Flexible shroud for curved beam stack structure

Abstract

A flexure beam stack structure compliant shroud for a gas turbine engine is disclosed. An example shroud assembly includes a plurality of concave flexure beams, a plurality of convex flexure beams, and a plurality of bumpers, wherein a first concave flexure beam of the plurality of concave flexure beams is counter-coupled with a first convex flexure beam of the plurality of convex flexure beams, a second concave flexure beam of the plurality of concave flexure beams is counter-coupled with a second convex flexure beam of the plurality of convex flexure beams, the first and second concave flexure beams are configured to stack on top of the first and second convex flexure beams, a first bumper of the plurality of bumpers is coupled to the first and second concave flexure beams, and a second bumper of the plurality of bumpers is coupled to the first and second convex flexure beams.

Description

Technical Field

[0001] This disclosure generally relates to shielding assemblies for gas turbines, and more specifically, to shielding assemblies with flexible curved beam stack structures. Background Technology

[0002] In a particular configuration, the compressor section of the engine comprises a high-pressure (HP) compressor and a low-pressure (LP) compressor in a sequential flow order. Similarly, the turbine section of the engine comprises a high-pressure (HP) turbine and a low-pressure (LP) turbine in a sequential flow order. The HP compressor, LP compressor, HP turbine, and LP turbine each comprise one or more rows of circumferentially spaced rotor blades spaced axially. Each rotor blade includes a blade tip. One or more shrouds may be radially outwardly positioned from the rotor blades and circumferentially surround the rotor blades. Attached Figure Description

[0003] This specification sets forth a complete and enabling disclosure for those skilled in the art, including its best mode, with reference to the accompanying drawings, wherein:

[0004] Figure 1 shows a cross-sectional view of an existing gas turbine engine.

[0005] Figure 2A and 2B A one-dimensional example of a flexible shield for a curved beam stack structure implemented according to the teachings of this disclosure is depicted.

[0006] Figure 3 Example graphs showing the force and deflection of the elastic buckling beam component of a flexible shield in a bent beam stack structure are presented.

[0007] Figure 4 This describes the example deflection response of a shielding structure for the flexibility of a bent beam stack within different classes of stiffness.

[0008] Figure 5A and 5B A three-dimensional example of a flexible shield for a curved beam stack structure implemented according to the teachings of this disclosure is depicted.

[0009] Figure 6 This is an illustration of a flexible protective enclosure assembly for an example of a bent beam stacked structure.

[0010] Figure 7 This is an illustration of a flexible shield assembly of an example curved beam stack structure within an example compressor.

[0011] Figure 8 An example flexible shield assembly of a curved beam stack structure within an existing compressor architecture is depicted, which is used as an active control system for the compressor.

[0012] Figure 9A flexible shroud assembly for an example curved beam stacked structure within an example compressor is depicted, including compressor housing slots for the structure; and

[0013] Figure 10A and 10B Visualizations of the 360-degree circumferential hairpin damper shield assembly and the discrete sector hairpin damper shield assembly as vibration damping mechanisms are provided.

[0014] These figures are not to scale. Instead, the thickness of layers or regions may be enlarged in the figures. Generally, the same reference numerals will be used throughout the figures and the accompanying written description to refer to the same or similar parts. As used herein, a statement that any part (e.g., layer, film, area, region, or plate) is on another part in any way (e.g., positioned on another part, located on another part, disposed on or formed on another part, etc.) indicates that the referred part is either in contact with the other part or that the referred part is above the other part, with one or more intermediate parts located between them. Connection references (e.g., attachment, coupling, connection, combination, separation, detachment, disconnection, separation, etc.) should be interpreted broadly and may include intermediate elements between sets of elements and relative movement between elements, unless otherwise stated. As used herein, the term "detachable" refers to the ability of two parts to be attached, joined, and / or otherwise combined, and then to be separated, disconnected, and / or otherwise nondestructively separated from each other (e.g., by removing one or more fasteners, removing connecting parts, etc.). Therefore, a connection / disconnection reference does not necessarily imply that two components are directly connected and fixed to each other. Declaring any part "in contact" with another part means that there are no intermediate parts between the two parts.

[0015] When identifying multiple elements or components that can be individually referred to, descriptive terms such as “first,” “second,” “third,” etc., are used herein. Unless otherwise specified or understood according to the context in which they are used, such descriptive terms are not intended to infer any meaning of priority, physical order, or arrangement in the list, or chronological order, but are merely used as markers to individually refer to multiple elements or components to facilitate understanding of the disclosed examples. In some examples, the descriptive term “first” may be used to refer to an element in the detailed description, while the same element may be referred to in the claims by different descriptive terms (such as “second” or “third”). In such cases, it should be understood that the use of such descriptive terms is merely for the convenience of referring to multiple elements or components. Detailed Implementation

[0016] Known shield assemblies for gas turbine engines provide a deflection response similar to a linear spring when loaded. The example shield assemblies disclosed herein provide a structure stacked with a bending beam, inherently equipped with elastic buckling behavior. In some examples, the elastic buckling nature of the stacked bending beam allows for a soft stiffness during blade-structure friction, causing the structure to conform to the shape of the airfoil upon blade contact. Furthermore, the example shield assemblies disclosed herein include a series of dampers along the stacked bending beam that engage with each other when loaded, thereby increasing the stiffness of the shield assembly and providing a further damping effect.

