion of the turbine engine, the at least a portion of the turbine engine including a turbine or a compressor; In response to determining that the turbine engine condition indicates that the casing is expanding, transmitting a first electrical current to the first multi-layer stack of material and the second multi-layer stack of material; as well as In response to determining that the turbine engine condition indicates that the casing is shrinking, a second electrical current is transmitted to the first multi-layer stack of material and the second multi-layer stack of material.

18. The non-transitory computer readable medium of claim 17, wherein: The condition parameter includes a temperature measurement, a pressure measurement, or an air density measurement.

19. The non-transitory computer readable medium of claim 17, wherein: The multi-layer stack of materials includes at least one of a piezoelectric material or a shape memory alloy.

20. The non-transitory computer readable medium of claim 19, wherein: When the instructions are executed, the at least one processor is caused to: In response to determining that the turbine engine condition indicates that the casing is expanding: transmitting the second current to a third multilayer stack of material and a fourth multilayer stack of material; as well as In response to determining that the turbine engine condition indicates that the casing is contracting: transmitting a third current to the first multi-layer stack of materials and the second multi-layer stack of materials; as well as A fourth current is transmitted to the third multilayer stack of materials and the fourth multilayer stack of materials.

Images