Extraction scoop for discharge pressure recovery in a gas turbine engine

Abstract

An example gas turbine engine includes a compressor including a casing defining a passage, and a shaft extending through the passage. The shaft is drivingly coupled to the compressor and a turbine of the gas turbine engine. The shaft has an opening for receiving a flow of gas from the passage. The gas turbine engine further includes an inner shroud, a stator vane coupled to and extending radially between the casing and the inner shroud, and a scoop disposed on a downstream side of the inner shroud. The scoop has a channel to direct the flow of gas radially inward toward the opening in the shaft.

Description

Technical Field

[0001] This disclosure generally relates to gas turbine engines, and more specifically, to exhaust pressure recovery in gas turbine engines. Background Technology

[0002] Turbofan engines (such as those used in aircraft) typically consist of a fan, a gas turbine engine that drives the fan, and an external bypass duct. A gas turbine engine includes one or more compressors, combustors, and one or more turbines arranged in a series flow configuration. Some gas turbine engines extract high-pressure air from one of the compressors, called "bleed air." This bleed air is directed to the turbine to cool it. Attached Figure Description

[0003] The specification with reference to the accompanying drawings sets forth a complete and feasible disclosure of the technology currently described to those skilled in the art, including its best mode, wherein:

[0004] Figure 1 This is a schematic cross-sectional view of an example turbofan engine from which the examples disclosed herein can be implemented;

[0005] Figure 2 is Figure 1 The enlarged view with annotations in the figure shows a portion of an example high-pressure compressor of an example turbofan engine with a known inner shield;

[0006] Figure 3 An enlarged view of Figure 2 is shown, which has an example of removing a spoon constructed according to the teachings of this disclosure;

[0007] Figure 4 It is along Figure 3 The cross-sectional view taken by line BB shows an example of removing the spoon;

[0008] Figure 5 yes Figure 3 and 4 An example of a three-dimensional cross-sectional view of a portion of a spoon being removed; and

[0009] Figure 6 The example shown in Figure 2 is an example of removing the spoon without the guide wheel blades.

[0010] Reference numerals used repeatedly in this specification and drawings are intended to indicate the same or similar features or elements of this disclosure. Detailed Implementation

[0011] Reference will now be made in detail to embodiments or examples of the currently described technology, one or more of which are illustrated in the accompanying drawings. Each example is provided by way of explanation and not limitation of the currently described technology. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made to the currently described technology without departing from the scope or spirit of the technology. For example, features shown or described as part of an embodiment or example may be used with another embodiment or example to produce yet another embodiment or example. Therefore, the currently described technology is intended to cover these modifications and variations that fall within the scope of the appended claims and their equivalents.

[0012] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components.

[0013] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0014] This document discloses an example bleed scoop and an example inner shroud with the example bleed scoop, which improves bleed airflow in a gas turbine engine. Turbofan engines (such as those used in aircraft) include gas turbine engines. A gas turbine engine includes a compressor, a combustor, and a turbine arranged in a series flow pattern. The gas turbine engine includes a shaft operatively connecting the turbine and the compressor, such that the turbine drives the compressor during operation of the gas turbine engine. In some cases, gas turbine engines are designed to extract some high-pressure air from the compressor. This extracted air is commonly referred to as "bleed air." The bleed air is directed to the turbine to cool it, which improves the efficiency of the gas turbine engine.

[0015] To extract the bleed air from the compressor, a portion of the compressor shaft has an opening (sometimes called a discharge port or outlet). A portion of the high-pressure air in the compressor flows through the opening and into the inner passage of the shaft. The inner passage (along with one or more channels or pipes) directs the airflow downstream to the turbine to cool it. For example, the airflow can be used to cool turbine blades and rotating disks to extend cycle life and hardware durability (static and rotating). This increases blade tip clearance, thereby improving efficiency (compression and / or power extraction). Additionally or alternatively, the air can be used for servicing purposes such as sump pressurization, sump cooling, fuel systems, and / or systems that manage external valves, pumps, gearboxes, full authority digital engine control (FADEC) computers, etc. However, the airflow in the compressor outside the opening often experiences significant pressure losses as it travels radially inward due to eddies. This reduces the bleed air pressure in the inner passage of the shaft, which adversely affects the cooling of downstream turbine blades and rotating components.