[0017] This document uses various terms to describe the orientation of features. As used herein, the orientation of features, forces, and moments is described with reference to the yaw, pitch, and roll axes of the vehicle associated with the features, forces, and moments. Typically, the accompanying figures are annotated with reference to the axial, radial, and circumferential directions of the gas turbine associated with the features, forces, and moments. Typically, the accompanying figures are annotated using a set of axes, including the roll axis R, pitch axis P, and yaw axis Y. As used herein, the terms "longitudinal" and "axial" are used interchangeably to refer to a direction parallel to the roll axis. As used herein, the term "lateral" is used to refer to a direction parallel to the pitch axis. As used herein, the terms "vertical" and "perpendicular" are used interchangeably to refer to a direction parallel to the yaw axis.

[0018] In some examples used herein, the term “substantially” is used to describe a relationship between two parts within three degrees of said relationship (e.g., substantially collinear relationship within three degrees of linearity, substantially perpendicular relationship within three degrees of verticality, substantially parallel relationship within three degrees of parallelism, etc.). As used herein, the term “link” refers to a connection between two parts that restricts the relative movement of the two parts (e.g., restricting at least one degree of freedom of the parts, etc.). “Comprising” and “including” (and all forms and tenses thereof) are used herein as open-ended terms. Therefore, whenever a claim uses any form of “comprising” or “including” (e.g., including, comprising, including, including, having, etc.) as a preamble or in any type of claim statement, it should be understood that additional elements, terms, etc., may be present without exceeding the scope of the corresponding claim or statement. 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, just as the terms “comprising” and “including” are open-ended. For example, when used in the form of A, B, and / or C, the term “and / or” refers to any combination or subset of A, B, and C, such as (1) A alone, (2) B alone, (3) C alone, (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 an implementation that includes any one 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 an implementation that includes any one 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 and B" is intended to refer to an implementation that includes (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 an implementation that includes (1) at least one A, (2) at least one B and (3) at least one A and at least one B.

[0019] As used herein, singular references (e.g., "a," "an," "first," "second," etc.) do not exclude multiples. The term "a" or "an" 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. Furthermore, although listed separately, multiple means, elements, or method actions can be implemented by, for example, a single unit or processor. Moreover, although individual features may be included in different examples or claims, these features may be combined, and inclusion in different examples or claims does not mean that such combinations of features are not feasible and / or advantageous.

[0020] Many gas turbine engine architectures include a shroud that is radially outwardly positioned from the engine's rotor blades and circumferentially surrounds them. The proximity of the rotor blades to the shroud assembly results in frequent physical contact between the blades and the shroud, ultimately leading to blade tip loss. Current methods for avoiding and / or mitigating blade tip loss involve increasing the clearance between the blades and the shroud to provide a larger gap between the blade tips and the shroud. However, this increased clearance leads to variations in airflow within the turbine. For example, a larger clearance may cause a portion of the airflow through the turbine to escape, thus reducing the overall turbine efficiency and increasing overall fuel consumption. Furthermore, current shroud assemblies designed to mitigate blade tip loss involve linear spring mechanisms that deflect radially inward in response to blade tip contact. However, the degree of radial inward deflection is limited and does not provide air damping and / or cushioning effects to allow for active control of airflow in the compressor and / or turbine.

[0021] The examples disclosed herein overcome the aforementioned drawbacks by stacking a set of curved beams to form a shroud (referred to herein as a flexible shroud of curved beam stacking or as an adaptive stiffness flexible shroud). In the examples disclosed herein, the flexible shroud of curved beam stacking allows for an elastic buckling response to forces applied to the shroud. For example, the importance of this elastic buckling response can be observed when rotor blades rub against the shroud assembly to prevent blade tip loss. The damper, used in conjunction with the curved beams, allows for structural rigidity as well as a degree of flexibility, thereby mitigating blade tip loss and providing an effective damping response.

[0022] Referring now to the accompanying drawings, wherein like numerals denote like elements throughout the figures, Figure 1 is a schematic cross-sectional view of a prior art turbofan-type gas turbine engine 100 (“turbofan 100”). As shown in Figure 1, the turbofan 100 defines a longitudinal or axial centerline axis 102 extending through it for reference. Generally, the turbofan 100 may include a core turbine 104 or a gas turbine engine disposed downstream of a fan section 106.

