Compressor bleed groove with variable wall structure

Abstract

Compressor bleed slots with variable wall structures are disclosed herein. An example apparatus disclosed herein is coupled to a wall of a bleed slot of a compressor of a gas turbine engine, the bleed slot defining a flow path, the apparatus including a member coupled to the wall and a plate coupled to the member, the plate has a first geometry at a first time under a first ambient condition and a second geometry at a second time under a second ambient condition, the flow path having a first area when the plate has the first geometry, the flow path having a second area when the plate has the second geometry, the first area being greater than the second area, the first time is after the second time.

Description

Technical Field

[0001] This disclosure generally relates to gas turbines, and more specifically, to compressor bleed air ducts having a variable wall structure. Background Technology

[0002] Gas turbine engines typically consist of an intake section, compressor section, combustion section, turbine section, and exhaust section in series. During operation, air enters the intake section and flows to the compressor section, where one or more axial compressors progressively compress the air until it reaches the combustion section, producing combustion gases. The combustion gases flow from the combustion section through a defined hot gas path within the turbine section and then exit the turbine section via the exhaust section. Attached Figure Description

[0003] In this specification with reference to the accompanying drawings, a complete and implementable disclosure, including its best mode, is set forth for those skilled in the art, in which:

[0004] Figure 1 This is a cross-sectional view of an example gas turbine engine that can implement the examples disclosed herein.

[0005] Figure 2 yes Figure 1 A partial cross-sectional view of an example compressor for a gas turbine engine.

[0006] Figure 3 yes Figure 1 A cross-sectional view of the bleed air channel of the compressor, including a first variable wall structure implemented in accordance with the teachings of this disclosure.

[0007] Figure 4A yes Figure 3 The air intake channel and the first variable wall structure are shown in a schematic diagram of the example first geometry.

[0008] Figure 4B yes Figure 3 The air intake channel and the first variable wall structure are shown in a schematic diagram of the example second geometry.

[0009] Figure 5 yes Figure 2 A cross-sectional side view of the compressor, including an example second variable wall structure implemented in accordance with the teachings of this disclosure.

[0010] Figure 6 yes Figure 5 A three-dimensional cross-sectional view of the second variable wall structure.

[0011] Figure 7 yes Figure 5 The front view of the second variable wall structure.

[0012] Figure 8 yes Figure 5 A three-dimensional view of the second variable wall structure.

[0013] Figure 9 yes Figure 2 A schematic diagram of the air intake channel, including an example third variable wall structure implemented in accordance with the teachings of this disclosure.

[0014] Figure 10 yes Figure 2 A schematic diagram of the air intake channel, including an example fourth variable wall structure implemented in accordance with the teachings of this disclosure.

[0015] Figure 11A yes Figure 2 A schematic diagram of the air intake channel and an example fifth variable wall structure implemented in accordance with the teachings of this disclosure, located in the example first position.

[0016] Figure 11B yes Figure 2 air intake channel and Figure 11A The fifth variable wall structure is shown in the second example position.

[0017] Figure 12 yes Figure 11A and 11B A three-dimensional view of the air intake groove and the fifth variable air intake structure.

[0018] Figure 13 yes Figure 2 A schematic diagram of the air intake channel and an example of a sixth variable wall structure implemented in accordance with the teachings of this disclosure.

[0019] Figure 14 yes Figure 2 A schematic diagram of the air intake channel and an example of a seventh variable wall structure implemented in accordance with the teachings of this disclosure.

[0020] Typically, the same reference numerals are used in the accompanying drawings and descriptions to denote the same or similar parts. The drawings are not necessarily drawn to scale. Detailed Implementation

[0021] Some gas turbine engines include a bleed air system that directs air from the cold section of the gas turbine engine (e.g., high-pressure compressor, low-pressure compressor, etc.) to another location, such as a bypass flow path, nacelle, or hot section of the gas turbine engine. Drawing air from the compressor's main flow path into the bleed air sump can result in excessive pressure loss due to turbulence at the bleed air sump inlet, especially during low-power conditions. Examples disclosed herein mitigate pressure loss in the bleed air sump and include variable wall structures that can move between multiple locations during gas turbine engine operation. The variable wall structures disclosed herein are passively controlled by the compressor's ambient conditions. Some of the variable wall structures disclosed herein include shape memory alloys and / or bimetallic structures that can move between different geometries depending on the compressor's ambient temperature. Some of the variable wall structures disclosed herein include biasing members that can move between different geometries depending on the compressor's ambient pressure. The variable wall structures disclosed herein reduce vortex formation in the compressor bleed air sump and reduce pressure loss in the compressor bleed air system (e.g., increase pressure recovery, etc.).

[0022] "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, having, etc.) in the 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, the phrase "at least" is open-ended when used as a transitional term (e.g., in the preamble of a claim), just as the terms "comprising" and "including" are open-ended. The term "and / or," when used in the form of, for example, A, B, and / or C, 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, or (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 (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 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 (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 processes, instructions, actions, activities, etc., 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, 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 processes, instructions, actions, activities, etc., 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, or (3) at least one A and at least one B.

[0023] As used herein, singular references (e.g., “a,” “an,” “first,” “second,” etc.) do not exclude plurals. As used herein, the term “a” or “an” refers to one or more of those objects. The terms “a” (or “an”), “one or more,” and “at least one” are used interchangeably herein. Furthermore, although listed separately, multiple means, elements, or actions may be implemented by, for example, the same entity or object. 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 imply that the combination of features is not feasible and / or disadvantageous.

[0024] As used in this document, a statement that any component (e.g., layer, membrane, region, area, or plate) is located on another component in any manner (e.g., positioned, located, disposed on, or formed on, etc.) indicates that the referenced component is in contact with the other component, or that the referenced component is located above the other component, and one or more intermediate components are located between them.

[0025] As used herein, a connection reference (e.g., attachment, coupling, connection, and engagement) may include intermediate components between the elements referenced by the connection reference and / or relative movement between these elements, unless otherwise stated. Therefore, a connection reference does not necessarily mean that two elements are directly connected and / or fixed to each other. As used herein, the statement that any component is in “contact” with another component is defined to mean that there is no intermediate component between the two components.

[0026] Unless otherwise expressly stated, descriptors such as “first,” “second,” “third,” etc., used herein do not in any way imply or otherwise indicate any priority, physical order, arrangement in a list, and / or sorting, but are merely used as labels and / or arbitrary names to distinguish elements in order to facilitate 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 by different descriptors such as “second” or “third.” In such cases, it should be understood that these descriptors are only used to clearly identify these elements in the discussion context (e.g., in the claims), where elements may, for example, share the same name.

[0027] As used herein, “approximately” and “about” modify their subjects / values ​​to identify variations that may exist in practical applications. For example, “approximately” and “about” may modify dimensions that may be inaccurate due to manufacturing tolerances and / or other practical defects, as would be understood by one of ordinary skill in the art. For example, “approximately” and “about” may indicate that such dimensions may be within a tolerance of + / - 10%, unless otherwise specified herein.

[0028] The terms “upstream” and “downstream” refer to the relative directions of fluid flow within a fluid path. For example, “upstream” refers to the direction in which the fluid flows in, and “downstream” refers to the direction in which the fluid flows out. Various terms are used herein to describe the orientation of features. Generally, figures are annotated with reference to the axial, radial, and circumferential directions of the gas turbine associated with the features, forces, and moments. As used herein, describing two features and / or axes as parallel means that the features are approximately parallel.

[0029] Gas turbine engines include a bleed air system that draws bleed air from the cold section of the gas turbine engine and directs it to another location. Bleed air can be used to cool engine components (e.g., hot section components, etc.), de-ic the aircraft components, remove excess air from the compressor, and / or for other applications. The pressure of the bleed air is directly related to its usefulness. That is, higher bleed air pressure allows for the extraction of additional work from the bleed air. The curvature of the compressor slots and associated turbulence effects (e.g., recirculation and vortex formation) can cause significant pressure losses in the bleed air (e.g., lower pressure recovery, etc.). In some examples, under specific engine conditions (e.g., low-power engine conditions), recirculation in the bleed air slots may be greater. The pressure losses associated with the bleed air slots reduce the efficiency of the drawn bleed air and may reduce engine efficiency.

[0030] The examples disclosed herein mitigate pressure losses associated with compressor bleed air ducts and include variable wall structures disposed within the bleed air ducts of a gas turbine engine compressor. The variable wall structures disclosed herein are movable during gas turbine engine operation and can vary the flow area of ​​the bleed air duct under different operating conditions of the gas turbine engine. Some of the example variable wall structures disclosed herein are passively controlled based on the environmental conditions of the bleed air chamber (e.g., ambient temperature and / or ambient pressure). As used herein, “environmental conditions” for the bleed air chamber refer to conditions (e.g., temperature distribution, pressure distribution, etc.) associated with the corresponding operating conditions of the gas turbine engine (e.g., the bleed air chamber has a first environmental condition during takeoff, a second environmental condition during cruise, etc.). As used herein, the phrases “environmental conditions,” “surrounding conditions,” and “chamber conditions” are used interchangeably. Some of the example variable wall structures disclosed herein include smart shape memory alloy (SMA) walls and / or bimetallic walls that take on different shapes depending on the ambient temperature of the bleed air duct. Some of the example variable wall structures disclosed herein include springs for controlling the position of the walls according to the ambient pressure of the bleed air duct. Some examples of variable wall structures disclosed in this article include perforations to allow air to flow through the wall and reduce negative acoustic effects.