[0016] This document discloses an example removal spoon and an example inner shroud with the example removal spoon, which improves airflow in the opening into the shaft. The compressor of a gas turbine engine includes a housing and a plurality of stator blades extending radially inward from the housing. The compressor includes an inner shroud, which is a circular or annular member surrounding the shaft. The radially inner ends of the stator blades are coupled to the inner shroud, such that the stator is coupled to the housing and the inner shroud and extends radially between the housing and the inner shroud. In some examples disclosed herein, the example removal spoon is positioned on the downstream side of the inner shroud. The removal spoon directs the airflow exiting the stator blades radially inward toward the opening in the shaft. Therefore, the airflow is smoother or more laminar, which improves exhaust pressure recovery and cooling supply air return margin.

[0017] In some examples, the extraction scoop includes an upstream wall and a downstream wall spaced apart from the upstream wall, such that a channel is formed between the upstream and downstream walls. The channel is shaped to guide airflow from the compressor radially inward toward an opening in the shaft. In some examples, the extraction scoop includes guide vanes in the channel. The guide vanes help to further improve airflow toward the opening. In some examples, the guide vanes have an airfoil cross-section. In some examples, the extraction scoop is integrally formed with a portion of an inner shroud. For example, the inner shroud may include a body and a panel on the radially outer side of the body. In some examples, the panel is a sheet of metal. In some examples, the extraction scoop is coupled to the downstream side of the panel. For example, the upstream wall may be an extension or portion of a radially inwardly curved panel.

[0018] Referring now to the accompanying drawings, where the same numbers indicate the same elements throughout all the drawings. Figure 1This is a schematic cross-sectional view of an example high-bypass turbofan gas turbine engine 100 (“turbofan engine 100”) that can be combined with the various examples disclosed herein. Although the example shown 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.

[0019] like Figure 1 As shown, the turbofan engine 100 includes an external bypass duct 104 (which may also be referred to as a nacelle, fan duct, or casing), a gas turbine engine 106 (which may also be referred to as a core turbine engine or turbomachinery), and a fan section 108. The gas turbine engine 106 and the fan section 108 are at least partially disposed within the external bypass duct 104. The gas turbine engine 106 is disposed downstream of the fan section 108 and drives the fan section 108 to generate forward thrust. Figure 1 As shown, the turbofan engine 100 and / or the gas turbine engine 106 define a longitudinal or axial centerline axis 102 extending therethrough, for reference. Figure 1 It also includes annotated direction diagrams for the axial direction A, radial direction R, and circumferential direction C. Generally, as used herein, the axial direction A is a direction extending approximately parallel to the centerline axis 102, the radial direction R is a direction extending orthogonally outward from or inward toward the centerline axis 102, and the circumferential direction C is a direction extending concentrically around the centerline axis 102.

[0020] The gas turbine engine 106 includes a basic tubular housing 110 (also referred to as a middle housing) defining an annular inlet 112. The housing 110 of the gas turbine engine 106 may be formed from a single housing or multiple housings. The housing 110 surrounds, in a series flow relationship: a compressor section having a boost or low-pressure compressor 114 (“LP compressor 114”) and a high-pressure compressor 116 (“HP compressor 116”); a combustion section 118 (also referred to as a combustor 118); a turbine section having a high-pressure turbine 120 (“HP turbine 120”) and a low-pressure turbine 122 (“LP turbine 122”); and an exhaust section 124. The gas turbine engine 106 includes a high-pressure shaft or spool 126 (“HP shaft 126”) drivably connected to the HP turbine 120 and the HP compressor 116. The gas turbine engine 106 also includes a low-pressure shaft or spool 128 (“LP shaft 128”) drivably connected to the LP turbine 122 and the LP compressor 114. The LP shaft 128 can also be connected to the fan spool or shaft 130 of the fan section 108. In some examples, the LP shaft 128 can be directly connected to the fan shaft 130 (i.e., a direct drive configuration). In alternative configurations, the LP shaft 128 can be connected to the fan shaft 130 via a reduction gear 132 (i.e., an indirect drive or gear-driven configuration). Although in this example the gas turbine engine 106 includes two compressors and two turbines, in other examples the gas turbine engine 106 may include only one compressor and one turbine.

