Gas turbine engine with movable inlet guide vanes and stator vanes

Abstract

A gas turbine engine having movable inlet guide vanes and stator vanes is described herein. An example gas turbine engine includes a housing defining a flow passage to a compressor. The housing includes an outer radial wall and an inner radial wall. The compressor includes alternating stages of rotor blades and stator vanes in a flow passage. The gas turbine engine also includes an inlet guide vane in the flow passage upstream of a first stage rotor vane of the compressor. An inlet guide vane extends between the outer radial wall and the inner radial wall. The inlet guide vane includes an outer radial panel coupled to the outer radial wall, an inner radial panel coupled to the inner radial wall, and an intermediate panel between the outer radial panel and the inner radial panel. The intermediate panel is rotatable relative to the outer radial panel and the inner radial panel.

Description

Technical Field

[0001] The present disclosure generally relates to aircraft engines, and more particularly to gas turbine engines having movable inlet guide vanes and stator vanes. Background Art

[0002] Aircraft engines (e.g., turbofan engines, turboprop engines, etc.) typically include a fan and a gas turbine engine (sometimes referred to as the engine core) to drive the fan to generate thrust. The gas turbine engine includes one or more compressors, a combustor, and one or more turbines in a series flow arrangement. The compressor may include one or more stages of rotor blades and stator vanes. Some gas turbine engines include inlet guide vanes (IGVs) located upstream of the first stage of rotor blades. The IGVs are angled relative to the axial direction, which causes the air to swirl into the first stage of rotor blades. Brief Description of the Drawings

[0003] A complete and enabling disclosure of the presently described technology for a person of ordinary skill in the art, including its best mode, is set forth in the specification with reference to the accompanying drawings, in which:

[0004] Figure 1 is a schematic cross-sectional view of an example turbofan engine having an example gas turbine engine, in which the examples disclosed herein may be implemented.

[0005] Figure 2 is Figure 1 an enlarged view of a section of a compressor of the example gas turbine engine of.

[0006] Figure 3 is a schematic view of an example inlet guide vane having three parts, and it can be implemented in the example gas turbine engine of Figure 1 of.

[0007] Figure 4A is Figure 3 a perspective view of the example inlet guide vane of, in which the three parts are aligned in the open position.

[0008] Figure 4B is Figure 4A a perspective view of the example inlet guide vane of, in which the middle part has been rotated to the closed position relative to the outer radial panel and the inner radial panel.

[0009] Figure 5 is a schematic view of another example inlet guide vane having two parts, and it can be implemented in the example gas turbine engine of Figure 1 of.

[0010] Fig. 6A is Figure 5Perspective view of an exemplary inlet guide vane, with the two parts aligned in the open position.

[0011] Figure 6B is Fig. 6A Perspective view of an exemplary inlet guide vane, with the inner radial part rotated to the closed position relative to the outer radial part.

[0012] Figure 7 Schematic view of an exemplary stator vane having two parts, and which can be implemented in a Figure 1 exemplary gas turbine engine.

[0013] Figure 8 is Figure 2 Schematic view of an exemplary compressor, showing a Figure 3 combination of an exemplary inlet guide vane and Figure 7 an exemplary stator vane.

[0014] The drawings are not to scale. Instead, the thickness of regions may be exaggerated in the figures. In general, the same reference numerals will be used throughout the drawings and the accompanying written description to refer to the same or like parts. DETAILED DESCRIPTION

[0015] Reference will now be made in detail to examples or embodiments of the presently described technology, one or more examples of which are shown in the drawings. Each example or embodiment is provided by way of explanation of the presently described technology and not limitation thereof. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the presently described technology without departing from the scope or spirit thereof. For example, features shown or described as part of one example or embodiment can be used with another example or embodiment to yield yet another example or embodiment. Accordingly, the presently described technology is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0016] The terms "upstream" and "downstream" refer to the relative position or direction with respect to fluid flow between an upstream position or fluid source and a downstream position or fluid end position. For example, "upstream" refers to a position that is relatively closer or in the direction toward the upstream position or fluid source, while "downstream" refers to a position that is relatively closer or in the direction toward the downstream position or the end position of the fluid. As used herein, the terms "axial" and "longitudinal" both refer to a direction parallel to the centerline axis of a gas turbine engine (e.g., a turboprop engine, a core gas turbine engine, etc.), while "radial" refers to a direction perpendicular to the axial direction, and "tangential" or "circumferential" refers to a direction mutually perpendicular to the axial direction and the radial direction. Thus, as used herein, "radially inward" refers to the relative position or direction along a radial line from the outer periphery of a gas turbine engine toward the centerline axis of the gas turbine engine, and "radially outward" refers to the relative position or direction along a radial line from the centerline axis of a gas turbine engine toward the outer periphery of the gas turbine engine.

[0017] "Comprising" and "including" (and all their forms and tenses) are used herein as open-ended terms. Thus, whenever a claim uses any form of "comprising" or "including" (e.g., includes, comprises, has, etc.) as a preamble or uses any form of "comprising" or "including" (e.g., includes, comprises, has, etc.) within any type of claim recitation, it should be understood that additional elements, terms, etc. may exist without falling outside the scope of the corresponding claim or recitation.