[0023] The core turbine 104 typically includes a generally tubular housing 108 (“turbine housing 108”) that defines an annular inlet 110. Housing 108 may be formed from a single housing or multiple housings. Housing 108 surrounds, in a series flow relationship, 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. A high-pressure shaft or spool 124 (“HP shaft 124”) drivesably connects the HP turbine 118 and the HP compressor 114. A low-pressure shaft or spool 126 (“LP shaft 126”) drivesably connects the LP turbine 120 and the LP compressor 112. The LP shaft 126 can also be coupled to the fan spool or shaft 128 (“fan shaft 128”) of the fan section 106. In some examples, the LP shaft 126 can be directly coupled to the fan shaft 128 (i.e., a direct drive configuration). In alternative configurations, the LP shaft 126 can be coupled to the fan shaft 128 via a reduction gearbox 130 (e.g., an indirect drive or gear drive configuration).

[0024] As shown in Figure 1, fan section 106 includes a plurality of fan blades 132, which are coupled to and extend radially outward from fan shaft 128. An annular fan housing 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. Furthermore, downstream section 138 of nacelle 134 may surround an outer portion of core turbine 104 to define a bypass airflow passage 140 between them.

[0025] As shown in Figure 1, air 142 enters the 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. The stator blades 150 and rotor blades 152 of the LP compressor, coupled to one or more sequential stages of the LP shaft 126, progressively compress the second portion 148 of the air 142 flowing through the LP compressor 112 en route to the HP compressor 114. Next, the stator blades 154 and rotor blades 156 of the HP compressor, coupled to one or more sequential stages of the HP shaft 124, further compress the second portion 142 of the air 142 flowing through the HP compressor 114. This supplies compressed air 158 to the combustion section 116, where the compressed air 158 is mixed with fuel and burned to provide combustion gases 160.

[0026] Combustion gas 160 flows through HP turbine 118, where one or more sequential stages of HP turbine stator blades 162 and HP turbine rotor blades 164, coupled to HP shaft 124, extract a first portion of kinetic and / or thermal energy from the combustion gas 160. This energy extraction supports the operation of HP compressor 114. Combustion gas 160 then flows through LP turbine 120, where one or more sequential stages of LP turbine stator blades 166 and LP turbine rotor blades 168, coupled to LP shaft 126, extract a second portion of thermal and / or kinetic energy from it. This energy extraction causes LP shaft 126 to rotate, thereby supporting the operation of LP compressor 112 and / or the rotation of fan shaft 128. Combustion gas 160 then exits core turbine 104 through exhaust section 122 of core turbine 104.

[0027] Along with the turbofan 100, the core turbine 104 serves a similar purpose and is seen in similar environments in land-based gas turbines, turbojet engines, and ducted fan engines, where the ratio of the first portion 146 of air 142 to the second portion 148 of air 142 is less than that in the turbofan, and in the ducted fan engine, the fan section 106 lacks a nacelle 134. In each of the turbofan, turbojet, and ducted engines, a reduction device (e.g., a reduction gearbox 130) may be included between any shaft and spool. For example, the reduction gearbox 130 may be positioned between the LP shaft 126 and the fan shaft 128 of the fan section 106. Figure 1 also includes a cowling 170 and offset arched universal joints 172, 174, and 176. The cowling 170 is a cover that reduces drag and cools the engine. The offset arched universal joints 172, 174, and 176 may include, for example, an infrared camera to detect thermal anomalies in the lower cowling region of the engine 100.

[0028] Figure 2A A one-dimensional example of a flexible shield 200 for a stacked bending beam structure implemented according to the teachings of this disclosure is depicted. The example shield includes example concave bending beams 202A and 202B, which are oppositely connected to example convex bending beams 204A and 204B. The concave bending beams 202A and 202B and the convex bending beams 204A and 204B are stacked between beams 208A and 208B, and the spacing (e.g., gaps) between the stacked structures allows the bending beams to move radially inward when a force is applied.

[0029] When sufficient force is applied, the example convex bending beams 204A and 204B elastically buckle to a convex shape, and similarly, under the same conditions, they elastically buckle to a concave shape. The flexible shield 200 of the example bending beam stack structure also includes a set of example edge buffers 206A, 206B, and 206C. When sufficient force is applied near the outer edge of the flexible shield 200 of the bending beam stack structure, causing the stacked beams to elastically buckle, the edge buffers 206A, 206B, and 206C engage with each other to generate load-bearing stiffness. When force is applied near the center of beams 208A and / or 208B, the example center buffers 210A and 210B similarly engage, and the engaged center buffers 210A and 210B collectively provide stiffness to the flexible shield 200 of the bending beam stack structure. Using variable geometries and / or variable materials for assembly, these proven hairpin structures of convex and concave curved beams (202A, 202B and 204A, 204B) are stacked together in a mixed arrangement to form a flexible shield 200 of the curved beam stack structure.