[0021] like Figure 1 As shown, the fan section 108 includes a plurality of fan blades 134, which are coupled to and extend radially outward from the fan shaft 130. An external bypass duct 104 circumferentially surrounds at least a portion of the fan section 108 and / or the gas turbine engine 106. Specifically, the gas turbine engine 106 is disposed within the external bypass duct 104, such that a bypass airflow passage or duct 136 is formed between the housing 110 of the gas turbine engine 106 and the external bypass duct 104. The external bypass duct 104 may be supported relative to the gas turbine engine 106 by a plurality of circumferentially spaced outlet guide vanes 138.

[0022] like Figure 1As shown, during operation of the turbofan engine 100, air 140 enters the inlet portion 142 of the turbofan engine 100. The air 140 is accelerated by the fan blades 134. A first portion 144 of the air 140 flows into a bypass airflow passage 136, while a second portion 146 of the air 140 flows into the inlet 112 of the gas turbine engine 106 (and thus into the LP compressor 114). One or more successive stages of the LP compressor stator blades 148 and the LP compressor rotor blades 150 coupled to the LP shaft 128 progressively compress the second portion 146 of the air 140 flowing through the LP compressor 114 and directed to the HP compressor 116. Subsequently, one or more successive stages of the HP compressor stator blades 152 and the HP compressor rotor blades 154 coupled to the HP shaft 126 further compress the second portion 146 of the air 140 flowing through the HP compressor 116. This provides compressed air 156 to the combustion section 118, where the compressed air 156 is mixed with fuel and burned to provide combustion gases 158.

[0023] Combustion gas 158 flows through HP turbine 120, where one or more successive stages of HP turbine stator blades 160 and HP turbine rotor blades 162 coupled to HP shaft 126 extract a first portion of kinetic and / or thermal energy. This energy extraction supports the operation of HP compressor 116. Combustion gas 158 then flows through LP turbine 122, where one or more successive stages of LP turbine stator blades 164 and LP turbine rotor blades 166 coupled to LP shaft 128 extract a second portion of thermal and / or kinetic energy. This energy extraction causes LP shaft 128 to rotate, which supports the operation of LP compressor 114 and / or rotation of fan shaft 130. Combustion gas 158 then exits gas turbine engine 106 through its exhaust section 124. Combustion gas 158 mixes with a first portion 144 of air 140 from bypass airflow passage 136 to generate propulsive thrust.

[0024] Similar to turbofan engine 100, gas turbine engine 106 is used for similar purposes and a similar environment is seen in land-based gas turbine engines, turbojet engines (where the ratio of the first portion 144 of air 140 to the second portion 146 of air 140 is smaller than that in turbofan engines), and ductless fan engines (where fan section 108 does not have an external bypass duct 104). In each of the turbofan engine, turbojet engine, and ductless engine, a reduction gear (e.g., reduction gear 132) may be included between any shaft and spool. For example, reduction gear 132 may be disposed between LP shaft 128 and fan shaft 130 of fan section 108.

[0025] Figure 2 is from Figure 1 The enlarged view marked 1 shows the image from... Figure 1This is part of the HP compressor 116 of the gas turbine engine 106. Figure 2 shows a known inner shroud design, which will be described in further detail below. The HP compressor 116 includes a housing 200. The housing 200 may correspond to a portion of the outer casing 110. The housing 200 defines a second portion 146 of air (e.g., air 140). Figure 1 The flow path 202 is through which the HP shaft 126 extends. As described above, the HP compressor 116 includes a plurality of rotor blades 154 (three of which are shown in Figure 2). The rotor blades 154 are coupled to and extend radially outward from the HP shaft 126. The rotor blades 154 are arranged in multiple rows or stages. Three example stages 154a-154c are labeled in Figure 2. Stages 154a-154c are spaced apart in the axial direction (A). Each of stages 154a-154c includes a plurality of rotor blades 154 circumferentially distributed around the HP shaft 126. In the gas turbine engine 106 ( Figure 1 During operation, the rotor blades 154 rotate together with the HP shaft 126.