[0018] As used herein, when the phrase "at least" is used as a transitional term (e.g., in the preamble of a claim), it is open-ended, just as the terms "comprising" and "including" are open-ended. For example, the term "and / or" when used in the form of, for example, A, B, and / or C, means 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, or (7) A and B and C. As used herein in the context of describing a structure, component, item, object, and / or thing, the phrase "at least one of A and B" is intended to refer to embodiments that include any one of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. Similarly, as used herein in the context of describing a structure, component, item, object, and / or thing, the phrase "at least one of A or B" is intended to refer to embodiments that include any one of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. As used herein in the context of describing the performance or execution of a process, instruction, action, activity, and / or step, the phrase "at least one of A and B" is intended to refer to embodiments that include any one of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. Similarly, as used herein in the context of describing the performance or execution of a process, instruction, action, activity, and / or step, the phrase "at least one of A or B" is intended to refer to embodiments that include any one of (1) at least one A, (2) at least one B, or (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 pluralities. As used herein, the term "a" or "an" object means one or more of that object. The terms "a" (or "an"), "one or more", and "at least one" are used interchangeably herein. Additionally, although listed separately, multiple devices, elements, or acts may be implemented by, for example, the same entity or object. Further, although individual features may be included in different examples or claims, these features may possibly be combined, and inclusion in different examples or claims does not imply that the combination of features is infeasible and / or disadvantageous.

[0020] As used herein, a connection reference (e.g., attached, coupled, connected, and joined) can include an intermediate member between the elements referred to by the connection reference and / or relative movement between these elements, unless otherwise stated. Thus, a connection reference does not necessarily mean that the two elements are directly connected and / or have a fixed relationship with each other.

[0021] Unless otherwise expressly stated, descriptors used herein such as "first", "second", "third", etc. do not in any way confer or otherwise indicate any meaning of priority, physical order, arrangement in a list, and / or sequencing, but are merely used as labels and / or arbitrary names to distinguish elements for ease of understanding of the disclosed examples. In some examples, the descriptor "first" may be used to refer to an element in the detailed description, while the same element may be referred to in the claims using a different descriptor such as "second" or "third". In such cases, it should be understood that these descriptors are only used to clearly identify those elements that may otherwise share the same name.

[0022] As used herein, "about" and "approximately" modify their subject / value to identify variations that may exist in real-world applications. For example, "about" and "approximately" may modify dimensions that may be inaccurate due to manufacturing tolerances and / or other real-world imperfections, as would be understood by a person of ordinary skill in the art. For example, "about" and "approximately" may indicate that these dimensions may be within a tolerance range of + / - 10%, unless otherwise specified herein.

[0023] Turbocharged engines (e.g., turbofan engines, turboprop engines, etc.), such as those used in aircraft, include a fan and a gas turbine engine to drive the fan to generate thrust. The gas turbine engine includes one or more compressor sections. For example, some gas turbine engines include a low-pressure compressor section and a high-pressure compressor section. Each compressor section may have one or more stages of rotor blades and stator vanes arranged in an alternating sequence in the axial direction.

[0024] Some gas turbine engines include inlet guide vanes (IGVs) located immediately upstream of the first-stage rotor blades of the compressor. Some gas turbine engines include a first set of IGVs located upstream of the low-pressure compressor section and a second set of IGVs located upstream of the high-pressure compressor section. The IGVs are angled to direct air into the compressor in a swirling direction. The pre-swirl air improves engine efficiency by reducing the amount of work required to drive the shaft to rotate the first-stage rotor blades. Some gas turbine engines include movable IGVs, sometimes referred to as variable IGVs (VIGVs). Specifically, each IGV may rotate about its radial axis. The IGV may rotate between a more closed position (which increases air swirl) and a more open position (where the air flow is more axial). This ability to vary the IGV angle improves engine efficiency and / or operability at part load or speed.

[0025] However, at part load or speed of the engine (e.g., 80 - 95% of the nominal speed), when the IGV is relatively closed, the first-stage rotor blades are susceptible to non-synchronous vibration (NSV), which can have a negative impact on operability and performance. Some known systems address this issue by increasing the durability of the airfoils, but this generally results in reduced efficiency. Additionally, the first-stage rotor blades are prone to stalling. One of the factors contributing to NSV and first-stage stall is the lack of flow in the outer span of the first-stage rotor near the casing (e.g., at or near the rotor tip) due to the closing of the IGV. In other words, while the IGV is closed to help swirl the air into the first stage or rotor blades, this closed position also causes insufficient airflow at the relatively fast-rotating rotor tip and increases the incidence on the airfoils, causing them to stall.

[0026] This disclosure presents an example IGV that includes two or more parts, where one part is fixed and the other is movable. For example, an IGV including an outer radial panel and an inner radial panel is disclosed. The outer radial panel remains fixed or stationary relative to the engine's casing, while the inner radial panel is movable (e.g., rotatable) relative to the outer radial panel and thus movable relative to the engine's casing. Therefore, the inner radial panel can be controlled (e.g., opened or closed) to affect the airflow angle, just like a typical IGV, but the outer radial panel remains in a fixed position (relatively open) to maintain a higher axial airflow towards the rotor tip, which reduces NSV and improves part-speed operability. The example IGV disclosed herein allows for further throttling of the front block at part or local speeds, which improves the flow towards the outer radial region (e.g., the tip) of the first-stage rotor blades, thereby enhancing the rotor throttling capacity. Compared to known IGV designs where the entire IGV rotates, the example split IGV design increases the inlet corrected mass flow rate and the total pressure ratio.

[0027] In another example disclosed herein, the IGV includes three parts, including an outer radial panel, an inner radial panel, and an intermediate panel between the outer radial panel and the inner radial panel. In this example, the outer radial panel and the inner radial panel remain fixed or stationary, while the intermediate panel is movable (e.g., rotatable). The fixed outer radial panel provides the advantages described above. Additionally, the fixed inner radial panel helps ensure higher axial flow near the inner radial portion of the rotor blades, which is beneficial for the second and subsequent stages of the rotor blades that typically lack axial airflow during part-speed operation. Therefore, the example three-part IGV significantly reduces NSV and improves engine operability.