[0031] Referring now to the accompanying drawings, the same numbers throughout the figure represent the same elements. Figure 1 This is a schematic cross-sectional view of the gas turbine engine 110. Figure 1 In the example shown, the gas turbine engine 110 is a high-bypass turbofan engine. Although the illustrated example is a high-bypass turbofan engine, the principles of this disclosure are also applicable to other types of engines, such as low-bypass turbofan engines, turbojet engines, turboprop engines, etc. Figure 1 As shown, the gas turbine engine 110 defines a longitudinal or axial centerline axis 112 extending through it for reference. Figure 1It also includes annotated orientation diagrams for the reference axial axis A, radial axis R, and circumferential axis C.

[0032] Typically, the gas turbine engine 110 includes a core turbine 114 located downstream of a fan section 116. The core turbine 114 includes a generally tubular outer casing 118 defining an annular inlet 120. The outer casing 118 may be formed from a single casing or multiple casings. The outer casing 118 surrounds, in series flow relationship, a compressor section having a turbocharger or low-pressure compressor 122 (“LP compressor 122”) and a high-pressure compressor 124 (“HP compressor 124”), a combustion section 126, a turbine section having a high-pressure turbine 128 (“HP turbine 128”) and a low-pressure turbine 130 (“LP turbine 130”), and an exhaust section 132. A high-pressure shaft or spool 134 (“HP shaft 134”) drivesably connects the HP turbine 128 and the HP compressor 124. A low-pressure shaft or spool 136 (“LP shaft 136”) drivesably connects the LP turbine 130 and the LP compressor 122. The LP shaft 136 can also be connected to the fan spool or shaft 138 of the fan section 116. In some examples, the LP shaft 136 is directly connected to the fan shaft 138 (e.g., direct drive configuration). In alternative configurations, the LP shaft 136 can be connected to the fan shaft 138 via a reduction gear 139 (e.g., indirect drive or gear drive configuration).

[0033] like Figure 1 As shown, fan section 116 includes a plurality of fan blades 140 coupled to and extending radially outward from fan shaft 138. An annular fan housing or nacelle 142 circumferentially surrounds at least a portion of fan section 116 and / or core turbine 114. Nacelle 142 may be partially supported relative to core turbine 114 by a plurality of circumferentially spaced outlet guide vanes 144. Furthermore, a downstream section of nacelle 142 may surround an external portion of core turbine 114 to define a bypass airflow passage 148 therebetween.

[0034] like Figure 1As shown, air 150 enters the inlet section 152 of the gas turbine engine 110 during operation. A first portion 154 of the air 150 flows into a bypass airflow passage 148, while a second portion 156 of the air 150 flows into the inlet 120 of the LP compressor 122. One or more successive stages of the LP compressor stator blades 170 and rotor blades 172, coupled to the LP shaft 136, progressively compress the second portion 156 of the air 150 flowing through the LP compressor 122 and toward the HP compressor 124. Next, one or more successive stages of the HP compressor stator blades 174 and rotor blades 176, coupled to the HP shaft 134, further compress the second portion 156 of the air 150 flowing through the HP compressor 124. This provides compressed air 158 to the combustion section 126, where the compressed air 158 is mixed with fuel and burned to provide combustion gases 160.

[0035] Combustion gas 160 flows through HP turbine 128, where one or more successive stages of HP turbine stator blades 166 and HP turbine rotor blades 168, coupled to HP shaft 134, extract a first portion of kinetic and / or thermal energy. This energy extraction supports the operation of HP compressor 124. Combustion gas 160 then flows through LP turbine 130, where one or more successive stages of LP turbine stator blades 162 and LP turbine rotor blades 164, coupled to LP shaft 136, extract a second portion of thermal and / or kinetic energy. This energy extraction causes LP shaft 136 to rotate, thereby supporting the operation of LP compressor 122 and / or the rotation of fan shaft 138. Combustion gas 160 then exits core turbine 114 through exhaust section 132. Turbine frame 161 with a cowling assembly is located between HP turbine 128 and LP turbine 130. The turbine frame 161 serves as a support structure, connecting the rear bearing of the high-pressure shaft to the turbine housing and forming an aerodynamic transition duct between the HP turbine 128 and the LP turbine 130. The cowling forms a flow path between the high-pressure and low-pressure turbines and can be formed using metal castings (e.g., nickel-based cast metal alloys).

[0036] The core turbine 114 is used for a similar purpose in conjunction with the gas turbine engine 110 and is exposed to similar environments as in land-based gas turbines, turbojet engines (where the ratio of the first portion 154 of air 150 to the second portion 156 of air 150 is less than the ratio of the turbofan), and ductless fan engines (where the fan section 116 lacks a nacelle 142). In turbofans, turbojet, and ductless engines, a reduction gear (e.g., reduction gear 139) can be included between any shaft and spool. For example, reduction gear 139 is disposed between the LP shaft 136 and the fan shaft 138 of the fan section 116.

[0037] As mentioned above Figure 1 The turbine frame 161 is located between the HP turbine 128 and the LP turbine 130 to connect the rear bearing of the high-pressure shaft to the turbine housing and to form an aerodynamic transition duct between the HP turbine 128 and the LP turbine 130. Air flows through the turbine frame 161 between the HP turbine 128 and the LP turbine 130.

[0038] Figure 2 yes Figure 1 A partial cross-sectional view of the example compressor housing 200 of the HP compressor 124 of the gas turbine engine 110. Figure 2 In the example shown, the HP compressor 124 includes a first bleed air duct 202 and a second bleed air duct 204. The compressor housing 200 defines a main flow path 206 that extends through the HP compressor 124 into the downstream turbomechanical components of the gas turbine engine 110. Figure 2 In the example shown, the first air intake flow path 208 extends from the main flow path 206 into the first air intake slot 202. Combined with... Figure 5-8 The compressor housing 200 and the first bleed slot 202 are described in more detail.

[0039] During operation of the gas turbine engine 110, air flows along the main flow path 206 and is compressed and directed by the HP compressor rotor blades 176. A portion of the air exits the main flow path 206 and enters the first bleed air chute 202 along a first bleed air flow path 208 (e.g., a first-stage flow path, etc.). The air in the first bleed air chute 202 can be discharged and / or used at another location in the aviation system associated with the HP compressor 124 (e.g., de-icing, cooling hot-section components of the gas turbine engine, pressurizing the aircraft associated with the gas turbine engine 110, etc.). Another portion of the air exits the main flow path 206 along an example second bleed air flow path 210 (e.g., a second-stage flow path, etc.). The use of multiple bleed air chute allows compressed air to be drawn from the HP compressor 124 at different temperatures and / or pressures (e.g., the pressure and temperature of the air drawn from the first bleed air chute 202 are lower than the air drawn through the second bleed air chute 204, etc.). While the example bleed air chute and variable wall structure are for reference only. Figure 1 The first bleed slot 202 of the HP compressor 124 is described herein, but the variable wall structure disclosed herein can be used in conjunction with bleed slots (e.g., second bleed slot 204, etc.) located in other locations in the HP compressor 124 and / or other components of the gas turbine engine (e.g., LP compressor 122, etc.).

[0040] Figure 3 yes Figure 1A cross-sectional view of the first bleed slot 202 of the HP compressor 124, including an exemplary first variable wall structure 300 implemented in accordance with the teachings of this disclosure. Figure 3 In the example shown, the first variable wall structure 300 includes a plate 302 and a member 304. Although Figure 3 The variable wall structure 300 is disposed in the first bleed air slot 202, but the variable wall structure described herein can be disposed in other bleed air slots of the gas turbine engine, including Figure 2 The second air intake slot 204.

[0041] Plate 302 is a variable geometry structure disposed within the air venting cavity 307 of the first air venting groove 202. As used herein, a "variable geometry structure" is a structure designed to be configured (e.g., movable, etc.) between multiple configurations, positions, and / or orientations during standard operation of the structure. Figure 3 In the illustrated example, plate 302 includes a first end 308 connected to member 304 and a second end 309 cantilevered within air duct 307 (e.g., separate from the side of the first air duct 202, suspended in the air duct 307, etc.). During operation of the first variable wall structure 300, the second end 309 moves relative to the first end 308, causing plate 302 to bend and adopt different geometries. The variable geometry of plate 302 causes a change in the flow area through the first air duct 202. For example, plate 302 may bend to block a portion (e.g., a portion of the first air duct 202, the entire first air duct 202, etc.) to reduce the amount of air flowing through the cavity. In some examples, the reduced air volume and / or the modified geometry of the first air duct 202 can reduce eddy formation and / or other flow effects, thereby reducing the pressure recovery of the first air duct 202. The following is in conjunction with... Figure 4A and 4B describe Figure 3 An example of the variable geometry of the first variable wall structure 300. As used herein, the terms “plate” and “wall” are used interchangeably to refer to the variable geometry structure of the variable wall structure disclosed herein.

[0042] In some examples, plate 302 is composed of a smart metal alloy (SMA). For example, plate 302 can be composed of any suitable SMA (e.g., copper-aluminum-nickel alloy, nickel-titanium alloy, iron-magnesium-tin alloy, copper-zinc-aluminum alloy, copper-aluminum-nickel alloy, etc.). In such examples, when plate 302 is heated (e.g., under hot engine conditions such as takeoff), the SMA takes on different pre-constructed shapes. Additionally or alternatively, plate 302 can be composed of multiple layers of materials. For example, plate 302 can be composed of two layers of different metals (e.g., a bimetallic structure, etc.) that are rigidly connected and have different coefficients of thermal expansion. For example, plate 302 may include a first layer composed of aluminum, titanium, steel, nickel alloy, and / or another metal and a second layer composed of a different metal (e.g., different titanium, different nickel alloy, different steel, etc.). When plate 302 is heated, the materials of plate 302 expand at different rates, which causes plate 302 to bend. In some such examples, the size and material of plate 302 can be selected to modify the bending profile of plate 302.