[0026] The HP compressor 116 also includes a plurality of stator blades 152. The stator blades 152 are coupled to and extend radially inward from the housing 200. The stator blades 152 are also arranged in multiple rows or stages. Two example stages 152a and 152b are labeled in Figure 2. Stages 152a and 152b are spaced apart in the axial direction (A). Stages 152a and 152b of stator blades 152 are arranged between stages 154a-154c of rotor blades 154. Each of stages 152a and 152b includes a plurality of stator blades 152 circumferentially distributed around the housing 200. The HP compressor 116 can have any number of stages of stator blades 152 and rotor blades 154. The stages of stator blades 152 and rotor blades 154 shown in Figure 2 can correspond to any stage, such as a starting stage, intermediate stage, or ending stage. During the operation of the gas turbine engine 106, air flows through passage 202 and through each stage of stator blades 152 and rotor blades 154, before reaching the combustor 118. Figure 1 The air pressure is gradually increased beforehand.

[0027] As shown in Figure 2, the HP compressor 116 includes an inner shroud 204, which is a circular or annular component. The inner shroud 204 is disposed in the passage 202 and surrounds or encloses the HP shaft 126, but does not physically contact the HP shaft 126. The stator blades 152 of the first stage 152a are coupled to the inner shroud 204. Specifically, the radially inner ends 206 of the stator blades 152 of the first stage 152a (one of which is in…) Figure 1(Referring to the example shown) is coupled to the inner shroud 204. Therefore, the stator blades 152 are coupled to the housing 200 and the inner shroud 204 and extend radially between the housing 200 and the inner shroud 204. In some examples, the inner shroud 204 is a continuous circular or annular member. In other examples, the inner shroud 204 may be formed as two or more separate parts. In the illustrated example, the inner shroud 204 includes a panel 210. The panel 210 is disposed on and / or otherwise formed radially outward of the inner shroud 204. The radially inner end 206 of the stator blades 152 is coupled to the panel 210. In some examples, the panel 210 is a sheet metal panel. The panel 210 allows air to flow smoothly along the inner shroud 204. The HP compressor 116 may include similar inner shrouds for each of the other stages of the stator blades 152.

[0028] In the example shown in Figure 2, the HP shaft 126 has an opening 214, which can also be referred to as a discharge opening or discharge port. Specifically, as... Figure 3 As shown, the HP shaft 126 defines the inner passage 216. In the gas turbine engine 106 ( Figure 1 During operation, a portion of the high-pressure air from passage 202 exiting the first stage 152a of stator blade 152 flows through opening 214 and into inner passage 216, as shown by the dashed airflow line 218. In some examples, HP shaft 126 includes multiple openings spaced apart and arranged circumferentially around HP shaft 126. This high-pressure air is sometimes referred to as “bleed air” because it is “discharged” from HP compressor 116. Inner passage 216 is fluidly connected to HP turbine 120 via one or more channels, passages, and / or pipes. Therefore, bleed air guided through opening 214 and into inner passage 216 is directed to HP turbine 120. Figure 1 Therefore, opening 214 receives airflow from passage 202 for cooling HP turbine 120. Figure 1 Air helps cool the HP turbine 120 and thus improves the efficiency of the gas turbine engine 106. Typically, the airflow 218 exiting the first stage 152a of the stator blades 152 flows radially inward and enters the opening 214. In the illustrated example, the panel 210 has a rounded or covered downstream edge 220 designed to help direct the airflow 218 towards the opening 214. However, as shown by the airflow path 218 in Figure 2, air tends to circulate in the area between the inner shroud 204 and the HP shaft 126. This reduces the bleed-out capacity of the HP shaft 126. In some cases, if the pressure in the inner passage 216 is not sufficient, air may flow backward, i.e., return through the opening 214 and enter the passage 202 of the HP compressor 116. This significantly reduces or affects the cooling operation of the HP turbine 120.

[0029] This article discloses an example device for increasing airflow toward opening 214 to improve emission capacity. For example, Figure 3 An example of a spoon 300 constructed according to the teachings of this disclosure is shown. Specifically, Figure 3 An example removal scoop 300 is shown implemented in conjunction with the inner shroud 204 of the HP compressor 116. The removal scoop 300 is located on the downstream side of the inner shroud 204. The removal scoop 300 can be considered as part of the inner shroud 204 or a separate component attached to the inner shroud 204. The removal scoop 300 is circular or annular and surrounds the HP shaft 126 with the inner shroud 204. Figure 3 In the example shown, the spoon 300 is attached to and / or integrally formed with the panel 210.