[0028] The present disclosure also discloses an exemplary stator vane having two or more sections, where one section is fixed and the other section is movable (e.g., rotatable). The exemplary stator vanes disclosed herein include an outer radial panel and an inner radial panel. In some examples, the inner radial panel is fixed while the outer radial panel is movable (e.g., rotatable). Thus, the outer radial panel can be opened or closed to affect the swirl to the next rotor stage, while the inner radial panel remains fixed, which helps to address hub weakness issues during part power or part speed conditions.

[0029] Now referring to the drawings, Figure 1 is a schematic cross-sectional view of an exemplary turbofan engine 100 that includes an exemplary gas turbine engine 102, which can incorporate various examples disclosed herein. The exemplary turbofan engine 100 can be implemented on an aircraft and can thus be referred to as an aircraft engine. Although the examples disclosed herein are described in connection with a gas turbine engine on a turbofan-type engine, the principles of the present disclosure are also applicable to other types or configurations of engines, such as turbojet engines, turboprop engines, engines without nacelles, such as ducted fan (UDF) engines, etc. Additionally, the exemplary principles disclosed herein can be implemented on other types of engines, such as non-aircraft engines (e.g., power generation engines).

[0030] As Figure 1 shown, the turbofan engine 100 includes a gas turbine engine 102, an outer bypass duct 104 (sometimes referred to as a nacelle or fan duct), and a fan section 106. The gas turbine engine 102 and the fan section 106 are at least partially disposed within the outer bypass duct 104. The gas turbine engine 102 is disposed downstream of the fan section 106 and drives the fan section 106 to generate forward thrust.

[0031] As Figure 1 shown, the turbofan engine 100 and / or the gas turbine engine 102 define a longitudinal or axial centerline axis 108 extending therethrough for reference. Figure 1 Also included is an annotated direction diagram with reference to the axial direction A, the radial direction R, and the circumferential direction C. Generally, as used herein, the axial direction A is the direction extending generally parallel to the centerline axis 108, the radial direction R is the direction extending orthogonally outward or inward toward the centerline axis 108 from the centerline axis 108, and the circumferential direction C is the direction extending concentrically around the centerline axis 108. Additionally, as used herein, the term "forward" refers to the direction along the centerline axis 108 in the direction of movement of the turbofan engine 100, e.g., Figure 1 the left side in Figure 1on the right side in

[0032] The gas turbine engine 102 includes a substantially tubular housing 110 (which may also be referred to as an intermediate housing) that defines an annular inlet 112. The housing 110 of the gas turbine engine 102 may be formed of a single housing or multiple housings. The housing 110 surrounds, in a series flow relationship, a compressor section having a supercharger or a low-pressure compressor 114 (“LP compressor 114”) and a high-pressure compressor 116 (“HP compressor 116”), a combustion section 118 (which may also be referred to as a combustor 118), a turbine section having a high-pressure turbine 120 (“HP turbine 120”) and a low-pressure turbine 122 (“LP turbine 122”), and an exhaust section 124.

[0033] The gas turbine engine 102 includes a high-pressure shaft 126 (“HP shaft 126”) that is drivingly coupled to the HP turbine 120 and the HP compressor 116. The gas turbine engine 102 also includes a low-pressure shaft 128 (“LP shaft 128”) that is drivingly coupled to the LP turbine 122 and the LP compressor 114. The LP shaft 128 is also coupled to a fan shaft 130.

[0034] The fan section 106 includes a plurality of fan blades 132 that are coupled to the fan shaft 130 and extend radially outward from the fan shaft 130. In some examples, the LP shaft 128 may be directly coupled to the fan shaft 130 (e.g., a direct drive configuration). In an alternative configuration, the LP shaft 128 may be coupled to the fan shaft 130 via a reduction gear 134 (i.e., an indirect drive or a gear drive configuration). Although in this example, the gas turbine engine 102 includes two compressors and two turbines, in other examples, the gas turbine engine 102 may include only one compressor and one turbine. Additionally, in other examples, the gas turbine engine 102 may include more than two compressors and turbines. In such examples, the gas turbine engine 102 may include more than two drive shafts or spools.

[0035] As Figure 1As shown, during operation of the turbofan engine 100, air 136 enters the inlet section 138 of the turbofan engine 100. The air 136 is accelerated by the fan blades 132 (and is thus sometimes considered a low-pressure compressor). A first portion 140 of the air 136 flows into the bypass air flow path 142, while a second portion 144 of the air 136 flows into the inlet 112 of the gas turbine engine 102 (and thus into the LP compressor 114). One or more successive stages of the LP compressor stator vanes 146 and the LP compressor rotor blades 148 coupled to the LP shaft 128 gradually compress the second portion 144 of the air 136 flowing through the LP compressor 114 and then direct it to the HP compressor 116. Next, one or more successive stages of the HP compressor stator vanes 150 and the HP compressor rotor blades 152 coupled to the HP shaft 126 further compress the second portion 144 of the air 136 flowing through the HP compressor 116. This provides compressed air 154 to the combustion section 118, where the compressed air 154 is mixed with fuel and burned to provide combustion gases 156. In some examples, the gas turbine engine 102 includes a set of inlet guide vanes in the flow path, immediately upstream of the LP compressor 114. The inlet guide vanes are used to help swirl the air into the first stage rotor blades of the LP compressor 114. Additionally, in some examples, the gas turbine engine 102 includes another set of inlet guide vanes in the flow path, immediately upstream of the HP compressor 116. The inlet guide vanes similarly help swirl the air into the first stage rotor blades of the HP compressor 116.