[0043] exist Figure 3 In the example shown, plate 302 includes a plurality of openings 310 (e.g., perforations, gaps, holes, etc.). Figure 3 In the example shown, opening 310 has a uniform pattern. In some examples, opening 310 is arranged in a grid pattern. In other examples, opening 310 may have any other suitable uniform arrangement. In other examples, opening 310 may be arranged in a non-uniform arrangement (e.g., random arrangement, etc.). Opening 310 allows air to pass through plate 302 during operation of gas turbine engine 110. In some examples, opening 310 suppresses (e.g., reduces, etc.) the acoustic effects associated with airflow through plate 302. Figure 3 In the example shown, opening 310 is a circular hole. In other examples, opening 310 can have any other shape (e.g., polygonal, slotted, oval, irregular, etc.). In other examples, opening 310 is not present (e.g., plate 302 is solid, etc.).

[0044] Component 304 connects plate 302 within the first air intake vent 202. Component 304 is a rigid structure that supports (e.g., suspends, etc.) plate 302 within air intake cavity 307. In some examples, component 304 includes at least one of a strut (e.g., one strut, multiple struts, etc.), a lattice (e.g., a honeycomb lattice, a triangular lattice, a cubic lattice, a tetragonal lattice, a higher-dimensional Bravais lattice, etc.), and / or a corrugated sheet (e.g., a curved sheet, etc.). In other examples, component 304 may be implemented by any other suitable rigid permeable structure (e.g., a rigid mesh, etc.). Figure 3In the example shown, member 304 extends radially and longitudinally. In other examples, member 304 may be positioned circumferentially (e.g., entering and exiting the sheet).

[0045] Figure 4A yes Figure 3 A schematic diagram of the first air intake groove 202 and the first variable wall structure 300 in the first geometry 400. Figure 4A In the example shown, the first bleed air duct 202 has a first environmental condition 402. In some examples, the first environmental condition 402 is a high-power engine condition (e.g., high-temperature condition, high-pressure condition, high-speed condition, etc.). As used herein, the phrases "high-power engine condition" and "low-power engine condition" are used to describe the operating state of the gas turbine engine 110. As used herein, the phrase "high-power engine condition" refers to a relatively high throttle condition of the gas turbine engine 110. For example, the first environmental condition 402 may be associated with a high-power flight phase of the gas turbine engine 110 (e.g., takeoff, climb, etc.) and / or a relatively high throttle position of the gas turbine engine 110 (e.g., maneuvering engine condition, full-power engine condition, 90% power engine condition, etc.). As used herein, the phrase "low-power engine condition" refers to a relatively low throttle condition of the gas turbine engine 110 (e.g., compared to a high-power engine condition, etc.). For example, a second environmental condition 408 may be associated with a low-power condition of the gas turbine engine 110 (e.g., cruise, ground idling, etc.).

[0046] exist Figure 4A In the example shown, the plate 302 of the first variable wall structure 300 has a first curvature 404. That is, in the first geometry 400, the plate 302 has a first curvature 404. In some examples, a first environmental condition 402 causes the plate 302 to exhibit the first curvature 404. Figure 4A In the example shown, plate 302 is approximately planar due to its first curvature 404. Figure 4A In the example shown, the first end 308 and the second end 309 are approximately coplanar (e.g., ends 308 and 309 occupy the same geometric plane, plate 302 is planar, etc.). In other examples, the first curvature 404 may be non-planar. For example, the first curvature 404 may be complementary to the curvature of the air duct 307 (e.g., the first curvature 404 of plate 302 is parallel to the internal curvature of the first air duct 202, etc.). In some such examples, plate 302 is equidistant from the upstream wall 412A (e.g., upstream edge, etc.) and downstream wall 412B (e.g., upstream edge, etc.) of the air duct 307. Figure 4A In the example shown, the first curvature 404 does not significantly inhibit the flow of air through the first bleed air flow path 208.

[0047] Figure 4B yes Figure 3 A schematic diagram of the first air intake groove 202 and the first variable wall structure 300 in the second geometry 406. Figure 4B In the example shown, the first bleed air duct 202 has a second ambient condition 408. In some examples, the second ambient condition 408 is a low-power engine condition (e.g., a relatively low temperature condition, a relatively low pressure condition, etc.). That is, the temperature and pressure associated with the second ambient condition 408 are lower than the temperature and pressure associated with the first ambient condition 402. In other examples, the second ambient condition 408 can be any other suitable engine condition. It should be understood that... Figure 4A The first environmental condition 402 and the second environmental condition 408 can occur during the same operation of the gas turbine engine 110. For example, the first environmental condition 402 can occur during a first time period of flight (e.g., takeoff), while the second environmental condition 408 can occur during a second time period later in the same flight (e.g., cruise, ground idling, etc.). It should also be understood that environmental conditions 402 and 408 can occur multiple times within the gas turbine engine 110 during a single flight operation.

[0048] exist Figure 4B In the example shown, the plate 302 of the first variable wall structure 300 has a second curvature 410. That is, in the second geometry 406, the plate 302 has a second curvature 410. Figure 4B In the example shown, plate 302 is non-planar due to the second curvature 410 (e.g., the second curvature 410 is a non-planar curvature, the first curvature 404 is a convex curvature, the second curvature 410 is a concave curvature, etc.). For example, the relatively lower temperature of the second environmental condition 408 compared to the first environmental condition 402 causes the SMA of plate 302 to exhibit the second curvature 410. Figure 4B In the example shown, in the second geometry 406, the second end 309 is deflected (e.g., displaced) towards the upstream wall 412A of the first air intake 202. Figure 4B In the example shown, the deflection of plate 302 creates an unblocked region 414A and a blocked region 414B, which, in contrast to... Figure 4A Compared to the approximate planar position of plate 302 (e.g., with Figure 4A Compared to the first geometry 400, this reduces the flow area of ​​the first air intake flow path 208.

[0049] exist Figure 4B In the example shown, the second geometry 406 and the second curvature 410 cause the second end 309 to deflect upstream relative to the main flow path of the HP compressor 146. Therefore, in Figure 4BIn the example shown, the unblocked region 414A is downstream of the blocked region 414B relative to the main flow path 206 (e.g., the unblocked region 414A is upstream of the blocked region 414B, etc.). In other examples, regions 414A and 414B may have other shapes, spatial relationships, and / or dimensions. For example, the unblocked region 414A may be upstream of the blocked region 414B. In other examples, regions 414A and 414B may be circumferentially arranged within the first air intake trough 202.

[0050] The obstruction region 414B inhibits (e.g., blocks, slows, reduces, etc.) airflow through the first air intake sump 202. For example, if the plate 302 includes an opening 310, the plate 302 reduces the airflow velocity through the obstruction region 414B. In other examples, if there is no opening 310, the plate 302 prevents airflow through the obstruction region 414B. In some examples, the plate 302 reduces recirculation (e.g., backflow, eddies, vortices, etc.) and / or other turbulence effects in the obstruction region 414B that are related to airflow from... Figure 2 The main flow path 206 turns Figure 2 This relates to the first bleed air flow path 208. In some examples, the reduction of recirculation and other turbulence effects increases the pressure recovery of the first bleed air slot 202. Therefore, Figure 3-4B The first variable wall structure 300 increases the pressure of the bleed air extracted from the first bleed slot 202 and the usability of the extracted bleed air. That is, the first variable wall structure 300 reduces the pressure drop in the first bleed slot 202, thereby maintaining the pressure and energy of the extracted bleed air.

[0051] Figure 5 yes Figure 2 A cross-sectional side view of the compressor housing 200, including an example second variable wall structure 500 implemented in accordance with the teachings of this disclosure. Figure 6 This is a perspective view of the second variable wall structure 500 within the first air intake groove 202 of the compressor housing 200. The second variable wall structure 500 and... Figure 3-4B The first variable wall structure 300 is similar, unless otherwise stated herein. Figure 5 and 6 In the example shown, the second variable wall structure 500 includes a first plate 502A, a second plate 502B, and a member 504. Figure 5 and 6 In the example shown, component 504 and Figure 2 The first air intake slot 202 is connected together with the deflection plate 506.

[0052] exist Figure 5 and 6In the example shown, the second variable wall structure 500 includes two plates (e.g., plates 502A, 502B, etc.). In other examples, the second variable wall structure 500 may include a different number of plates (e.g., one plate, three plates, etc.). In some examples, the second variable wall structure 500 may depend on the dimensions of the first air intake slot 202 (e.g., area, length, width, etc.), the stiffness of plates 502A, 502B, and / or the thickness of plates 502A, 502B. For example, the stiffness, dimensions, and / or thickness of plates 502A, 502B can affect the temperature sensitivity of the geometry of plates 502A, 502B (e.g., higher stiffness and / or thickness of plates 502A, 502B can reduce the temperature sensitivity of the second variable wall structure 500, etc.). In some examples, using multiple plates (e.g., plates 502A, 502B, etc.) allows plates 502A, 502B to approximate the curvature of the first air intake 202 (e.g., the circumferential curvature of the gas turbine engine 110, etc.). Figure 3 Similar to plate 302, one or both of plates 502A and 502B may be composed of shape memory alloy (SMA). Additionally or alternatively, one or both of plates 502A and 502B may consist of two or more metal layers (e.g., including bimetallic structures of materials with different coefficients, etc.). Figure 5 In the examples shown, boards 502A and 502B do not include openings (e.g., perforations, similar to...). Figure 3 (e.g., opening 310). In other examples, one or both of plates 502A and 502B may include one or more openings to facilitate airflow through them.