[0030] exist Figure 3 In the example shown, the scoop 300 includes an upstream wall 302 and a downstream wall 304 spaced apart from the upstream wall 302, such that a channel 306 is formed between the upstream wall 302 and the downstream wall 304. The channel 306 guides the airflow exiting the first stage 152a of the stator blades 152 radially inward toward the opening 214 and into the inner passage 216, as shown by the dashed airflow path 308. Figure 3 As shown, the shape of the channel 306 helps to direct airflow towards the opening 214 in a smoother, more laminar manner. This reduces (e.g., minimizes) or restricts circulation in the region between the inner shroud 204 and the HP shaft 126, thereby improving airflow into the opening 214. This increases or improves the air intake capacity of the HP shaft 126.

[0031] In some examples, such as Figure 3 As shown, the take-out spoon 300 includes guide vanes 310. Guide vanes 310 are disposed in a channel 306 between the upstream wall 302 and the downstream wall 304. Guide vanes 310 facilitate further laminar radial inward guidance of airflow towards the opening 214. In this example, guide vanes 310 have an airfoil cross-section. In some examples, this helps reduce tip loss. In other examples, guide vanes 310 may have different cross-sectional shapes (e.g., straight, triangular, elliptical, etc.). In this example, guide vanes 310 are disposed at the center of the channel and are equidistant from the upstream wall 302 and the downstream wall 304. In other examples, guide vanes 310 may be closer to or further away from the upstream wall 302 and / or the downstream wall 304. Guide vanes 310 divide the channel 306 into two sub-channels. In other examples, the take-out spoon 300 may include more than one guide vane (e.g., two, three, four, etc.) dividing the channel 306 into more sub-channels. In other examples, the scoop 300 may not include any guide vanes. Conversely, in some examples, the channel 306 may be empty.

[0032] In the example shown, the spoon removal 300 includes a stator stop 312 (e.g., a flange) extending from the downstream wall 304. The stator stop 312 extends axially downstream from the downstream wall 304. Figure 3 (From center to right). The stator stop 312 may be integrally formed with the downstream wall 304. In the example shown, the HP shaft 126 has a root or hub 314. The rotor blades 154 of the second stage 154b are coupled to the HP shaft 126 at the hub 314. The hub 314 is located downstream of the inner shroud 204. In the example shown, the hub 314 includes a rotor stop 316 (e.g., an arm or flange). The rotor stop 316 extends axially upstream of the hub 314 (from center to right). Figure 3 (From center to left) and radially outward ( Figure 3 Extending upwards (from center). Thus, the stator blocking member 312 and the rotor blocking member 316 overlap in the radial direction (R). For example... Figure 3 As shown, a gap 318 is formed between the stator barrier 312 and the rotor barrier 316. The gap 318 can be relatively small. However, the stator barrier 312 and the rotor barrier 316 do not contact each other because the hub 314 rotates together with the rotor blade 154, but the scoop 300 is stationary with the stator blade 152. The configuration of the stator barrier 312 and the rotor barrier 316 can be referred to as flow barriers. This configuration of the stator barrier 312 and the rotor barrier 316 prevents the airflow 308 from circulating radially outward away from the opening 214, thus helping to improve the airflow orientation towards the opening 214.

[0033] Figure 4 It is along Figure 3 The cross-sectional view taken by line BB. Figure 4 Multiple stator blades 152 are shown. The stator blades 152 are connected to the panel 210 of the inner shroud 204. The scoop 300 is positioned along the downstream side of the panel 210 of the inner shroud 204. Figure 5 This is a perspective view of a portion of panel 210 and the removal spoon 300. They will be described together below. Figure 4 and Figure 5 .

[0034] exist Figure 4 and Figure 5 In the illustrated example, the upstream wall 302 of the scoop 300 is an extension or portion of the panel 210. For example, the downstream side of the panel 210 is radially inwardly curved, forming the upstream wall 302 of the scoop 300. Therefore, in some examples, the panel 210 and the upstream wall 302 are integrally formed as a single, single part or component. As mentioned above, in some examples, the panel 210 is a sheet metal panel. The downstream wall 304 is spaced apart from the upstream wall 302, forming a channel 306. The guide vane 310 is located in the channel 306 between the upstream wall 302 and the downstream wall 304. Figure 4 and Figure 5As shown, the upstream wall 302, the downstream wall 304, and the guide vane 310 are parallel to each other and spaced apart from each other.