[0036] The combustion gases 156 flow through the HP turbine 120, where one or more successive stages of the HP turbine stator vanes 158 and the HP turbine rotor blades 160 coupled to the HP shaft 126 extract a first portion of the kinetic energy and / or heat energy. This energy extraction supports the operation of the HP compressor 116. Then, the combustion gases 156 flow through the LP turbine 122, where one or more successive stages of the LP turbine stator vanes 162 and the LP turbine rotor blades 164 coupled to the LP shaft 128 extract a second portion of the heat energy and / or kinetic energy therefrom. This energy extraction causes the LP shaft 128 to rotate, which supports the operation of the LP compressor 114 and / or the rotation of the fan shaft 130. Then, the combustion gases 156 exit the gas turbine engine 102 through its exhaust section 124. The combustion gases 156 are mixed with the first portion 140 of the air 136 from the bypass air flow path 142. The mixed gases are discharged from the exhaust nozzle 166 (e.g., a convergent / divergent nozzle) of the bypass air flow path 142 to generate a propulsive thrust.

[0037] Figure 2 is shown Figure 1An enlarged view of a portion of the housing 110 and the HP compressor 116 of the gas turbine engine 102. The housing 110 includes an outer radial wall 200 and an inner radial wall 202 that define a flow passage 204 for directing air to the HP compressor 116. As Figure 2 shown, the gas turbine engine 102 includes a plurality of inlet guide vanes 206 (one of which is referenced in Figure 2 ), which are in the flow passage 204, upstream of the first stage rotor blades of the HP compressor 116. The inlet guide vanes 206 are circumferentially distributed in the flow passage 204. The inlet guide vanes 206 are radially oriented (e.g., in the radial direction R shown in Figure 2 ). Specifically, each inlet guide vane 206 extends between the outer radial wall 200 and the inner radial wall 202. The inlet guide vanes 206 are used to control the mass flow rate and generate a pre-whirl of the air before the first stage rotor of the HP compressor 116. In some examples, the inlet guide vanes 206 are fixed relative to the housing 110. In other examples, the inlet guide vanes 206 may have one or more movable (e.g., rotatable) portions to change the mass air flow rate and / or the air flow direction, examples of which will be further disclosed in detail herein.

[0038] As described above, the HP compressor 116 includes a plurality of alternating stages of rotor blades and stator vanes that extend radially in the flow passage 204. For example, as Figure 2 shown, the HP compressor 116 includes rotor blades 210a of the first stage 208a, rotor blades 210b of the second stage 208b, rotor blades 210c of the third stage 208c, rotor blades 210d of the fourth stage 208d, and so on. The stages 208a-208d are spaced apart in the axial direction (A). The rotor blades 210a-210d are coupled to the HP shaft 126 and extend radially outward from the HP shaft 126. Specifically, the root end of each of the rotor blades 210a-210d is coupled to the HP shaft 126. The distal end or tip of each of the rotor blades 210a-210d is close to but does not contact the outer radial wall 200. Thus, the rotor blades 210a-210d substantially span the entire radial dimension of the flow passage 204. The rotor blades 210a-210d of each stage are circumferentially distributed around the HP shaft 126. During operation of the gas turbine engine 102, the rotor blades 210a-210d rotate with the HP shaft 126 to compress or increase the velocity of the air passing through the flow passage 204, which gradually increases the pressure of the air and then reaches the combustor 118 ( Figure 1 ). Although four example stages are shown, it will be understood that the HP compressor 116 may include any number of rotor blade stages, and each stage may include any number of rotor blades.

[0039] As Figure 2 As shown, the HP compressor 116 includes a first stage 212a of stator vanes 214a located between a first stage 208a and a second stage 208b of rotor blades 210a, 210b, a second stage 212b of stator vanes 214b located between a second stage 208b and a third stage 208c of rotor blades 210b, 210c, a third stage 212c of stator vanes 214c located between a third stage 208c and a fourth stage 208d of rotor blades 210c, 210d, a fourth stage 212d of stator vanes 214d downstream of the fourth stage 208d of rotor blades 210d, and so on. The stages 212a - 212d are spaced apart in the axial direction (A). Each of the stages 212a - 212d of stator vanes 214a - 214d redirects or skews the air flow prior to a subsequent rotor stage. The stator vanes 214a - 214d of each stage are circumferentially distributed around the housing 110. The stator vanes 214a - 214d are coupled to the outer radial wall 200 and extend radially inwardly from the outer radial wall 200. For example, as Figure 2 shown, the stator vanes 214a of the first stage 212a extend between the outer radial wall 200 of the housing 110 and an inner shroud 216 carried by or coupled to the inner radial end of the stator vanes 214a. In some examples, the stator vanes 214a - 214d are fixed relative to the housing 110. In other examples, the stator vanes 214a - 214d may have one or more movable (e.g., rotatable) parts to vary the mass air flow rate and / or the air flow direction, examples of which will be disclosed in further detail herein. Although four example stator stages are shown in the figures, it will be understood that the HP compressor 116 may include any number of stator stages, and each stage may include any number of stator vanes.

[0040] The LP compressor 114 ( Figure 1 ) similarly includes multiple alternating stages of rotor blades and stator vanes. In some examples, the gas turbine engine 102 includes another set of inlet guide vanes upstream of the first stage rotor blades of the LP compressor 114 in the flow passage 204.