[0053] The deflection plate 506 is a thin-walled structure that is connected to the compressor housing 200 in the first air intake slot 202. Figure 2 In the example shown, deflector plate 506 is the bleed chamber 307 of the first bleed slot 202 (e.g., the outer surface of deflector plate 506 partially defines the first bleed flow path 208, etc.). Component 504 connects plates 502A, 502B to deflector plate 506. In other examples, deflector plate 506 is not present. In some such examples, component 504 may be connected to a solid portion of the compressor housing 200.

[0054] Figure 7 yes Figure 5 and Figure 6 The front view of the second variable wall structure 500. Figure 7 In the example shown, component 504 includes curvature 702. In Figure 7 In the example shown, a gap 704 is included between plates 502A and 502B. Figure 5-7In the example shown, component 504 is a corrugated sheet with curved corrugations. In other examples, component 504 may have straight corrugations and / or curved corrugations. Figure 7 In the example shown, component 504 comprises three and a half corrugations. In other examples, component 504 may have any other suitable number of corrugations (e.g., two corrugations, five corrugations, ten corrugations, etc.). Additionally or alternatively, component 504 may include any other suitable structure through which air can flow (e.g., lattice, struts, mesh, etc.). For example, component 504 may be two or more struts extending between deflection plate 506 and plates 502A, 502B. Figure 7 In the example shown, the curvature 702 of component 504 corresponds to the curvature 702 of gas turbine engine 110.

[0055] exist Figure 7 In the example shown, plates 502A and 502B respectively include a first side 706A and a second side 706B. Figure 7 In the example shown, sides 706A and 706B are spaced apart by gap 704. In some examples, the size of gap 704 is such that sides 706A and 706B of plates 502A and 502B are subjected to high temperature and / or high strain engine conditions (e.g., high-power engine conditions, takeoff, ...). Figure 4B During the second environmental condition 408, etc., the plates 502A and 502B are adjacent to each other (e.g., contact, engagement, etc.). In some such examples, sides 706A and 706B include a coating (e.g., a low-friction coating, etc.) to facilitate contact between sides 706A and 706B. In other examples, the size of gap 704 allows plates 502A and 502B to remain spaced apart under all engine conditions. In some examples, gap 704 is not present. In some such examples, plates 502A and 502B contact each other under some or all engine conditions (e.g., plates 502A and 502B are adjacent under all engine conditions, etc.). In some such examples, sides 706A and 706B are curved and / or include joints to facilitate the abutment of plates 502A and 502B.

[0056] Figure 8 yes Figure 5-7 A perspective view of the second variable wall structure 500. Figure 8 In the example shown, the second variable wall structure 500 has a first geometry 802 (indicated by solid lines) and a second geometry 804 (indicated by dashed lines). In some examples, the first geometry 802 corresponds to the gas turbine engine 110 being in high-power engine conditions (e.g., Figure 4A The position of the second variable wall structure 500 when the first environmental condition 402, etc., is met. In some examples, the second geometry 804 corresponds to the gas turbine engine 110 being in high-power engine conditions (e.g., Figure 4B The position of the second variable wall structure 500 under the second environmental condition 408, etc. Figure 8 In the example shown, plates 502A and 502B are configured to have the same response to the environmental conditions of the air intake. That is, when the second variable wall structure 500 has a first geometry 802, plates 502A and 502B have the same first curvature (e.g., flat, planar, unbent, etc.), and when the second variable wall structure 500 has a second geometry 804, plates 502A and 502B have the same second curvature (e.g., same curvature profile, same bend, etc.). Figure 8 In the example shown, in order to achieve the same response (e.g., the same temperature sensitivity, the same temperature response, etc.), plates 502A and 502B are made of the same material, the same size, and the same shape, and are connected to component 504 at the same relative position.

[0057] and Figure 3-4B The first variable wall structure 300 is similar. Figure 5-8 The second variable wall structure 500 increases the pressure recovery of the first bleed air channel 202 under low-power engine conditions. Specifically, the curvature of the plates 502A and 502B in the second geometry 804 suppresses the recirculation of bleed air in the first bleed air flow path 208 by forming a blocking portion 806. When the second variable wall structure 500 has the second geometry 804, the blocking portion 806 reduces the flow area of ​​the bleed air chamber 307 and suppresses (e.g., prevents, reduces, etc.) the flow of air through the first bleed air channel 202. When the gas turbine engine 110 is in high-power engine conditions, the second variable wall structure 500 has the first geometry 802, and the flow of bleed air through the first bleed air channel 202 is substantially unaffected by the plates 502A and 502B.

[0058] Figure 9 yes Figure 2 A schematic diagram of the first air intake channel 202, including an example third variable wall structure 900 implemented in accordance with the teachings of this disclosure. Figure 9 In the example shown, the third variable wall structure 900 includes a first plate 902, a second plate 904, a first member 906, and a second member 908. Members 906 and 908 are... Figure 3-4B The component 304 is similar, except that the first component 906 extends from the upstream wall 412A of the first air intake channel 202, while the second component 908 extends from the downstream wall 412B of the first air intake channel 202.

[0059] Boards 902 and 904 Figure 3 Similar to board 302, unless otherwise stated herein. Figure 9 In the example shown, the first plate 902 includes a first end 912 and a second end 914. Figure 9 In the example shown, the first end 912 of the first plate 902 is fixedly connected to the upstream wall 412A via the first member 906. Figure 9 In the example shown, the second end 914 of the first plate 902 is suspended (e.g., cantilevered within the first air intake 202). Figure 9 In the example shown, the second plate 904 includes a third terminal 916 and a fourth terminal 918. Figure 9 In the example shown, the third end 916 of the second plate 904 is fixedly connected to the downstream wall 412B via the second member 908. Figure 9 In the example shown, the fourth end 918 of the second plate 904 is suspended (e.g., cantilever, etc.) within the first air intake 202. Figure 9 In the examples shown, plates 902 and 904 do not include openings (e.g., perforations, similar to...). Figure 3 (e.g., opening 310). In other examples, one or both of plates 902 and 904 may include one or more openings to facilitate airflow through them.

[0060] exist Figure 9 In the example shown, the third variable wall structure 900 has a first geometry 920 (represented by solid lines) and a second geometry 922 (represented by dashed lines). In some examples, the first geometry 920 corresponds to the gas turbine engine 110 being in high-power engine conditions (e.g., Figure 4A The position of the third variable wall structure 900 when the first environmental condition 402, etc., is met, while the second geometry 922 corresponds to the gas turbine engine 110 being in low-power engine conditions (e.g., Figure 4B The position of the third variable wall structure 900 under the second environmental condition 408, etc.

[0061] In the second geometry 922, the second end 914 and the fourth end 918 converge to form a blocking region 924. When the third variable wall structure 900 has the second geometry 922, the adjacency of the ends 912, 914 inhibits (e.g., prevents, reduces, etc.) airflow through the blocking region 924 of the first air intake 202. In other examples, in the second geometry 922, the ends 912, 914 are not adjacent and are close (e.g., a small gap is formed between the ends 912, 914, etc.). In some such examples, the gap between the ends 912, 914 is reduced but does not completely prevent airflow through the blocking region 924. In the second geometry 922, the plates 902, 904 are substantially parallel and spaced apart from the ends 912, 914 (e.g., a large gap exists between the ends 912, 914, etc.). When the gas turbine engine 110 is in high-power engine condition, the third variable wall structure 900 has a first geometry 920, and the airflow through the first air intake groove 202 is basically unaffected by the plates 902 and 904.

[0062] Figure 10 yes Figure 2 A schematic diagram of the first air intake channel 202, including an example of a fourth variable wall structure 1000 implemented in accordance with the teachings of this disclosure. Figure 10 In the example shown, the fourth variable wall structure 1000 includes a first plate 1002, a second plate 1004, a third plate 1006, a first component 1008, and a second component 1010.

[0063] Boards 1002, 1004, 1006 and Figure 3 Similar to board 302, unless otherwise stated herein. Figure 10 In the example shown, the first plate 1002 includes a first end 1012 and a second end 1014. Figure 10 In the example shown, the first end 1012 of the first plate 1002 is suspended in the first air intake groove 202, while the second end 1014 is connected to the first member 1008. Figure 10 In the example shown, the second plate 1004 includes a third terminal 1016 and a fourth terminal 1018. Figure 10 In the example shown, the third end 1016 of the second plate 1004 is suspended in the first air intake trough 202, while the fourth end 1018 is connected to the second member 1010. Figure 10 In the example shown, the third plate 1006 includes a fifth terminal 1020 and a sixth terminal 1022. In Figure 10 In the example shown, the fifth end 1020 of the second plate 1004 is suspended in the first air intake trough 202, while the sixth end 1022 is connected to the upstream wall 412A. Figure 10In the example shown, as the ambient temperature of the second air intake trough 202 decreases, the ends 1012, 1016, and 1020 deflect upstream relative to the main flow path 206.

[0064] In other examples, the plates 1002, 1004, and 1006 of the fourth variable wall structure 1000 have different spatial relationships within the first air intake channel 202. For example, the second end 1014 of the first plate 1002 may be connected to the upstream wall 412A, while the third plate 1006 may be disposed in the middle of the air intake chamber 307 of the first air intake channel 202. In some such examples, as the ambient temperature of the first air intake channel 202 decreases, the ends 1012, 1016, and 1020 deflect upstream relative to the main flow path 206. Figure 10 In the examples shown, plates 1002, 1004, and 1006 do not include openings. In other examples, some or all of plates 1002, 1004, and 1006 may include one or more openings (e.g., perforations, similar to...). Figure 3 (The opening 310, etc.) is designed to facilitate the flow of air through it.