[0030] Figure 2B Another one-dimensional example of a flexible shield 200 for a curved beam stack structure implemented according to the teachings of this disclosure is shown. Figure 2B Many of the components in the example are combined with the above. Figure 2A The described components are basically similar or identical; however, Figure 2B The example illustrates a flexible shield 200 with a curved beam stack structure, comprising left inner buffers 216A, 216B, and 216C, and right inner buffers 218A, 218B, and 218C. Furthermore, the example flexible shield 200 with a curved beam stack structure includes a set of concave-edge curved beams 212A and 212B and a set of convex-edge curved beams 214A and 214B.

[0031] like Figure 2B As shown, the example curved beam stacked structure's flexible shield 200 provides a greater advantage than... Figure 2A The examples show greater rigidity (e.g., stiffness) because the flexible shield 200 along the bending beam stack structure includes a greater number of dampers. Therefore, in some examples, the flexible shield of the bending beam stack structure may include fewer or more dampers, and various configurations of convex and concave bending beams to accommodate location-based or function-based load and / or damping requirements. The adaptive stiffness of the shield is inherently achieved through multi-ligament deformation and / or elastic buckling of the bending beams, and the shield allows for variable stiffness relative to task and event conditions.

[0032] Figure 3A graph of example force-deflection curve 300 is shown, illustrating the force and deflection of, for example, a flexible shielding structure of a bending beam stack. Force-deflection curve 300 depicts a first type of stiffness 305, a second type of stiffness 310, and a third type of stiffness 315 associated with the flexible shielding assembly of the bending beam stack structure, demonstrating the deflection behavior of the associated example flexible shielding assembly of the bending beam stack structure.

[0033] Example first-class stiffness 305 represents a flexible shield assembly of a high-stiffness bending beam stack structure of any class. In first-class stiffness 305, as the amount of curved force 302 applied to the shield assembly increases, the observed deflection 304 of the shield assembly increases almost linearly with the response. In the examples disclosed herein, the observed deflection 304 of the shield assembly represents the degree of displacement of the structure when a force is applied to it. Furthermore, in the examples disclosed herein, including those with greater stiffness than... Figure 2A and 2B The shield assembly of the 200 fewer buffers will belong to the first category of stiffness 305.

[0034] Example Class 2 stiffness 310 represents a flexible shroud assembly for a moderately stiff bending beam stack structure of any class. In Class 2 stiffness 310, elastic buckling 308 (e.g., Euler buckling) behavior is observed in the force versus deflection curve 300. Elastic buckling behavior is desirable for a flexible shroud of a bending beam stack structure because it allows for a dynamic response to the force 302 of the curve (e.g., temporary physical deformation) while still retaining the ability to return to the original structure or arrangement of the beams within the shroud. In the examples disclosed herein, Figure 2A and 2B The shield 200 belongs to the second type of stiffness 310. As shown in this paper, the various components of the shield allow for variable stiffness relative to task and event conditions.

[0035] Example Class 3 stiffness 315 represents a flexible shield assembly of a low-stiffness bending beam stack structure of any class. Similar to the behavior observed in Example Class 1 stiffness 305, in Example Class 3 stiffness 315, as the amount of curvilinear force 302 applied to the shield assembly increases, the observed deflection 304 of the shield assembly also appears to increase at the same rate. In the examples disclosed herein, including those with stiffness greater than... Figure 2A and 2B The shield assemblies with a greater number of 200 buffers will belong to the third category of stiffness 315.

[0036] Figure 4 It is aimed at Figure 3The illustration depicts example deflection responses 400 of flexible shields 200 for each of the first type of stiffness 305, the second type of stiffness 310, and the third type of stiffness 315 in a bending beam stack structure. In the first type of stiffness 305, a first force 402 is applied to a first shield assembly 408A with a high stiffness level. Due to the rigid nature of the first shield assembly 408A, little dynamic response to the first force 402 is shown in the illustration. In the second type of stiffness 310, a second force 404 is applied to a second shield assembly 408B with a medium stiffness level. The deflection response of the second type of stiffness 310 shows an ideal elastic buckling response to the second force 404 applied to the second shield assembly 408B. Example flexible shields 200 of this type for bending beam stack structures include sequentially contacting deflection limiters and deflection ligaments to modulate force-deflection behavior and provide an elastic buckling response.