[0041] Figure 3 An example inlet guide vane 300 is shown that can be implemented as Figure 2 the inlet guide vane 206. In other words, each of the inlet guide vanes 206 can be implemented as Figure 3 the inlet guide vane 300. The inlet guide vane 300 extends or spans between the outer radial wall 200 and the inner radial wall 202 of the housing 110. The inlet guide vane 300 has a leading edge 302 and a trailing edge 304.

[0042] In the illustrated embodiment, the inlet guide vane 300 includes or is divided into three parts, including an outer radial panel 306, an inner radial panel 308, and an intermediate panel 310 between the outer radial panel 306 and the inner radial panel 308. The panels 306, 308, 310 may also be referred to as parts. In this embodiment, the outer radial panel 306 and the inner radial panel 308 are fixed or stationary relative to the housing 110, while the intermediate panel 310 is rotatable relative to the outer radial panel 306 and the inner radial panel 308. For example, as Figure 3 shown, the outer radial panel 306 is coupled to the outer radial wall 200 and extends radially inward from the outer radial wall 200 (e.g., in the Figure 3 downward direction). Similarly, the inner radial panel 308 is coupled to the inner radial wall 202 and extends radially outward from the inner radial wall 202 (e.g., in the Figure 3 upward direction). In this example, the outer radial panel 306 is fixed to the outer radial wall 200, and the inner radial panel 308 is fixed to the inner radial wall 202. For example, the outer radial panel 306 and the inner radial panel 308 may be integrally formed with the outer radial wall 200 and the inner radial wall 202 and / or otherwise fixedly coupled (e.g., via welding, via threaded fasteners, etc.) to the outer radial wall 200 and the inner radial wall 202. Thus, the outer radial panel 306 and the inner radial panel 308 are non-movable. However, in this example, the intermediate panel 310 is rotatable relative to the outer radial panel 306 and the inner radial panel 308 and is thus rotatable relative to the housing 110. For example, the intermediate panel 310 may rotate about the longitudinal or centerline axis 311 of the inlet guide vane 300 that extends in the radial direction. The intermediate panel 310 may rotate between a closed position and an open position. This enables the air in the intermediate section along the flow channel 204 ( Figure 2 ) to be angled or swirled, while the air in the outer radial section and the inner radial section may maintain a higher flow rate in the axial direction.

[0043] In Figure 3In the example shown, the outer radial panel 306 has a first radial length L1, the inner radial panel 308 has a second radial length L2, and the intermediate panel 310 has a third radial length L3. The sum of the first, second, and third radial lengths L1, L2, and L3 corresponds to the radial span between the outer radial wall 200 and the inner radial wall 202 at the location of the inlet guide vane 300. In the example shown, the third radial length L3 is greater than the first radial length L1 and the second radial length L2. In some examples, the third radial length L3 is greater than the sum of the first and second radial lengths L1 and L2. Thus, the movable intermediate panel 310 constitutes the largest portion of the inlet guide vane 300. In some examples, the first radial length L1 and the second radial length L2 are the same. In other examples, the first radial length L1 and the second radial length L2 are different. In some examples, the first radial length L1 of the outer radial panel 306 and the second radial length L2 of the inner radial panel 308 are each about 5% to about 30% of the total radial span between the outer radial wall 200 and the inner radial wall 202. For example, the first radial length L1 can be about 5% of the total radial span, the second radial length L2 can be about 5% of the total radial span, and the third radial length L3 can be about 90% of the total radial span. As another example, the first radial length L1 can be about 30% of the total radial span, the second radial length L2 can be about 30% of the total radial span, and the third radial length L3 can be about 40% of the total radial span. This range ensures that there is a sufficient amount of rotatable section to still effectively swirl the air in the intermediate section of the flow channel 204( Figure 2 ), and also ensures that there is a sufficient amount of fixed section to maintain a higher flow rate in the axial direction along the inner radial section and the outer radial section of the flow channel 204. In some examples, this ratio depends on the magnitude of the aerodynamic separation at adjacent rotor blades (e.g., the size of the rotating stall cell).

[0044] To rotate the intermediate panel 310, the inlet guide vane includes two shafts that extend through the outer radial panel 306 and the inner radial panel 308. For example, as Figure 3As shown, the inlet guide vane 300 has a first shaft 312 that is coupled to a first end 314 of an intermediate panel 310. The first shaft 312 extends through an outer radial panel 306 and through an opening 316 in an outer radial wall 200. For example, the outer radial panel 306 may be hollow or have a central passage for the first shaft 312. Similarly, the inlet guide vane 300 has a second shaft 318 that is coupled to a second end 320 of the intermediate panel 310. The second shaft 318 extends through an inner radial panel 308. The inner radial panel 308 may be hollow or have a central passage for the second shaft 318. The second shaft 318 is rotatably supported by a trunnion or bearing 322 on an inner radial wall 202, which enables the second shaft 318 to rotate smoothly. Additionally or alternatively, trunnions or bearings may be provided in / on the inner radial panel 308 (e.g., on an end of the inner radial panel 308 facing the second end 320 of the intermediate panel 310). In the illustrated example, the gas turbine engine 102 includes an actuator 324 for rotating the first shaft 312, which causes rotation of the intermediate panel 310. In this example, the first shaft 312 is coupled to a synchronizing ring 326. In some examples, the synchronizing ring 326 is coupled to all the shafts of all the inlet guide vanes. The actuator 324 can be activated to move (e.g., rotate) the synchronizing ring 326, which synchronizes the movement (e.g., rotation) of all the intermediate panels of the inlet guide vanes. In other examples, the actuator 324 may be connected to the first shaft 312 in other configurations (e.g., via a direct connection, via a gear train). In some examples, the actuator 324 is a hydraulic actuator or a pneumatic actuator. In other examples, the actuator 324 may be other types of actuators (e.g., an electric actuator, a solenoid, a motor).