[0065] Components 1008, 1010 and Figure 3-4B Component 304 is similar, unless otherwise stated herein. Figure 10 In the example shown, the first component 1008 is from Figure 4A The upstream wall 412A extends from the middle, while the second member 1010 extends from... Figure 4A The downstream wall 412B extends through the first plate 1002. In some examples, a third member (not shown) extends between the second end 1014 of the first plate 1002 and the fourth end 1018 of the second plate 1004. In some examples, members 1008, 1010 may be implemented by one or more supports and / or other structural features extending through some or all of the plates 1002, 1004, 1006.

[0066] exist Figure 10 In the example shown, the fourth variable wall structure 1000 has a first geometry 1024 (represented by solid lines), a second geometry 1026 (represented by short dashed lines), and a third geometry 1028 (represented by long dashed lines). In some examples, the first geometry 1024 corresponds to the gas turbine engine 110 being in high-power engine conditions (e.g., Figure 4A The position of the fourth variable wall structure 1000 when the first environmental condition 402, etc., is specified. In some examples, the second geometry 1026 corresponds to the position when the gas turbine engine 110 is under medium power conditions (e.g., descent, etc.). In some examples, the third geometry 1028 corresponds to the position when the gas turbine engine 110 is under low power engine conditions (e.g., descent, etc.). Figure 4B The location under the second environmental condition (e.g., 408). Figure 10 In the example shown, the second geometry 1026 represents a position between the first geometry 1024 and the third geometry 1028. That is, the fourth variable wall structure 1000 moves through the second geometry 1026 to move from the first geometry 1024 to the third geometry 1028, or from the third geometry 1028 to the first geometry 1024. It should be understood that the fourth variable wall structure 1000 gradually translates between geometries 1024, 1026, and 1028, and in some examples, the fourth variable wall structure 1000 may occupy an intermediate position between geometries 1024, 1026, and 1028.

[0067] In the first geometry 1024, the first plate 1002 has a first curvature 1030, the second plate 1004 has a second curvature 1032, and the third plate 1006 has a third curvature 1034. Figure 10 In the example shown, curvatures 1030, 1032, and 1034 are complementary to the curvature of the air intake chamber 307 (e.g., some or all of the curvatures 1030, 1032, and 1034 of plates 1002, 1004, and 1006 are parallel to the curvature of the interior of the first air intake groove 202, etc.). Figure 10 In the example shown, in the third curvature 1034, the third plate 1006 is adjacent to the downstream wall 412B along the length of the third plate 1006. In other examples, curvatures 1030, 1032, and 1034 are approximately planar curvatures (e.g., plates 1002, 1004, and 1006 are flat in the first geometry 1024, plates 1002, 1004, and 1006 are approximately planar in the first geometry 1024, etc.). Additionally or alternatively, curvatures 1030, 1032, and 1034 are identical (e.g., planar, etc.). In other examples, some or all of curvatures 1030, 1032, and 1034 are different and / or non-planar. Figure 10 In the example shown, in the first geometry 1024, the curvatures 1030, 1032, and 1034 of plates 1002, 1004, and 1006 do not substantially inhibit airflow through the first airflow path 208. As used herein, the first geometry 1024 is also referred to herein as the “fully open geometry,” the “open geometry,” and the “open position” of the fourth variable wall structure 1000.

[0068] In the second geometry 1026, the first plate 1002 has a fourth curvature 1036, the second plate 1004 has a fifth curvature 1038, and the third plate 1006 has a sixth curvature 1040. Figure 10 In the example shown, in the fourth curvature 1036, the first end 1012 of the first plate 1002 deflects towards the upstream wall 412A of the first air intake trough 202. Figure 10 In the example shown, in the fifth curvature 1038, the third end 1016 of the second plate 1004 deflects towards the upstream wall 412A of the first air intake trough 202 and the first plate 1002. Figure 10 In the example shown, in the sixth curvature 1040, the fifth end 1020 of the third plate 1006 deflects towards the upstream wall 412A of the first air intake trough 202 and plates 1004, 1006. Figure 10 In the example shown, adjacent suppression (e.g., partial suppression, complete suppression, etc.) of airflow along the first bleed airflow path 208 occurs at plates 1002, 1004, and 1006. In some examples, in the second geometry 1026, the curvatures 1036, 1038, and 1040 of plates 1002, 1004, and 1006 reduce the flow area of ​​the first bleed airflow path 208, which can reduce recirculation and / or other air effects that reduce pressure recovery in the first bleed air slot 202. As used herein, the second geometry 1026 is also referred to herein as a “partially closed geometry” and a “partially closed location.”

[0069] In the third geometry 1028, the first plate 1002 has a seventh curvature 1042, the second plate 1004 has an eighth curvature 1044, and the third plate 1006 has a ninth curvature 1046. Figure 10 In the example shown, in the seventh curvature 1042, the first end 1012 of the first plate 1002 is adjacent to the upstream wall 412A of the first air intake trough 204. Figure 10 In the example shown, in the eighth curvature 1044, the third end of the second plate 1004 is adjacent to the first plate 1002. Figure 10 In the example shown, in the ninth curvature 1046, the fifth end 1020 of the third plate 1006 is adjacent to the second plate 1004. Figure 10 In the example shown, the adjacency of plates 1002, 1004, 1006 inhibits (e.g., partially inhibits, completely inhibits, etc.) the flow of air along the first air intake flow path 208. In some examples, depending on the presence of openings in plates 1002, 1004, 1006 and / or the shape of plates 1002, 1004, 1006, in the third geometry 1028, the fourth variable wall structure 1000 prevents air from flowing through the first air intake flow path 208. In some examples, in the third geometry 1028, the adjacency of plates 1002, 1004, 1006 mitigates (e.g., reduces, prevents, etc.) other air effects that reduce recirculation and decrease pressure recovery in the first air intake slot 202. As used herein, the third geometry 1028 is also referred to herein as a “fully closed geometry,” a “closed geometry,” and a “closed position.”

[0070] Figure 11A yes Figure 2A schematic diagram of the first air intake trough 202 and an example of a fifth variable wall structure 1100 implemented according to the teachings of this disclosure. Figure 11A In the example shown, the fifth variable wall structure 1100 includes Figure 3 The components include 304, 1102, 1104, and 1106. Figure 11A In the example shown, the fifth variable wall structure 1100 is in the first geometry 1108, which corresponds to when the gas turbine engine 110 has Figure 4A The position of the fifth variable wall structure 1100 under the first environmental condition 402 (e.g., high-power engine conditions, etc.). Figure 11A In the example shown, the first plate 1102 has a first end 1110 and a second end 1112. Figure 11A In the example shown, the second plate 1104 has a third end 1114 and a fourth end 1116. Figure 11A In the example shown, member 304 extends from upstream wall 412A. In other examples, member 304 extends from downstream wall 412B.

[0071] Plates 1102 and 1104 are variable geometry structures, disposed within the air intake chamber 307 of the first air intake groove 202. Figure 11A In the example shown, the first end 1110 of the first plate 1102 and the third end 1114 of the second plate 1104 are connected to the member 304, such that the second end 1112 of the first plate 1102 and the fourth end 1116 of the second plate 1104 are cantilevered (e.g., suspended) within the air duct 307. Figure 11A In the example shown, the first end 1110 of the first plate 1102 and the third end 1114 of the second plate 1104 are connected by a joint 1120 (e.g., a hinge). The joint 1120 allows the plates 1102 and 1104 to rotate about the joint 1120 (e.g., the first plate 1102 rotates about the first end 1110, the second plate 1104 rotates about the third end 1114, etc.), allowing the distance between the second end 1112 and the fourth end 1116 to vary (e.g., depending on the environmental conditions of the air chamber 307, etc.). Figure 11A In the example shown, plates 1102 and 1104 are approximately equidistant from each other between the upstream wall 412A and the downstream wall 412B. In other examples, plates 1102 and 1104 may be positioned at another location in the air venting chamber 307 (e.g., closer to the upstream wall 412A, etc.).

[0072] exist Figure 11A In the example shown, plates 1102 and 1104 each include a first plurality of openings 1118A and a second plurality of openings 1118B. Openings 1118A and 1118B are perforations, openings, gaps, etc., in plates 1102 and 1104, allowing air to flow through them. Figure 11A In the example shown, openings 1118A and 1118B have a uniform pattern (e.g., a grid pattern, etc.). In other examples, openings 1118A and 1118B are arranged in a non-uniform manner (e.g., a random arrangement, etc.). In some examples, openings 1118A and 1118B respectively suppress (e.g., reduce, etc.) the acoustic effects associated with airflow over plates 1102 and 1104. Figure 11A In the examples shown, openings 1118A and 1118B can have any suitable geometry (e.g., circular, polygonal, slotted, oval, irregular, etc.). In other examples, some or all of openings 1118A and 1118B are absent. In some such examples, one or both of plates 1102 and 1104 are solid. Figure 11A In the example shown, one of the first plurality of openings 1118A is aligned with a corresponding one of the second plurality of openings 1118B.