[0035] exist Figure 4 and Figure 5 In the example shown, the extraction spoon 300 includes a rib 400a (which may also be referred to as a web) extending between the upstream wall 302 and the downstream wall 304. The rib 400a provides stiffness and rigidity to the extraction spoon 300. The rib 400a connects the upstream wall 302, the downstream wall 304, and the guide vane 310. The rib 400a also supports the guide vane 310 axially downstream of the downstream wall 304 and the upstream wall 302. In some examples, the extraction spoon 300 includes multiple ribs. For example, as... Figure 4 As shown, additional ribs 400b and 400c are illustrated. The scoop 300 may include any number of ribs (e.g., four, five, etc.). In some examples, ribs 400a-400c are spaced apart at specific intervals (e.g., every 10 cm, every 50 cm, etc.). Ribs 400a-400c divide the channel 306 into channel portions or segments 306a-306c between adjacent ribs in ribs 400a-400c. Figure 4 In some examples, the upstream wall 302, downstream wall 304, guide vane 310, and ribs 400a-400c are integrally formed (e.g., constructed as a monolithic structure). In some examples, the panel 210 and the extraction scoop 300 are integrally formed. For example, the panel 210, upstream wall 302, downstream wall 304, guide vane 310, and ribs 400a-400c may be integrally formed. In other examples, one or more of the panel 210, upstream wall 302, downstream wall 304, guide vane 310, and ribs 400a-400c may be formed as separate components joined (e.g., via welding, via fasteners, etc.) to adjacent structures. In some examples, the panel 210 and the extraction scoop 300 are manufactured by one or more manufacturing processes (e.g., stamping, extrusion, machining, and / or any other forming or alternative manufacturing process). Additionally or alternatively, the panel and / or extraction scoop 300 may be manufactured by additive manufacturing (sometimes referred to as 3D printing).

[0036] exist Figure 4 and Figure 5In the illustrated example, panel 210 includes a plurality of recesses 402 (which may also be referred to as extraction scoops) formed in the top surface of panel 210. The recesses 402 are disposed along the downstream edge 220 of panel 210. The recesses 402 are spaced apart from each other, and each of the recesses 402 is aligned with a corresponding channel segment in channel segments 306a-306c. The recesses 402 guide airflow into the channel 306. Specifically, airflow exiting stator blade 152 follows the recesses 402 and enters the channel 306. This provides a smoother transition for the airflow to bend radially inward. Therefore, the recesses 402 facilitate improved airflow entry into the channel 306 and thus into the opening 214 for bleed pressure. However, in other examples, panel 210 may not include any recesses.

[0037] While in some examples the bleed air is used to cool the HP turbine 120, in other examples it can be used to cool the LP turbine 122. Additionally or alternatively, the bleed air can be used for various other purposes in the turbofan engine 100 and / or the aircraft. For example, the bleed air can be used to pressurize certain seals in the gas turbine engine 106, which helps maintain tighter fits and tolerances. Furthermore, if the turbofan engine 100 is used on an aircraft, the bleed air can be used to power and / or provide a constant air supply to one or more systems, such as an environmental control system (ECS) (which provides pressurized and temperature-controlled air to the cabin), a wing anti-icing system, and / or an engine anti-icing system. Moreover, while the example removal scoop 300 is described in conjunction with the HP compressor 116, the example removal scoop 300 can be similarly implemented in one or more locations of the LP compressor 114.

[0038] Although Figure 3-5 The example scoop 300 shown includes a guide vane 310, but in other examples, the scoop 300 may not include any guide vane. For example, Figure 6 An example is shown where the scoop 300 in the channel 306 does not include the guide vane. Instead, the channel 306 is empty. The downstream wall 304 is still accessible via spaced ribs in ribs 400a-400c (in... Figure 6 (Referring to one of them) is connected to the upstream wall 302. The upstream wall 302 and the downstream wall 304 are smooth and radially curved inward. Therefore, even without guide vanes, the shape of the channel 306 (as defined between the first wall 302 and the second wall 304) can smoothly, laminarly guide the airflow 308 to the opening 214 (Figure 2 and 204). Figure 3 ).

[0039] Therefore, it can be understood that this document has disclosed examples of improved airflow into the exhaust opening in the compressor shaft. The examples disclosed herein improve exhaust pressure recovery and increase bleed air pressure. This improves reflux margin, such as the reflux margin of the HP turbine cooling supply. The examples disclosed herein can be added (modified) to existing gas turbine engines and / or added to newly manufactured gas turbine engines.