[0037] In the third stiffness 315, a third force 406 is applied to the third shroud assembly 408C, which has a low stiffness level. The deflection response of the third stiffness 315 shows a full buckling response to the third force 406 applied to the third shroud assembly 408C. The balance between stiffness and elasticity present in the third stiffness 315 provides the shroud with a structure that allows it to withstand forces, but also produces an elastic buckling response to forces, which provides clearance between the blades to reduce the impact of the blades on the shroud. This clearance reduces blade tip loss by reducing the likelihood of the blade tip contacting the shroud. During friction with the blade, the clearance also works in conjunction with the negative stiffness of the shroud to further reduce blade tip loss.

[0038] Figure 5A and 5B A two-dimensional example of a flexible shield 200 for a curved beam stack structure implemented according to the teachings of this disclosure is depicted. Figure 5A and Figure 5B Many of the components in the example are combined with those above. Figure 2A and 2B The described components are basically similar or identical; however, Figures 5A-5B The difference between the examples is that they are two-dimensional descriptions. In the examples disclosed herein, the flexible shield of the curved beam stack structure can be achieved using a variety of high-temperature resistant materials, including but not limited to nickel alloys, superalloys, etc.

[0039] Figure 6This is an illustration of an example flexible shroud assembly 600 with a bent beam stack structure. The example shroud assembly 600 includes an anti-rotation plate 605, abrasion-resistant material 610, a gap 612, a flexible shroud 200 with a bent beam stack structure, a shroud arm 616, a retaining ring 620, and blades 630. The example anti-rotation plate 605 is mounted on the shroud arm 616 to prevent axial rotation of the flexible shroud 615 with a bent beam stack structure within the shroud assembly 600. The example retaining ring 620 further retains the flexible shroud 615 with a bent beam stack structure to prevent displacement and / or any other undesirable movement. The example blade 630 is a rotor blade. The example gap 612 and the example abrasion-resistant material 610 (e.g., foil, ring, etc.) work with the elastic buckling nature of the flexible shroud 615 with a bent beam stack structure to prevent blade damage and / or blade tip loss when the blade 630 contacts the flexible shroud 615 with a bent beam stack structure.

[0040] Figure 7 yes Figure 6 An illustration of an example shield assembly 600 in an example portion of compressor 700. An example gap 612 creates a space (e.g., clearance) between the shield assembly 600 and the blades 630 to further prevent blade damage during the expansion and contraction of parts within the portion of compressor 700. In the examples disclosed herein, the example shield assembly 600 is configured to be located within an example cavity 705 and deflects in response to force as an active control mechanism for external pressure (e.g., air pressure) and / or airflow.

[0041] Figure 8 An example shield control mechanism 805 is depicted within a compressor 800 as an active control mechanism for air pressure and / or airflow. The shield control mechanism 805 includes an example stacked shield assembly 806 and rotor blades 630. A gap 612 between the stacked shield assembly 806 and the rotor blades 630 is designed to provide clearance to prevent blade friction during aircraft takeoff; once takeoff is complete, the gap 612 closes. When the aircraft reaches cruise altitude, a pressure cavity manifold 807 within the compressor 800 is opened to allow air pressures 808A, 808B, and 808C to enter the shield control mechanism 805. As air pressures 808A, 808B, and 808C flow through the shield control mechanism 805, the shield control mechanism 805 moves radially inward to deflect the pressure forces, providing mechanical damping and / or buffering effects as an active control mechanism for the compressor 800. The air cushioning effect and / or vibration damping effect, further achieved by the passive flow of air pressures 808A, 808B and 808C through the air damping orifices in the shroud control mechanism 805, serve as a passive control mechanism for the compressor 800 when the shroud control mechanism 805 does not move radially inward.

[0042] Figure 9 Depicting from Figure 7 An example flexible shroud compressor assembly 900 with a curved beam stacked structure is included within an example portion of compressor 700. The flexible shroud 200 with a curved beam stacked structure is located atop blades 630, and the example flexible shroud compressor assembly 900 with a curved beam stacked structure includes stator blade slots (e.g., fixed stator blade slots or stator blade sectors) 905A and 905B for airflow and structure within a portion of compressor 700. In the example disclosed herein, the example flexible shroud compressor assembly 900 with a curved beam stacked structure also includes a back plate 910 coupled to the flexible shroud 200 with a curved beam stacked structure. The back plate 910 engages with housing slots 915A, 915B to retain the flexible shroud 200 with a curved beam stacked structure in a suitable position within a portion of compressor 700.

[0043] Figure 10A and 10B Visualizations of an example 360-degree circumferential hairpin damper shield assembly and an example discrete sector circumferential hairpin damper shield assembly as vibration damping mechanisms are provided, respectively.