[0073] exist Figure 11A In the example shown, the second end 1112 and the fourth end 1116 are connected by a biasing member 1106. As used herein, a "biasing member" is a mechanical structure that applies a biasing force to another structure. The biasing member 1106 biases plates 1102 and 1104 toward the upstream wall 412A and the downstream wall 412B, respectively. That is, the biasing member 1106 applies a biasing force to plates 1102 and 1104. For example, the biasing member 1106 can be implemented by a spring (e.g., a flat spring, leaf spring, air spring, coil spring, disc spring, etc.). In some such examples, the biasing force of the biasing member 1106 is resisted by the ambient pressure within the air chamber 307. For example, as the pressure in the air chamber 307 increases, the pressure acting on plates 1102 and 1104 biases ends 1112 and 1116 together, thus opposing the biasing force of the biasing member 1106. Under high pressure conditions, such as the first environmental condition 402, the relatively large pressure of the flow in the first bleed air flow path 208 overcomes the biasing force of the biasing member 1106, and causes the plates 1102 and 1104 to have Figure 11A The first geometric shape is 1108. Figure 11A In the example shown, the bias member 1106 is V-shaped. In other examples, the bias member 1106 may have different shapes (e.g., C-shaped, U-shaped, coil-shaped, etc.).

[0074] Additionally or alternatively, the bias member 1106 may have a variable geometry based on the ambient temperature within the bleed air chamber 307. For example, the bias member 1106 may be composed of a smart metal alloy (SMA). In some such examples, the bias member 1106 may be composed of any suitable SMA (e.g., copper-aluminum-nickel alloy, nickel-titanium alloy, iron-magnesium-tin alloy, copper-zinc-aluminum alloy, copper-aluminum-nickel alloy, etc.). In such examples, when the bias member 1106 is heated (e.g., under hot engine conditions such as takeoff), the SMA may be configured to bend to a retracted position (e.g., Figure 11A (as shown in the diagram). In some such examples, the rigid connection between ends 1112, 1116 and the biasing member 1106 causes the fifth variable wall structure 1100 to become Figure 11A The first geometric shape is 1108.

[0075] Additionally or alternatively, the bias member 1106 may be composed of multiple layers of materials. For example, the bias member 1106 may be composed of two layers of different metals (e.g., a bimetallic structure, etc.) that are rigidly connected and have different coefficients of thermal expansion. For example, the bias member 1106 may include a first layer composed of aluminum, titanium, steel, nickel alloys and / or another metal and a second layer composed of different metals (e.g., different titaniums, different aluminums, different nickel alloys, different steels, etc.). When the bias member 1106 is heated, the materials of the bias member 1106 expand at different rates, which causes the bias member 1106 to bend. In some such examples, the rigid connection of the ends 1112, 1116 with the bias member 1106 causes the fifth variable wall structure 1100 to become Figure 11A The first geometric shape is 1108.

[0076] exist Figure 11A In the example shown, in the first geometry 1108, plates 1102 and 1104 are substantially parallel, and ends 1112 and 1116 are adjacent (e.g., ends 1112 and 1116 are adjacent, or there is a small gap between ends 1112 and 1116, etc.). In some examples, plates 1102 and 1104 are adjacent along their lengths. Figure 4A In the example shown, the first geometry 1108 of the fifth variable wall structure 1100 does not substantially inhibit airflow through the first air intake path 208. That is, in the first environmental condition 402, the plates 1102 and 1104 of the fifth variable wall structure 1100 do not substantially inhibit airflow through the first air intake groove 202.

[0077] Figure 11B yes Figure 2 The first air intake slot 202 and Figure 11A-11B A schematic diagram of the fifth variable wall structure 1100. In Figure 11BIn the example shown, the fifth variable wall structure 1100 is in the second geometry 1122, which corresponds to when the gas turbine engine 110 is in Figure 4B The position of the fifth variable wall structure 1100 under the second environmental condition 408 (e.g., low-power engine condition, etc.). For example, if the bias member 1106 is temperature sensitive (e.g., the bias member 1106 is composed of SMA, the bias member 1106 is bimetallic, etc.), the lower temperature of the second environmental condition 408 compared to the first environmental condition 402 causes the bias member 1106 to expand and move the ends 1112, 1116 toward the walls 412A, 412B, respectively. Additionally or alternatively, if the bias member 1106 is pressure sensitive (e.g., the bias member 1106 is a spring, etc.), the lower pressure of the second environmental condition 408 compared to the first environmental condition 402 causes the spring force of the bias member 1106 to move the ends 1112, 1116 toward the walls 412A, 412B, respectively.

[0078] exist Figure 11B In the example shown, the expansion of the bias member 1106 causes plates 1102 and 1104 to rotate about the connector 1120 and form a blocking region 1124. Figure 11A In the example shown, the obstruction region 1124 is located at the center of the air intake chamber 307. In other examples, depending on the location of the fifth variable wall structure 1100, the obstruction region 1124 may be located at another location within the air intake chamber 307 (e.g., adjacent to the upstream wall 412A, etc.). Figure 11B In the example shown, in the second geometry 1122, the second end 1112 is removed from the fourth end 1116. The blockage region 1124 reduces the flow area through the first bleed air flow path 208. Figure 3-4B The first variable wall structure 300 is the same. Figure 11A-11B The fifth variable wall structure 1100 increases the pressure recovery of the first bleed air slot 202 under low-power engine conditions. That is, the expansion of the bias member 1106 and the rotation of the plates 1102, 1104 in the second geometry 1122 inhibit the recirculation of the bleed air in the first bleed air flow path 208 by creating a blocking region 1124.

[0079] Figure 12 yes Figure 11A A perspective view of the fifth variable wall structure 1100, which is set in Figure 2 In the compressor housing 200. Figure 12 In the example shown, the compressor housing 200 includes Figure 2 First air intake slot 202, Figure 3 The air venting chamber 307 Figure 4A and 4B Walls 412A, 412B and Figure 5Deflection plate 506. In Figure 12 In the example shown, the fifth variable wall structure 1100 includes Figure 11A and 11B Boards 1102 and 1104 Figure 3 , 11A and component 304 of 11B and Figure 11A and 11B Connector 1120. In Figure 12 In the example shown, the fifth variable wall structure 1100 has Figure 11A The first geometric shape 1108 (represented by solid lines) and Figure 11B The second geometric shape 1122 (represented by dashed lines).

[0080] exist Figure 12 In the example shown, member 304 is a support extending between upstream wall 412A and downstream wall 412B. In other examples, member 304 extends only from upstream wall 412A or only from downstream wall 412B. Figure 12 In the example shown, connector 1120 is formed in member 304. In some such examples, member 304 may include a notch and / or other openings to facilitate rotation of plates 1102, 1104 about connector 1120 (e.g., expansion of connector 1120, etc.). Figure 12 In the example shown, the upstream wall 412A of the first air intake channel 202 is Figure 5 The deflection plate 506. In other examples, the deflection plate 506 is absent, and the upstream wall 412A is formed by a portion of the compressor housing 200. Figure 12 In the example shown, component 304 is connected to two plates 1102, 1104. In other examples, component 304 may be implemented by any other suitable structure that allows flow through the first air duct 202 to pass through component 304 (e.g., lattice, corrugated sheet, etc.).

[0081] exist Figure 12 In the example shown, bias member 1106 is absent. Figure 12 In the example shown, plates 1102 and 1104 may be composed of temperature-sensitive materials (e.g., SMA, bimetallic layers, etc.). In some such examples, as the temperature of the air bleed chamber 307 changes (e.g., from...), the temperature of the air bleed chamber 307 changes (e.g., from...). Figure 4A and 11A The first environmental condition 402 becomes Figure 4B and 11BThe materials of plates 1102 and 1104 may cause them to bend and the fifth variable wall structure 1100 to take on a corresponding geometry of 1108 or 1122, depending on the second environmental condition 408, etc. That is, the material composition of plates 1102 and 1104 causes them to rotate about the joint 1120 and the fifth variable wall structure 1100 to take on different geometries (e.g., geometries 1108, 1122, geometries between the first and second geometries 1122, etc.) based on the ambient temperature of the first air duct 202 (e.g., first environmental condition 402, second environmental condition 408, environmental conditions with temperatures between the first and second environmental conditions 402, etc.). In other examples, a biasing member 1106 is disposed between plates 1102 and 1104.

[0082] Figure 13 yes Figure 2 A schematic diagram of the first air intake groove 202 and an example of a sixth variable wall structure 1300 implemented according to the teachings of the present invention. Figure 13 In the example shown, the sixth variable wall structure 1300 includes a first plate 1302, a second plate 1304, a first member 1306, and a second member 1308. Figure 13 In the example shown, the first plate 1302 has a first end 1310 and a second end 1312. Figure 13 In the example shown, the first end 1310 of the first plate 1302 is connected to the first member 1306, while the second end 1312 of the second plate 1304 is suspended in the air duct 307. Figure 13 In the example shown, the second plate 1304 has a third end 1314 and a fourth end 1316.

[0083] exist Figure 13 In the example shown, the third end 1314 is connected to the second component 1308, while the fourth end 1316 is suspended in the air bleed chamber 307. Figure 13 In the example shown, the compressor housing 200 includes Figure 2 First air intake slot 202, Figure 3 The air venting chamber 307 and Figure 4A and 4B Walls 412A and 412B. Components 1306 and 1308 and... Figure 3 The component 304 is similar, except that (1) the first component 1306 extends from the upstream wall 412A to the first plate 1302, (2) the second component 1308 extends from the downstream wall 412B to the second plate 1304, and (3) as otherwise described.

[0084] exist Figure 13In the example shown, the sixth variable wall structure 1300 has a first geometry 1317 (shown in solid lines) and a second geometry 1318 (shown in dashed lines). In some examples, the first geometry 1317 corresponds to when the gas turbine engine 110 has high-power engine conditions (e.g., Figure 4A The position of the sixth variable wall structure 1300 under the first environmental condition 402, etc., and corresponding to the position of the gas turbine engine 110 under high-power engine conditions (e.g., Figure 4B When the second environmental condition 408, etc., is applied, the second geometry of the sixth variable wall structure 1300 is 1318.