[0040] This document discloses example devices, systems, and articles for improving exhaust gas flow in gas turbine engines. Further examples and combinations thereof include the following:

[0041] Example 1 is a gas turbine engine comprising: a compressor including a housing defining a passage; a shaft extending through the passage and dromotivically connecting the compressor and a turbine of the gas turbine engine, the shaft having an opening for receiving airflow from the passage; an inner shroud; stator blades coupled to the housing and the inner shroud and extending radially between the housing and the inner shroud; and a take-out scoop disposed downstream of the inner shroud, the take-out scoop having a channel to guide the airflow radially inward toward the opening in the shaft.

[0042] Example 2 includes a gas turbine engine according to any of the preceding clauses, wherein the extraction scoop includes an upstream wall and a downstream wall spaced apart from the upstream wall, and the channel is defined between the upstream wall and the downstream wall.

[0043] Example 3 includes a gas turbine engine according to any of the preceding clauses, wherein the extraction scoop includes guide vanes disposed in the channel between the upstream wall and the downstream wall.

[0044] Example 4 includes a gas turbine engine according to any of the preceding clauses, wherein the guide vane has an airfoil cross section.

[0045] Example 5 includes a gas turbine engine according to any of the preceding clauses, wherein the extraction spoon includes a rib extending between the upstream wall and the downstream wall.

[0046] Example 6 includes a gas turbine engine according to any of the preceding clauses, wherein the rib supports the downstream wall and the guide vane, and is axially downstream of the upstream wall.

[0047] Example 7 includes a gas turbine engine according to any of the preceding clauses, wherein the upstream wall, the downstream wall, the guide vane, and the rib are integrally formed.

[0048] Example 8 includes a gas turbine engine according to any of the preceding clauses, wherein the inner shroud includes a panel, the stator blades are coupled to the panel, and the extraction scoop is coupled to the panel.

[0049] Example 9 includes a gas turbine engine according to any of the preceding clauses, wherein the panel includes a plurality of recesses along a downstream edge of the panel for guiding the airflow into the channel.

[0050] Example 10 includes a gas turbine engine according to any of the preceding clauses, wherein the extraction spoon includes a plurality of ribs dividing the channel into channel segments, and wherein each of the plurality of recesses is aligned with a corresponding channel segment in the channel segments.

[0051] Example 11 includes a gas turbine engine according to any of the foregoing clauses, wherein the panel is a sheet metal panel.

[0052] Example 12 includes a gas turbine engine according to any of the preceding clauses, wherein the extraction spoon includes a stator stop extending axially downstream from the downstream wall.

[0053] Example 13 includes a gas turbine engine according to any of the preceding clauses, further including rotor blades coupled to and extending radially outward from the shaft, the rotor blades being coupled to the shaft at a hub downstream of the inner shroud, the hub including an upstream axially extending rotor stop such that the stator stop and the rotor stop overlap in the radial direction.

[0054] Example 14 includes a gas turbine engine according to any of the preceding clauses, wherein a gap is formed between the stator stopper and the rotor stopper.

[0055] Example 15 includes a gas turbine engine according to any of the preceding clauses, wherein the compressor is a high-pressure compressor, and wherein the shaft is a high-pressure shaft.

[0056] Example 16 is an inner shroud comprising: a panel wherein radially inner ends of a plurality of stator blades are coupled to the panel; and a take-out scoop disposed on a downstream side of the panel, the take-out scoop including an upstream wall and a downstream wall spaced apart from the upstream wall such that a channel is formed between the upstream wall and the downstream wall, the channel being used to guide airflow in the compressor radially inward.

[0057] Example 17 includes an inner shroud according to any of the preceding clauses, wherein the extraction spoon includes guide vanes in the channel and spaced apart from the upstream wall and the downstream wall.

[0058] Example 18 includes an inner shroud as described in any of the preceding clauses, wherein the guide vane has an airfoil cross-section.

[0059] Example 19 includes an inner shroud as described in any of the preceding clauses, wherein the scoop includes a rib extending axially between the upstream wall and the downstream wall.

[0060] Example 20 includes an inner cover according to any of the foregoing clauses, wherein the upstream wall is integrally formed with the panel.