[0044] Figure 10A Example 3 is a 360-degree shield assembly 1005. The 360-degree shield assembly 1005 depicts a type of assembly in which a single continuous piece of material (e.g., a high-temperature resistant material, including but not limited to nickel alloys, superalloys, etc.) is used to form the shield assembly 1005. In this monolithic construction, a change initiated at one location on the shield assembly 1005 produces a corresponding change at one or more other locations on the shield assembly 1005 because the shield is a single, continuous piece. For example, when an example inward force 1015A or outward force 1015B is applied at a first location 1006A of the 360-degree shield assembly 1005, an adjustment to the shape of the 360-degree shield assembly 1005 occurs not only at the desired first location 1006A, but also at one or more other locations (e.g., a second location 1007A, a third location 1008A, and a fourth location 1009A). Unexpected movement caused by the response to the inward force 1015A and / or outward force 1015B along the continuous shield assembly 1005 may produce unexpected effects, such as slight damping effect, friction, etc.

[0045] Figure 10BAn example alternative embodiment of the shield assembly is shown, wherein a plurality of discrete segments are used to form an example discrete shield assembly 1010. Each segment of the discrete shield assembly 1010 is formed of the same or different materials (e.g., high-temperature resistant materials, including but not limited to nickel alloys, superalloys, etc.). When an internal force 1015A or an external force 1015B is applied to the first segment or portion 1006B of the example discrete shield assembly 1010, no corresponding movement is caused in the other segments 1007B, 1008B, and / or 1009B because these segments are interconnected but separate and can bend or move independently of each other, which is consistent with... Figure 10A The 360-degree shield assembly 1005 differs from the others. For example, when an inward force 1015A or an outward force 1015B is applied at the first segment 1006B, other segments 1007B, 1008B, and / or 1009B may not experience any corresponding movement. Therefore, the attenuation response along the discrete shield assembly 1010 produces a greater effect than... Figure 10A The 360-degree protective shield component 1005 provides a stronger damping effect.

[0046] Some examples provide turbine shield assemblies that include means for deflecting forces. The means for deflecting forces can be, for example, through concave bending beams 202A, 202B, 208A, 208B, 212A, 212B (…). Figure 2A ) and / or convex bending beams 204A, 204B, 214A, 214B ( Figure 2B This can be achieved by means of radially inward buckling. For example, an example device for deflecting a force deflects the force by means of radially inward buckling. The example turbine shield assembly also includes means for providing stiffness in response to a force. For example, the means for providing stiffness can be, for example, buffers 206A, 206B, 206C, 210A, 210B, 216A, 216B, 216C, 218A, 218B, 218C (…). Figure 2A-2B To achieve this.

[0047] Examples disclosed herein include flexible shrouds with a bent beam stack structure. Examples disclosed herein mitigate rotor blade tip losses by employing an elastic buckling response to any force applied to the shroud. The disclosed examples can reduce the cost of continuously replacing rotor blades in gas turbine engines and / or be used as active control systems for compressors by utilizing damping effects. While certain example methods, apparatuses, and articles of manufacture have been disclosed herein, the scope of this patent is not limited thereto. Rather, this patent covers all methods, apparatuses, and articles of manufacture that fall within the scope of the claims of this patent.

[0048] Further aspects of this disclosure are provided by the subject matter of the following provisions:

[0049] Example 1 is a shield assembly for a gas turbine engine, comprising: a plurality of concave curved beams; a plurality of convex curved beams; and a plurality of buffers, wherein a first concave curved beam of the plurality of concave curved beams is reverse-connected to a first convex curved beam of the plurality of convex curved beams, and a second concave curved beam of the plurality of concave curved beams is reverse-connected to a second convex curved beam of the plurality of convex curved beams, the first concave curved beam and the second concave curved beam are configured to be stacked on top of the first convex curved beam and the second convex curved beam, respectively, a first buffer of the plurality of buffers is connected to the first concave curved beam and the second concave curved beam, and a second buffer of the plurality of buffers is connected to the first convex curved beam and the second convex curved beam.

[0050] Example 2 is a shield assembly according to any of the foregoing provisions, wherein a gap is formed between the first concave curved beam and the second concave curved beam stacked on top of the first convex curved beam and the second convex curved beam.

[0051] Example 3 is a shield assembly according to any of the preceding clauses, wherein, when a load is applied, the first concave bending beam and the second concave bending beam, the first convex bending beam and the second convex bending beam, and one or more of the first and second buffers of the plurality of buffers are arranged to move radially inward.

[0052] Example 4 is a shield assembly according to any of the foregoing provisions, wherein the first and second buffers of the plurality of buffers are further configured to engage when the load is applied to resist radially inward movement.

[0053] Example 5 is a shield assembly according to any of the foregoing clauses, wherein the adaptive stiffness of the shield is inherently achieved through multi-ligament deformation.

[0054] Example 6 is a shield assembly according to any of the foregoing clauses, further designed to have variable stiffness relative to task and event conditions.