[0085] exist Figure 13 In the example shown, plates 1302 and 1304 are variable geometry structures, which are set in... Figure 3 In the air venting chamber 307. Unless otherwise stated herein, plates 1302, 1304 and Figure 3 , 4A Similar to plate 302 of 4B. For example, plates 1302 and 1304 can be composed of SMA or two or more layered metals. Figure 13 In the example shown, the first plate 1302 has a first curvature 1320 in the first geometry 1317 and a second curvature 1322 in the second geometry 1318. Figure 13 In the example shown, the second plate 1304 has a third curvature 1324 in the first geometry 1317 and a fourth curvature 1326 in the second geometry 1318. In the first geometry 1317 and with curvatures 1320 and 1324, plates 1302 and 1304 are approximately planar (e.g., the ends 1310 and 1312 of the first plate 1302 are coplanar, and the ends 1314 and 1316 of the second plate 1304 are coplanar, etc.). In the second geometry 1318 and with curvatures 1322 and 1326, plates 1302 and 1304 are non-planar (e.g., the ends 1310 and 1312 of the first plate 1302 are not coplanar, and the ends 1314 and 1316 of the second plate 1304 are not coplanar, etc.).

[0086] exist Figure 13 In the example shown, plates 1302 and 1304 define a channel 1328 within the air venting chamber 307. Figure 13In the example shown, plates 1302 and 1304 are parallel in the first geometry 1317 (e.g., the distance between the first end 1310 and the third end 1314 is the same as the distance between the second end 1312 and the fourth end 1316, and the channel 1328 has a uniform spacing along plates 1302 and 1304, etc.). In other examples, plates 1302 and 1304 converge along the first airflow path 208 (e.g., the channel 1328 expands along the first airflow path 208, etc.) and / or diverge along the first airflow path 208 (e.g., the channel 1328 retracts along the first airflow path 208, etc.). In the first geometry 1317 (e.g., under high-power engine conditions, etc.), air can flow through the channel 1328 (e.g., between plates 1302 and 1304, etc.), between the first plate 1302 and the upstream wall 412A, and between the second plate 1304 and the downstream wall 412B. Figure 13 In the example shown, in the first geometry 1317, the sixth variable wall structure 1300 does not inhibit the flow of air through the first air intake slot 202 under the first environmental condition 402.

[0087] In the second geometry 1318, plates 1302 and 1304 exhibit a second curvature 1322 and a fourth curvature 1326, respectively, in response to a temperature drop in the bleed air chamber 307 (e.g., during low-power engine conditions, in...). Figure 4B During the second environmental condition 408, etc.). The second curvature 1322 of the first plate 1302 causes the second end 1312 to deflect towards the upstream wall 412A and form the first blocking region 1330A. The fourth curvature 1326 of the second plate 1304 causes the fourth end 1316 to deflect towards the downstream wall 412B and form the second blocking region 1330B. Figure 13 In the example shown, the second end 1312 and the fourth end 1316 are spaced apart from walls 412A and 412B, respectively, allowing some air to pass through obstructed regions 1330A and 1330B (e.g., obstructed regions 1330A and 1330B are partially obstructed regions, etc.). In other examples, one or both ends 1312 and 1316 of plates 1302 and 1304 are adjacent to the corresponding walls in walls 412A and 412B (e.g., in contact, nearly adjacent, etc.). In some such examples, flow cannot pass through obstructed regions 1330A and 1330B and can only flow through channel 1328. In the second geometry 1318, plates 1302 and 1304 mitigate (e.g., reduce, prevent, etc.) recirculation (e.g., backflow, eddies, vortices, etc.) and / or other turbulence effects in obstructed regions 1330A and 1330B, which are related to the diversion of air from the main flow path 206 to the first bleed flow path 208. In some examples, the reduction in recirculation and other turbulence effects increases the pressure recovery of the first bleed-out duct 202. Therefore, Figure 13The sixth variable wall structure 1300 increases the pressure of the bleed air drawn from the first bleed slot 202 and the usefulness of the drawn bleed air.

[0088] Figure 14 yes Figure 2 A schematic diagram of the first air intake channel 202 and the seventh variable wall structure 1400 implemented in accordance with the teachings of this disclosure. Figure 14 In the example shown, the seventh variable wall structure 1400 includes a first plate 1402, a second plate 1404, Figure 13 The first component 1306 and Figure 13 The second component 1308. In Figure 14 In the example shown, the first plate 1402 has a first end 1406 and a second end 1408. Figure 14 In the example shown, the first end 1406 of the first plate 1402 is connected to the first member 1306, and the second end 1408 of the first plate 1402 is suspended in the air venting chamber 307. Figure 14 In the example shown, the second plate 1404 has a third end 1410 and a fourth end 1412. Figure 14 In the example shown, the third end 1410 of the second plate 1404 is connected to the second member 1308, and the fourth end 1412 of the second plate 1404 is suspended in the air venting chamber 307. Figure 13 In the example shown, the compressor housing 200 includes Figure 2 First air intake slot 202, Figure 3 The air venting chamber 307 and Figure 4A and 4B Walls 412A and 412B.

[0089] exist Figure 14 In the example shown, the seventh variable wall structure 1400 has a first geometry 1414 (indicated by solid lines) and a second geometry 1416 (indicated by dashed lines). In some examples, the first geometry 1414 corresponds to the gas turbine engine 110 operating under high-power engine conditions (e.g., Figure 4A The position of the seventh variable wall structure 1400 under the first environmental condition 402, etc., and corresponding to the gas turbine engine 110 being in high-power engine conditions (e.g., Figure 4B The second geometry 1416 of the seventh variable wall structure 1400 under the second environmental condition 408, etc.

[0090] exist Figure 14 In the example shown, plates 1402 and 1404 are variable geometry structures, which are set in... Figure 3 In the air venting chamber 307. Plates 1302 and 1304 and Figure 3 , 4ASimilar to board 302 of 4B, unless otherwise stated herein. Figure 14 In the example shown, the first plate 1402 includes a first plate portion 1418 and a second plate portion 1420. Figure 14 In the example shown, the second plate 1404 includes a third plate portion 1422 and a fourth plate portion 1424. Figure 14 In the example shown, the first plate 1402 has a first curvature 1426 in the first geometry 1414 and a second curvature 1428 in the second geometry 1416. Figure 14 In the example shown, the second plate 1404 has a third curvature 1430 in the first geometry 1414 and a fourth curvature 1431 in the second geometry 1416.

[0091] exist Figure 14 In the example shown, in the first geometry 1414 and the first curvature 1426, the first plate portion 1418 and the second plate portion 1420 are approximately coplanar (e.g., the first plate 1402 is planar in the first geometry 1414, and the ends 1406, 1408 are coplanar, etc.). Figure 14 In the example shown, in the first geometry 1414 and the second curvature 1428, the third plate portion 1422 and the fourth plate portion 1424 are approximately coplanar (e.g., the second plate 1404 is planar in the second geometry, as are the ends 1410, 1412, etc.). Figure 14 In the example shown, in the second geometry 1416 and the second curvature 1428, the first plate portion 1418 is approximately planar, while the second plate portion 1420 is curved such that the second end 1408 is deflected toward the upstream wall 412A. Figure 14 In the example shown, in the second geometry 1416 and the fourth curvature 1431, the third plate portion 1422 is approximately planar, while the fourth plate portion 1424 is curved such that the fourth end 1412 is deflected toward the downstream wall 412B.

[0092] exist Figure 14 In the example shown, the first plate portion 1418 of the first plate 1402 and the third plate portion 1422 of the second plate 1404 are both approximately planar and / or static in the first geometry 1414 and the second geometry 1416. That is, plate portions 1418 and 1422 do not change and / or are insensitive to the environmental conditions of the air purging chamber 307. Figure 14In the example shown, the second plate portion 1420 of the first plate 1402 and the fourth plate portion 1424 of the second plate 1404 bend (e.g., move, deflect, etc.) in response to temperature changes in the air chamber 307. In some examples, to facilitate the movement of plate portions 1420, 1424 and the immobility of plate portions 1418, 1422, the first plate portion 1418 and the third plate portion 1422 are thicker than the second plate portion 1420 and the fourth plate portion 1424. Additionally or alternatively, the first member 1306 and / or the second member 1308 may extend along the lengths of the first plate portion 1418 and the third plate portion 1422, respectively, to prevent deflection of the plate portions 1418, 1420. Additionally or alternatively, the first plate portion 1418 and the third plate portion 1422 may be composed of a non-temperature-sensitive material, while the second plate portion 1420 and the fourth plate portion 1424 may be composed of a temperature-sensitive material (e.g., SMA, bimetallic material, etc.). In other examples, plates 1402 and 1404 may be composed entirely of temperature-sensitive materials.

[0093] exist Figure 14 In the example shown, the first plate portion 1418 and the third plate portion 1422 are in Figure 3 A channel 1432 is defined within the air venting chamber 307. Figure 14 In the example shown, in the first geometry 1414, channel 1432 extends along the length of plates 1402, 1404 (e.g., channel 1432 extends between the second plate portion 1420 and the fourth plate portion 1424, etc.). In the first geometry 1414 (e.g., during high-power engine conditions, during a first period, etc.), air can flow through channel 1432 (e.g., between plates 1402, 1404, etc.), between the first plate 1402 and the upstream wall 412A, and between the second plate 1404 and the downstream wall 412B. Figure 14 In the example shown, in the first geometry 1414, the curvatures 1426 and 1431 of the plates 1402 and 1404 of the seventh variable wall structure 1400 do not inhibit the flow of air in the first environmental condition 402 through the first air intake groove 202.