[0045] Figure 4A is a perspective view of the inlet guide vane 300, where the intermediate panel 310 is aligned with the outer radial panel 306 and the inner radial panel 308. For example, the leading edges of all three parts are aligned. This position may be referred to as the open position. Figure 4B is a perspective view of the inlet guide vane 300, where the intermediate panel 310 has rotated relative to the outer radial panel 306 and the inner radial panel 308. Specifically, the intermediate panel 310 has rotated to the closed position. The outer radial panel 306 and the inner radial panel 308 remain fixed in the open position. In some examples, even in the open position, the outer radial panel 306 and the inner radial panel 308 are angled relative to the axial direction. For example, the outer radial panel 306 and the inner radial panel 308 may be angled about 20° relative to the axial direction. The intermediate panel 310 can rotate between the same angle (e.g., about 20°) and another angle (e.g., about 85°) corresponding to the closed position. As Figure 4A and Figure 4BAs shown, the inlet guide vane 300 has an airfoil cross-sectional shape. In other examples, the inlet guide vane 300 may have a different cross-sectional shape.

[0046] Figure 5 Another example inlet guide vane 500 is shown, which may be implemented as Figure 2 the inlet guide vane 206. In other words, each of the inlet guide vanes 206 may be implemented as Figure 5 the inlet guide vane 500. The inlet guide vane 500 extends or spans between the outer radial wall 200 and the inner radial wall 202 of the housing 110. The inlet guide vane 500 has a leading edge 502 and a trailing edge 504.

[0047] In the illustrated example, the inlet guide vane 500 includes two parts, including an outer radial panel 506 and an inner radial panel 508. The outer radial panel 506 is coupled to the outer radial wall 200 and extends radially inwardly from the outer radial wall 200 (e.g., in Figure 5 the downward direction). The inner radial panel 508 extends between the outer radial panel 506 and the inner radial wall 202. In this example, the outer radial panel 506 is fixed, while the inner radial panel 508 is rotatable relative to the outer radial panel 506 (e.g., about the longitudinal or centerline axis 511 of the inlet guide vane 500 that extends in the radial direction). This allows the air in the middle and radially inner sections of the flow passage 204 ( Figure 2 ) to be angled or redirected without affecting the angle of the air at the radially outer section.

[0048] In the illustrated example, the outer radial panel 506 has a first radial length L1, and the inner radial panel 508 has a second radial length L2. In the illustrated example, the second radial length L2 is greater than the first radial length L1. Thus, the movable inner radial panel 508 constitutes the largest part of the inlet guide vane 500. In some examples, the first radial length L1 of the outer radial panel 506 is about 5% to about 30% of the total radial span between the outer radial wall 200 and the inner radial wall 202.

[0049] Similar to the inlet guide vane 300, the inlet guide vane 500 includes a shaft 510 coupled to the first end 512 of the inner radial panel 508. The shaft 510 extends through the outer radial panel 506 and through an opening 514 in the outer radial wall 200. The shaft 510 can be rotated by an actuator 516. The second end 518 of the inner radial panel 508 is rotatably supported by a trunnion or bearing 520 on the inner radial wall 202.

[0050] Fig. 6AIs a perspective view of the inlet guide vane 500, where the inner radial panel 508 is aligned with the outer radial panel 506. For example, the leading edges of the two parts are aligned. This position can be referred to as the open position. Figure 6B Is a perspective view of the inlet guide vane 500, where the inner radial panel 508 has been rotated relative to the outer radial panel 506 to the closed position.

[0051] In some examples, similar to the inlet guide vanes 300, 500 disclosed above, one or more stator vanes can be composed of one or more fixed parts and one or more movable (e.g., rotatable) parts. For example, Figure 7 An example stator vane 700 is shown. In some examples, the stator vane 700 is implemented as the stator vane 214a of the first stage 212a. In other words, each of the stator vanes 214a can be implemented as Figure 7 the stator vane 700. The stator vane 700 has a leading edge 702 and a trailing edge 704. As Figure 7 shown, the HP compressor 116 ( Figure 2 ) includes an inner shroud 216, which is a circular or annular member. The inner shroud 216 is disposed in the flow passage 204 ( Figure 2 ) and surrounds or encircles the HP shaft 126 ( Figure 2 ), but does not physically contact the HP shaft 126. As Figure 7 shown, the stator vane 700 extends radially between the outer radial wall 200 and the inner shroud 216.

[0052] In the example shown, the stator vane 700 includes an outer radial panel 708 and an inner radial panel 710. In this example, the inner radial panel 710 is fixed or stationary relative to the outer radial wall 200 of the housing 110, while the outer radial panel 708 is rotatable relative to the inner radial panel 710 and thus rotatable relative to the outer radial wall 200 of the housing 110. This allows the outer radial panel 708 to angle or redirect the air flow while still allowing the inner radial panel 710 to remain fixed and provide structural stiffness to the inner portion of the stator vane 700, which is beneficial during partial speed conditions.