[0055] Example 7 is a shield assembly according to any of the foregoing clauses, wherein the buffer is a sequential contact deflection limiter and the bending beam is a deflection ligament.

[0056] Example 8 is a shield assembly according to any of the foregoing clauses, wherein the buffer and the bending beam adjust force-deflection behavior.

[0057] Example 9 is a shield assembly according to any of the foregoing clauses, wherein the air damping orifice produces an air cushioning effect, and wherein the shield assembly deflects radially inward in response to airflow to suppress vibration.

[0058] Example 10 is a shield assembly according to any of the foregoing clauses, wherein hairpin structures comprising at least the plurality of convex curved beams and the plurality of concave curved beams are stacked together in a mixed arrangement using variable geometry and variable materials.

[0059] Example 11 is a gas turbine comprising: a compressor including a compressor housing and a plurality of compressor blades, the compressor housing defining a first compressor housing slot and a second compressor housing slot; a turbine including a turbine housing and a plurality of turbine blades; a shaft rotatably connecting the compressor and the turbine; and a shroud for at least one of the compressor or the turbine, the shroud comprising: a first concave curved beam of a plurality of concave curved beams, the first concave curved beam being counter-connected to a first convex curved beam of a plurality of convex curved beams; a second concave curved beam of the plurality of concave curved beams, the second concave curved beam being counter-connected to a second convex curved beam of the plurality of convex curved beams; the first concave curved beam and the second concave curved beam being configured to stack on top of the first convex curved beam and the second convex curved beam; a first buffer of a plurality of buffers, the first buffer being connected to the first concave curved beam and the second concave curved beam; and a second buffer of the plurality of buffers, the second buffer being connected to the first convex curved beam and the second convex curved beam.

[0060] Example 12 is a gas turbine according to any of the foregoing provisions, wherein a gap is formed between the first concave curved beam and the second concave curved beam, which are configured to be stacked on top of the first convex curved beam and the second convex curved beam.

[0061] Example 13 is a gas turbine according to any of the foregoing provisions, wherein, when a load is applied, one or more of the first concave curved beam and the second concave curved beam, the first convex curved beam and the second convex curved beam, and the first and second buffers of the plurality of buffers move radially inward.

[0062] Example 14 is a gas turbine according to any of the foregoing provisions, wherein the first and second buffers of the plurality of buffers are further configured to engage when a sufficient load has been applied to prevent further radially inward movement.

[0063] Example 15 is a gas turbine according to any of the foregoing clauses, wherein the adaptive stiffness of the shield is achieved through multi-ligament deformation.

[0064] Example 16 is a gas turbine according to any of the foregoing clauses, wherein the shield is arranged to have variable stiffness relative to mission and event conditions.

[0065] Example 17 is a gas turbine according to any of the foregoing provisions, wherein the buffer sequentially contacts the deflection limiter, and the bending beam is a deflection ligament.

[0066] Example 18 is a gas turbine according to any of the foregoing provisions, wherein the air damping orifice produces an air cushioning effect, and wherein the shield assembly deflects radially inward in response to airflow to suppress vibration.

[0067] Example 19 is a gas turbine according to any of the foregoing provisions, wherein a hairpin structure comprising at least the plurality of convex curved beams and the plurality of concave curved beams is stacked together in a mixed arrangement using variable geometry and variable materials.

[0068] Example 20 is a turbine shield assembly including: means for deflecting a force by radially inward buckling; and means for providing stiffness in response to said force.

[0069] The following claims are incorporated herein by reference into this specific embodiment, wherein each claim exists independently as a separate embodiment of this disclosure.

Claims

1. A shield assembly for a gas turbine engine, characterized in that, include: Multiple concave curved beams; Multiple convex curved beams; and Multiple buffers, in: The first concave curved beam of the plurality of concave curved beams is reverse-connected to the first convex curved beam of the plurality of convex curved beams. The first concave shape of the first concave curved beam is defined relative to the first buffer of the plurality of buffers connected to the first concave curved beam, and the first convex shape of the first convex curved beam is defined relative to the second buffer of the plurality of buffers connected to the first convex curved beam. The second concave curved beam of the plurality of concave curved beams is connected in opposite directions to the second convex curved beam of the plurality of convex curved beams. The second concave shape of the second concave curved beam is defined relative to the first buffer connected to the second concave curved beam, and the second convex shape of the second convex curved beam is defined relative to the second buffer connected to the second convex curved beam. The first concave curved beam and the second concave curved beam are configured to be stacked on top of the first convex curved beam and the second convex curved beam, respectively. The first buffer of the plurality of buffers is connected to the first concave curved beam and the second concave curved beam, and The second buffer of the plurality of buffers is connected to the first convex curved beam and the second convex curved beam; The second buffer among the plurality of buffers is configured to be radially aligned with the first buffer among the plurality of buffers in a stacked configuration so as to directly engage with the first buffer among the plurality of buffers when a load is applied to the shield assembly.