[0061] This written description uses examples to disclose this disclosure, including best practices, and also enables any person skilled in the art to practice this disclosure, including making and using any device or system and performing any combination of methods. The patent scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0062] While this disclosure has been described as having an exemplary design, it can be further modified within its scope. Therefore, this application is intended to cover any variations, uses, or adaptations of this disclosure using its general principles. Furthermore, this application is intended to cover known or customary practices within the field to which this disclosure pertains and that deviate from the scope of this disclosure from the limits of the appended claims.

Claims

1. A gas turbine engine, characterized in that, include: A compressor, the compressor including a housing defining a passageway; A shaft extending through the passage, the shaft drivingly connecting the compressor and turbine of the gas turbine engine, the shaft having an opening for receiving airflow from the passage; Inner protective cover; Stator blades, the stator blades being connected to the housing and the inner shroud, and extending radially between the housing and the inner shroud; as well as A scoop is provided downstream of the inner shroud. The scoop has a channel to guide the airflow radially inward toward the opening in the shaft. The scoop includes an upstream wall, a downstream wall spaced apart from the upstream wall, and a rib extending between the upstream wall and the downstream wall. The channel is defined between the upstream wall and the downstream wall. The rib extends cantilevered from the upstream wall, and the downstream wall extends cantilevered from the rear end of the rib, such that the rib axially supports the downstream wall downstream of the upstream wall.

2. The gas turbine engine according to claim 1, characterized in that, in, The extraction spoon includes guide vanes disposed in the channel between the upstream wall and the downstream wall.

3. The gas turbine engine according to claim 2, characterized in that, in, The guide vane has an airfoil cross section.

4. The gas turbine engine according to claim 2, characterized in that, in, The rib supports the downstream wall and the guide vane, and is axially downstream of the upstream wall.

5. The gas turbine engine according to claim 2, characterized in that, in, The upstream wall, the downstream wall, the guide vane, and the rib are integrally formed.

6. The gas turbine engine according to claim 1, characterized in that, in, The inner cover includes a panel, the stator impeller is connected to the panel, and the take-out spoon is connected to the panel.

7. The gas turbine engine according to claim 6, characterized in that, in, The panel includes a plurality of recesses along its downstream edge for guiding the airflow into the channel.

8. The gas turbine engine according to claim 7, characterized in that, in, The extraction spoon includes a plurality of ribs that divide the channel into channel segments, and each of the plurality of recesses is aligned with a corresponding channel segment in the channel segment.

9. The gas turbine engine according to claim 6, characterized in that, in, The panel is a metal sheet panel.

10. The gas turbine engine according to claim 1, characterized in that, in, The scoop includes a stator stop extending axially downstream from the downstream wall.

11. The gas turbine engine according to claim 10, characterized in that, It further includes rotor blades coupled to and extending radially outward from the shaft, the rotor blades being coupled to the shaft at a hub downstream of the inner shroud, the hub including an upstream axially extending rotor stop such that the stator stop and the rotor stop overlap in the radial direction.

12. The gas turbine engine according to claim 11, characterized in that, in, A gap is formed between the stator blocking member and the rotor blocking member.

13. The gas turbine engine according to claim 1, characterized in that, in, The compressor is a high-pressure compressor, and the shaft is a high-pressure shaft.

14. An inner casing for a gas turbine engine, the gas turbine engine including a compressor, characterized in that, The inner protective cover includes: A panel, wherein the radially inner ends of a plurality of stator blades are connected to the panel; and A scoop is provided on the downstream side of the panel. The scoop includes an upstream wall, a downstream wall spaced apart from the upstream wall, and a rib extending between the upstream wall and the downstream wall. The rib extends cantilevered from the upstream wall, and the downstream wall extends cantilevered from the rear end of the rib, such that the rib axially supports the downstream wall downstream of the upstream wall. A channel is formed between the upstream wall and the downstream wall to guide airflow in the compressor radially inward.

15. The inner protective cover according to claim 14, characterized in that, in, The extraction spoon includes guide vanes that are located in the channel and spaced apart from the upstream wall and the downstream wall.

16. The inner protective cover according to claim 15, characterized in that, in, The guide vane has an airfoil cross section.

17. The inner protective cover according to claim 14, characterized in that, in, The upstream wall is integrally formed with the panel.

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