[0053] As disclosed above, the outer radial panel 708 is rotatable. For example, the outer radial panel 708 can rotate about a longitudinal or central axis extending in the radial direction. In the illustrated example, the HP compressor 116 includes an actuator 716 for rotating the outer radial panel 708 of the stator vane 700. The stator vane 700 includes a first shaft 718 that is coupled to the outer radial panel 708 and extends through an opening 720 in the outer radial wall 200. The actuator 716 can rotate the first shaft 718, which causes rotation of the outer radial panel 708. In some examples, a synchronizing ring 722 is coupled to all of the shafts of the stator vane. The actuator 716 can rotate the synchronizing ring 722 to synchronously rotate all of the outer radial panels of the stator vane. In other examples, the actuator 716 can be connected to the first shaft 718 in other configurations (e.g., via a direct connection, via a gear train). In some examples, the actuator 716 is a hydraulic actuator or a pneumatic actuator. In other examples, the actuator 716 can be another type of actuator (e.g., an electric actuator, a solenoid, a motor). In the illustrated example, the stator vane 700 includes a second shaft 724 that is coupled to the outer radial panel 708 and extends through the inner radial panel 710. Trunnions or bearings 726 can be provided on the inner shroud 216 to enable smooth rotation of the second shaft 724 (and thus the outer radial panel 708). Additionally or alternatively, trunnions or bearings can be provided on the inner radial panel 710.

[0054] In the illustrated example, the outer radial panel 708 has a first radial length L1, and the inner radial panel 710 has a second radial length L2. In the illustrated example, the first radial length L1 is greater than the second radial length L2. Thus, the movable outer radial panel 708 constitutes the largest portion of the stator vane 700. In some examples, the second radial length L2 of the inner radial panel 710 is from about 5% to about 30% of the total radial span or length of the stator vane 700.

[0055] In some examples, inlet guide vanes having fixed and rotatable portions can be implemented in combination with stator vanes having fixed and rotatable portions in the gas turbine engine 102. For example, Figure 8 An example portion of the gas turbine engine 102 is shown, which shows the inlet guide vanes 206, the first stage 208a of the rotor blades 210a, and the first stage 212a of the stator vanes 214a. In this example, the inlet guide vanes 206 are implemented as Figure 3 the inlet guide vanes 300 shown in. Thus, each of the inlet guide vanes 206 includes a fixed or stationary outer radial panel 306 and an inner radial panel 308, and a rotatable intermediate panel 310. Additionally, the stator vanes 214a are implemented as Figure 7The stator vane 700 shown in []. Thus, each of the stator vanes 214a includes a rotatable outer radial panel 708 and a fixed or stationary inner radial panel 710. The combination of the inlet guide vane 300 and the stator vane 700 improves engine operability and reduces NSV. In other examples, the inlet guide vane 206 may be implemented as Figure 5 the inlet guide vane 500 shown in [].

[0056] Although the inlet guide vanes 300, 500 are described in connection with the inlet guide vane 206 upstream of the HP compressor 116, the inlet guide vanes 300, 500 may be similarly implemented as inlet guide vanes upstream of the LP compressor 114. Additionally, the exemplary stator vane 700 may be implemented as the first stage stator vane of the LP compressor 114. Thus, any of the exemplary inlet guide vanes and / or stator vanes disclosed herein may be similarly implemented with the LP compressor 114.

[0057] From the foregoing, it can be seen that the exemplary inlet guide vane has a rotatable portion (to enable the inlet guide vane to change the swirl of the air flowing towards the rotor) and a fixed outer radial portion (which improves the rotor tip flow when the rotatable portion is closed or partially closed). Specifically, the outer radial portion is fixed in the open position such that the rotor tip of the first stage rotor blade has an improved flow field and is less likely to separate and cause NSV and partial velocity stall. This significantly improves engine operability. Exemplary stator vanes having a fixed portion and a rotatable portion are also disclosed herein. The fixed portion helps to improve the structural integrity near the hub or inner radial portion of the stator vane.

[0058] Further examples and their exemplary combinations are provided by the subject matter of the following clauses:

[0059] A gas turbine engine, comprising: a housing that defines a flow passage leading to a compressor, the housing including an outer radial wall and an inner radial wall, the compressor including rotor blades and stator vanes in alternating stages in the flow passage; and an inlet guide vane in the flow passage, upstream of the first stage rotor blade of the compressor, the inlet guide vane extending between the outer radial wall and the inner radial wall, the inlet guide vane including: an outer radial panel coupled to the outer radial wall; an inner radial panel coupled to the inner radial wall; and an intermediate panel between the outer radial panel and the inner radial panel, the intermediate panel being rotatable relative to the outer radial panel and the inner radial panel.

[0060] A gas turbine engine according to any one of the preceding clauses, wherein the outer radial panel and the inner radial panel are fixed relative to the housing.

[0061] A gas turbine engine according to any one of the preceding clauses, wherein the outer radial panel has a first radial length, the inner radial panel has a second radial length, and the intermediate panel has a third radial length.

[0062] A gas turbine engine according to any one of the preceding clauses, wherein the third radial length is greater than the first radial length and the second radial length.

[0063] A gas turbine engine according to any one of the preceding clauses, wherein the first radial length and the second radial length are the same.

[0064] A gas turbine engine according to any one of the preceding clauses, wherein the first radial length and the second radial length are different.

[0065] A gas turbine engine according to any one of the preceding clauses, wherein the inlet guide vane includes a first shaft connected to a first end of the intermediate panel, the first shaft extending through the outer radial panel and through an opening in the outer radial wall.

[0066] A gas turbine engine according to any one of the preceding clauses, further comprising an actuator that rotates the first shaft to cause rotation of the intermediate panel.