2. The protective cover assembly according to claim 1, characterized in that, in, A gap is formed between the first concave curved beam and the second concave curved beam, which are stacked on top of the first convex curved beam and the second convex curved beam.

3. The protective cover assembly according to claim 1, characterized in that, in, When a load is applied, the first concave bending beam and the second concave bending beam, the first convex bending beam and the second convex bending beam, and one or more of the first and second buffers of the plurality of buffers are arranged to move radially inward.

4. The protective cover assembly according to claim 3, characterized in that, in, The first and second buffers of the plurality of buffers are further configured to engage when the load is applied to resist radially inward movement.

5. The protective cover assembly according to claim 1, characterized in that, in, The adaptive stiffness of the shield assembly is inherently achieved through multi-ligament deformation.

6. The protective cover assembly according to claim 1, characterized in that, It is further designed to have variable stiffness relative to task and event conditions.

7. The protective cover assembly according to claim 1, characterized in that, in, The plurality of buffers are sequential contact deflection limiters, and the bending beam is a deflection ligament.

8. The protective cover assembly according to claim 7, characterized in that, in, The plurality of buffers and the bending beam adjust the force-deflection behavior.

9. The protective cover assembly according to claim 1, characterized in that, in, The air damping orifice produces an air cushioning effect, wherein the shield assembly deflects radially inward in response to airflow to suppress vibration.

10. The protective cover assembly according to claim 1, characterized in that, in, It further includes a hairpin structure, which at least comprises the plurality of convex curved beams and the plurality of concave curved beams stacked together in a mixed arrangement using variable geometry and variable materials.

11. A gas turbine, characterized in that, include: A compressor, the compressor including a compressor housing and a plurality of compressor blades, the compressor housing defining a first compressor housing slot and a second compressor housing slot; The turbine includes a turbine housing and multiple turbine blades; A shaft rotatably connects the compressor and the turbine; and A protective cover, used for at least one of the compressor or the turbine, the protective cover comprising: A first concave curved beam among a plurality of concave curved beams, the first concave curved beam being reverse-connected to a first convex curved beam among a plurality of convex curved beams, the first concave shape of the first concave curved beam being defined relative to a first buffer among a plurality of buffers connected to the first concave curved beam, and the first convex shape of the first convex curved beam being defined relative to a second buffer among a plurality of buffers connected to the first convex curved beam. The second concave curved beam of the plurality of concave curved beams is reverse-connected to the second convex curved beam of the plurality of convex curved beams. The second concave shape of the second concave curved beam is defined relative to the first buffer connected to the second concave curved beam, and the second convex shape of the second convex curved beam is defined relative to the second buffer connected to the second convex curved beam. The first concave curved beam and the second concave curved beam are configured to be stacked on top of the first convex curved beam and the second convex curved beam; The first buffer, one of a plurality of buffers, is coupled to the first concave curved beam and the second concave curved beam; and The second buffer of the plurality of buffers is connected to the first convex curved beam and the second convex curved beam; The second buffer among the plurality of buffers is configured to be radially aligned with the first buffer among the plurality of buffers in a stacked configuration so as to directly engage with the first buffer among the plurality of buffers when a load is applied to the shield assembly.

12. The gas turbine according to claim 11, characterized in that, in, A gap is formed between the first concave curved beam and the second concave curved beam, which are configured to be stacked on top of the first convex curved beam and the second convex curved beam.

13. The gas turbine according to claim 11, characterized in that, in, When a load is applied, the first concave bending beam and the second concave bending beam, the first convex bending beam and the second convex bending beam, and one or more of the first and second buffers of the plurality of buffers move radially inward.

14. The gas turbine according to claim 11, characterized in that, in, The first and second buffers of the plurality of buffers are further configured to engage when a sufficient load has been applied to prevent further radial inward movement.

15. The gas turbine according to claim 11, characterized in that, in, The adaptive stiffness of the shield is achieved through multi-ligament deformation.

16. The gas turbine according to claim 11, characterized in that, in, The shield is arranged to have variable stiffness relative to task and event conditions.

17. The gas turbine according to claim 16, characterized in that, in, The plurality of buffers sequentially contact the deflection limiter, and the bending beam is a deflection ligament.

18. The gas turbine according to claim 11, characterized in that, in, The air damping orifice produces an air cushioning effect, wherein the shield deflects radially inward in response to airflow to suppress vibration.

19. The gas turbine according to claim 11, characterized in that, in, It further includes a hairpin structure, which at least comprises the plurality of convex curved beams and the plurality of concave curved beams stacked together in a mixed arrangement using variable geometry and variable materials.

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