[0094] In the second geometry 1416, plates 1402 and 1404 exhibit a second curvature 1428 and a fourth curvature 1431, respectively, in response to a temperature drop in the bleed air chamber 307 (e.g., during low-power engine conditions, in...). Figure 4B During the second environmental condition 408, etc.). The second curvature 1428 of the first plate 1402 causes the second end 1408 to deflect towards the upstream wall 412A to form the first blocking region 1434A. The fourth curvature 1431 of the second plate 1404 causes the fourth end 1412 to deflect towards the downstream wall 412B to form the second blocking region 1434B. Figure 14In the example shown, the second end 1408 and the fourth end 1412 are spaced apart from walls 412A and 412B, respectively, allowing some air to pass through the obstruction regions 1434A and 1434B (e.g., obstruction regions 1434A and 1434B are partially obstructed regions, etc.). In other examples, one or both ends 1408 and 1412 of plates 1402 and 1404 may be adjacent to (e.g., in contact, nearly adjacent, etc.) the corresponding walls in walls 412A and 412B. In some such examples, flow cannot pass through obstruction regions 1434A and 1434B and can only flow through channel 1432. In the second geometry 1416, plates 1402 and 1404 reduce recirculation (e.g., backflow, eddies, vortices, etc.) and / or other turbulence effects in obstruction regions 1434A and 1434B, which are associated with air diverting from the main flow path 206 to the first bleed flow path 208. In some examples, the reduction in recirculation and other turbulence effects increases the pressure recovery of the first bleed-out duct 202. Therefore, Figure 14 The seventh variable wall structure 1400 increases the pressure of the bleed air extracted from the first bleed slot 202 and the usefulness of the extracted bleed air.

[0095] This paper discloses an example variable wall structure for use in a compressor bleed air sump. The example variable wall structure disclosed herein can move between different positions depending on engine conditions. The example disclosed herein reduces recirculation and other turbulence effects in the bleed air sump during low-power engine conditions. The reduction in recirculation effects reduces pressure loss within the compressor bleed air sump, thereby increasing the pressure and energy of the extracted bleed air. The increase in the pressure and energy of the extracted bleed air increases its usability (e.g., the amount of work that can be extracted, etc.).

[0096] Further aspects of this disclosure are provided by the subject matter of the following clauses:

[0097] An apparatus for connecting to the wall of a bleed air slot of a compressor of a gas turbine engine, the bleed air slot defining a flow path, the apparatus including a member connected to the wall and a plate connected to the member, the plate having a first geometry at a first time under a first environmental condition and a second geometry at a second time under a second environmental condition, the flow path having a first area when the plate has the first geometry and a second area when the plate has the second geometry, the first area being greater than the second area, the first time being after the second time.

[0098] The apparatus according to any of the preceding items, wherein the plate includes a plurality of through openings.

[0099] The apparatus according to any of the preceding items, wherein the first environmental condition includes a first temperature, the second environmental condition includes a second temperature, and the first temperature is higher than the second temperature.

[0100] The apparatus according to any of the preceding items, wherein the plate comprises a shape memory alloy.

[0101] The apparatus according to any of the preceding items, wherein the plate includes a first layer and a second layer, the first layer including a first material having a first coefficient of thermal expansion, and the second layer including a second material having a second coefficient of thermal expansion.

[0102] The apparatus according to any of the preceding items, wherein the plate includes curvature in the second geometry and the plate is approximately planar in the first geometry.

[0103] The apparatus according to any of the preceding items, wherein the plate is a first plate, and the apparatus further includes a second plate connected to the member, the first plate including a first side, the second plate including a second side adjacent to the first side, the second plate having a first geometry under a first environmental condition, and a second geometry under a second environmental condition.

[0104] The apparatus according to any of the preceding items, wherein the components include at least one of (1) a pillar, (2) a honeycomb lattice or (3) a corrugated sheet.

[0105] The apparatus according to any of the preceding items, wherein the plate is a first plate, wherein the member is a first member, the first plate includes a first end and a second end, and the apparatus further includes a second plate including a third end and a fourth end, a connector connecting the third end to the first end, and a second member extending between the fourth end and the first end, the second member applying a biasing force to the first plate.

[0106] According to any of the preceding items, in the first geometry, the first plate is parallel to and joined with the second plate, and in the second geometry, the fourth end is spaced apart from the first end.

[0107] The apparatus according to any of the preceding items, wherein the second component is V-shaped.

[0108] The apparatus according to any of the preceding items, wherein the first plate includes a first plurality of openings, and when the first plate has a first geometry, the second plate includes a second plurality of openings aligned with the first plurality of openings.

[0109] The device according to any of the preceding items, wherein the second component includes a spring, the first environmental condition includes a first pressure, the second environmental condition includes a second pressure, and the second pressure is greater than the first pressure.

[0110] The apparatus according to any of the preceding items, wherein the second component comprises a shape memory alloy.

[0111] The apparatus according to any of the preceding items, wherein the second component includes a first layer and a second layer, the first layer including a first material having a first coefficient of thermal expansion, and the second layer including a second material having a second coefficient of thermal expansion.

[0112] The apparatus according to any of the preceding items, wherein the plate is a first plate, the member is a first member, the first plate includes a first end, and the apparatus further includes a second plate engaged with the first plate in a second geometry, and a third plate engaged with the second plate in a second geometry.

[0113] The apparatus according to any of the preceding claims, wherein the plate is a first plate, the first plate includes a first portion and a second portion, and the apparatus further includes a second plate spaced apart from the first plate, the second plate including a third portion parallel to the first portion in a first geometry and a second geometry, and a fourth portion parallel to the second portion in the first geometry, the fourth portion being deflected from the second portion in the second geometry.

[0114] A compressor includes the means according to any of the preceding items, wherein the compressor defines a radial axis, an axial axis and a circumferential axis, and a member extends circumferentially between a wall and a plate.

[0115] The compressor according to any of the preceding items, wherein the flow path is an air intake flow path, the wall is a first wall, and the compressor includes a housing defining a main flow path, and the air intake channel includes a first wall and a second wall located downstream of the first wall relative to the main flow path, and wherein the plate is deflected toward the first wall in a first geometry.

[0116] A gas turbine engine includes a compressor according to any of the preceding claims, and a combustion section connected to the compressor.

[0117] A compressor defining a radial axis, an axial axis, and a circumferential axis, the compressor including a compressor housing, the compressor housing including an air intake channel, the air intake channel including a wall, the wall structure including a member connected to the wall, and a plate connected to the member, the plate having a first geometry under a first environmental condition at a first time and a second geometry under a second environmental condition at a second time, a flow path having a first area when the plate has the first geometry, and a flow path having a second area when the plate has the second geometry, the first area being greater than the second area, and the first time being after the second time.

[0118] The compressor according to any of the preceding items, wherein the flow path is an air intake flow path, the wall is a first wall, and the air intake slot further includes a second wall located downstream of the first wall relative to the main flow path, and the plate is deflected toward the first wall in a first geometry.

[0119] A gas turbine engine includes a compressor, the compressor housing including a bleed air channel, the bleed air channel including a wall, the wall structure including a member connected to the wall, and a plate connected to the member, the plate having a first geometry under a first environmental condition at a first time and a second geometry under a second environmental condition at a second time, a flow path having a first area when the plate has the first geometry, and a flow path having a second area when the plate has the second geometry, the first area being greater than the second area, and the first time occurring after the second time; and a combustion section connected to the compressor.

[0120] The following claims are hereby incorporated by reference in this detailed description. Although certain example systems, apparatuses, articles, and methods have been disclosed herein, the scope of this document is not limited thereto. Rather, this document covers all systems, apparatuses, articles, and methods that fall fully within the scope of the claims herein.

Claims

1. A device for connecting to the wall of a bleed air chute of a compressor of a gas turbine engine, the bleed air chute defining a flow path, characterized in that, The device includes: Components, the components being connected to the wall; and A plate, the plate being connected to the member, the plate having: In a first geometry under a first environmental condition at a first time, when the plate has the first geometry, the flow path has a first area; and In a second time and under a second environmental condition, the flow path has a second area when the plate has the second geometry, the first area is larger than the second area, and the first time is after the second time.

2. The apparatus according to claim 1, characterized in that, The plate includes multiple openings.

3. The apparatus according to claim 1, characterized in that, The first environmental condition includes a first temperature, the second environmental condition includes a second temperature, and the first temperature is higher than the second temperature.

4. The apparatus according to claim 3, characterized in that, The plate mentioned above includes a shape memory alloy.

5. The apparatus according to claim 3, characterized in that, The plate said plate includes: A first layer, the first layer comprising a first material having a first coefficient of thermal expansion; and The second layer comprises a second material having a second coefficient of thermal expansion.

6. The apparatus according to claim 1, characterized in that, The plate includes curvature in the second geometry and is planar in the first geometry.

7. The apparatus according to claim 6, characterized in that, The plate is a first plate, and the device further includes a second plate coupled to the member, the first plate including a first side, the second plate including a second side adjacent to the first side, the second plate having the first geometry under the first environmental conditions and having the second geometry under the second environmental conditions.

8. The apparatus according to claim 1, characterized in that, The component includes at least one of (1) a strut, (2) a honeycomb lattice, or (3) a corrugated sheet.

9. The apparatus according to claim 1, characterized in that, The plate is a first plate, the component is a first component, the first plate includes a first end and a second end, and the device further includes: The second board, the second board includes: The third end; and Fourth end; A connector that connects the third end to the first end; and A second member extends between the fourth end and the first end, and the second member applies a biasing force to the first plate.

10. The apparatus according to claim 9, characterized in that, In the first geometry, the first plate is parallel to and joined with the second plate, and in the second geometry, the fourth end is spaced apart from the first end.

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