[0067] A gas turbine engine according to any one of the preceding clauses, further comprising a second shaft connected to a second end of the intermediate panel, the second shaft extending through the inner radial panel, the second shaft being rotatably supported by a trunnion or bearing on the inner radial wall.

[0068] A gas turbine engine according to any one of the preceding clauses, wherein the outer radial panel is a first outer radial panel and the inner radial panel is a first inner radial panel, wherein the compressor includes stator vanes, the stator vanes including: a second inner radial panel; and a second outer radial panel that is rotatable relative to the second inner radial panel.

[0069] A gas turbine engine according to any one of the preceding clauses, wherein the second inner radial panel is fixed relative to the housing.

[0070] A gas turbine engine according to any one of the preceding clauses, wherein the stator vanes include a first shaft connected to the second outer radial panel, the first shaft extending through an opening in the outer radial wall.

[0071] A gas turbine engine according to any one of the preceding clauses, further comprising an actuator that rotates the first shaft to cause rotation of the second outer radial panel.

[0072] A gas turbine engine according to any one of the preceding clauses, further comprising a second shaft coupled to the second outer radial panel, the second shaft extending through the second inner radial panel and rotatably coupled to the inner shroud.

[0073] A gas turbine engine according to any one of the preceding clauses, wherein the inlet guide vane has an airfoil cross-sectional shape.

[0074] A gas turbine engine comprising: a housing that defines a flow passage leading to a compressor, the housing including an outer radial wall and an inner radial wall, the compressor including rotor blades and stator vanes of alternating stages in the flow passage; an inlet guide vane in the flow passage upstream of the first-stage rotor blades of the compressor, the inlet guide vane extending between the outer radial wall and the inner radial wall; and a first-stage stator vane of the compressor, the stator vane extending radially inward from the outer radial wall, each stator vane including: an outer radial panel that is rotatable relative to the housing; and an inner radial panel that is fixed relative to the housing.

[0075] A gas turbine engine according to any one of the preceding clauses, further comprising an inner shroud, and wherein the inner radial ends of the stator vanes are coupled to the shroud.

[0076] A gas turbine engine according to any one of the preceding clauses, further comprising an actuator that rotates the outer radial panel of each stator vane.

[0077] A gas turbine engine according to any one of the preceding clauses, further comprising a synchronizing ring, the actuator moving the synchronizing ring to cause rotation of the outer radial panel of each stator vane.

[0078] A gas turbine engine according to any one of the preceding clauses, wherein at least a portion of the inlet guide vane is rotatable relative to the housing.

[0079] An inlet guide vane is provided in a flow passage of a gas turbine engine upstream of a compressor. The inlet guide vane includes: an outer radial panel; an inner radial panel; and an intermediate panel between the outer radial panel and the inner radial panel, wherein the intermediate panel is rotatable relative to the outer radial panel and the inner radial panel.

[0080] An inlet guide vane is provided in a flow passage of a gas turbine engine upstream of a compressor. The inlet guide vane includes: an outer radial panel; and an inner radial panel, wherein the inner radial panel is rotatable relative to the outer radial panel.

[0081] A stator vane is provided in a compressor of a gas turbine engine. The stator vane includes: an outer radial panel; and an inner radial panel, wherein the outer radial panel is rotatable relative to the inner radial panel.

[0082] Although certain example methods, devices, and articles have been disclosed herein, the scope of this patent is not limited thereto. Instead, this patent covers all methods, devices, and articles that fall entirely within the scope of the claims of this patent.

Claims

1. A gas turbine engine, characterized in that: include: a casing defining a flow passage to a compressor, the casing including an outer radial wall and an inner radial wall, the compressor including alternating stages of rotor blades and stator vanes in the flow passage; as well as an inlet guide vane in the flow passage upstream of a first stage rotor blade of the compressor, the inlet guide vane extending between the outer radial wall and the inner radial wall, the inlet guide vane comprising: an outer radial panel coupled to the outer radial wall; an inner radial panel coupled to the inner radial wall; and An intermediate panel is between the outer radial panel and the inner radial panel, and the intermediate panel is rotatable relative to the outer radial panel and the inner radial panel.

2. The gas turbine engine according to claim 1, characterized in that in, The outer radial panel and the inner radial panel are fixed relative to the housing.

3. The gas turbine engine according to claim 1, characterized in that in, The outer radial panel has a first radial length, the inner radial panel has a second radial length, and the intermediate panel has a third radial length.

4. The gas turbine engine according to claim 3, characterized in that in, The third radial length is greater than the first radial length and the second radial length.

5. The gas turbine engine according to claim 4, characterized in that in, The first radial length and the second radial length are the same.

6. The gas turbine engine according to claim 4, characterized in that in, The first radial length and the second radial length are different.

7. The gas turbine engine according to claim 1, characterized in that in, The inlet guide vane includes a first shaft coupled to a first end of the intermediate panel, the first shaft extending through the outer radial panel and through an opening in the outer radial wall.

8. The gas turbine engine according to claim 7, characterized in that Further included is an actuator that rotates the first shaft to cause rotation of the middle panel.

9. The gas turbine engine according to claim 8, characterized in that Further included is a second shaft coupled to a second end of the intermediate panel, the second shaft extending through the inner radial panel, the second shaft being rotatably supported by a trunnion or bearing on the inner radial wall.

10. The gas turbine engine according to claim 1, characterized in that in, The outer radial panel is a first outer radial panel and the inner radial panel is a first inner radial panel, wherein the compressor comprises a stator vane, the stator vane comprising: a second inner radial panel; and A second outer radial panel is rotatable relative to the second inner radial panel.

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