CN120426132A - Compressor assembly for a gas turbine engine with multi-stage exhaust gas extraction - Google Patents

Abstract

The compressor assembly includes a compressor housing, a blade row within the compressor housing, first and second discharge cavities defined at first and second axial positions in the compressor housing, wherein the second axial position at least partially overlaps the first axial position in the axial direction, and first and second discharge ports defining first and second inlets leading to the first and second discharge cavities, respectively. The first discharge port extends from the first compressor stage to the first discharge cavity to direct compressed air from the first compressor stage through the first inlet and into the first discharge cavity. The second discharge port defines a second inlet leading to the second discharge cavity. The second discharge port extends from the second compressor stage to the second discharge cavity to direct compressed air from the second compressor stage through the second inlet and into the second discharge cavity.

Description

Compressor assembly for a gas turbine engine with multi-stage exhaust extraction

PRIORITY INFORMATION

The present application claims priority from the indian provisional patent application filed 2/2024 with serial number 202411007088.

Technical Field

The present disclosure relates generally to compressors in gas turbine engines, and more particularly, to compressor assemblies for gas turbine engines having exhaust gas extraction features.

Background

Gas turbine engines typically include a compressor, a combustor, and a turbine in serial flow communication. The turbine is mechanically coupled to the compressor, and these three components define a turbine core. The turbomachine core is operable in a known manner to generate a hot pressurized combustion gas stream to operate the engine and perform useful work, such as providing propulsive thrust or mechanical work.

In at least some known gas turbine engines, a portion of the high pressure air is extracted or bled from the compressor for other uses, such as turbine cooling, pressurized bearing oil pans, purge air, or aircraft environmental control. This "bleed" is discharged from the compressor using a bleed port (bleed scoop) located in a particular portion or stage of the compressor. The extracted air is then supplied to various locations where air is required through exhaust ports located around the periphery of the engine.

The compressor has a plurality of stages, each subsequent stage having a higher static pressure than the upstream stage, the last stage discharging air at a desired compressor discharge pressure ("CDP"). Each stage represents an increasing mechanical work input. During operation, exhaust gas is extracted from the compressor flow path for nacelle pressurization and turbine blade cooling.

Drawings

A full and enabling disclosure of the present disclosure, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:

FIG. 1 is a schematic cross-sectional view of a gas turbine engine including a compressor assembly according to an embodiment of the present disclosure;

FIG. 2 is a partial cross-sectional view of a portion of the compressor assembly of the engine of FIG. 1, particularly illustrating a flow extraction device of the compressor assembly;

FIG. 3 is a partial perspective view of an embodiment of a compliant joint of a flow extraction apparatus of a compressor assembly in accordance with an embodiment of the present disclosure;

FIG. 4 is a partial perspective view of an embodiment of a compressor assembly having a flow extraction device, particularly illustrating a flow extraction tube of the flow extraction device, according to an embodiment of the present disclosure;

FIG. 5A is a cross-sectional view of a flow extraction tube of a flow extraction device according to an embodiment of the disclosure;

FIG. 5B is a cross-sectional view of a flow extraction tube of a flow extraction device according to another embodiment of the present disclosure;

FIG. 5C is a cross-sectional view of a flow extraction tube of a flow extraction device according to yet another embodiment of the disclosure;

FIG. 6 is a schematic diagram of an embodiment of a compressor assembly having a flow extraction device, particularly illustrating compressed air from two stages of a compressor of an engine being discharged to the flow extraction device, in accordance with an embodiment of the present disclosure;

FIG. 7 is a circumferential view of the exhaust cavity arrangement of the flow extraction device of FIG. 6, particularly illustrating exhaust gas from two compressor stages being diverted to respective exhaust ports, in accordance with an embodiment of the disclosure;

FIG. 8 is a schematic diagram of an embodiment of a compressor assembly having a flow extraction device, particularly illustrating compressed air from three stages of a compressor of an engine being discharged to the flow extraction device, in accordance with an embodiment of the present disclosure, and

Fig. 9 is a circumferential view of the exhaust cavity arrangement of the flow extraction device of fig. 8, particularly illustrating exhaust gas from three compressor stages being diverted to respective exhaust ports, in accordance with an embodiment of the disclosure.

Detailed Description

Reference will now be made in detail to embodiments of the disclosure, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the disclosure, not limitation of the disclosure. Indeed, those skilled in the art will appreciate that various modifications and variations may be made to the disclosure without departing from the scope or spirit thereof. For instance, features illustrated or described as part of one embodiment, can be used with another embodiment to yield a still further embodiment. Accordingly, the present disclosure is intended to cover such modifications and variations as fall within the scope of the appended claims and their equivalents.

The term "exemplary" as used herein means "serving as an example, instance, or illustration. Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. Moreover, all embodiments described herein are to be considered as exemplary unless explicitly stated otherwise.

The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise.

For example, the term "at least one" in the context of "at least one of A, B and C" refers to a alone, B alone, C alone, or any combination of A, B and C.

The term "turbine" refers to a machine that includes one or more compressors, a heat generating section (e.g., a combustion section), and one or more turbines that collectively produce a torque output.

The term "gas turbine engine" refers to an engine that has a turbine as its full or partial power source. Example gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and the like, as well as hybrid versions of one or more of these engines.

The term "combustion section" refers to any heat addition system of a turbine. For example, the term combustion section may refer to a section that includes one or more of a deflagration combustion assembly, a rotary detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat addition assembly. In certain example embodiments, the combustion section may include an annular combustor, a can combustor, a tubular combustor, a Trapped Vortex Combustor (TVC), or other suitable combustion system, or a combination thereof.

The term "rotor" as used herein refers to any component in a rotary machine (e.g., a turbine engine) that rotates about a rotational axis. For example, the rotor may include a shaft or spool of a rotary machine (e.g., a turbine engine).

As used herein, the term "stator" refers to any component in a rotary machine (e.g., a turbine engine) having a configuration and arrangement that is coaxial with a rotor of the rotary machine. The stator may be disposed radially inward or radially outward of at least a portion of the rotor along a radial axis. Additionally, or alternatively, the stator may be axially disposed adjacent at least a portion of the rotor.

The terms "low" and "high" or their respective degrees of comparison (e.g., lower, higher, where applicable) when used in connection with a compressor, turbine, shaft or spool piece, etc., all refer to relative speeds within an engine unless otherwise indicated. For example, a "low turbine" or "low speed turbine" defines a component configured to operate at a lower rotational speed (e.g., a maximum allowable rotational speed) than a "high turbine" or "high speed turbine" of the engine.

The terms "forward" and "aft" refer to relative positions within the gas turbine engine or carrier and refer to the normal operational attitude of the gas turbine engine or carrier. For example, for a gas turbine engine, reference is made to a location closer to the engine inlet and then to a location closer to the engine nozzle or exhaust.

The terms "upstream" and "downstream" refer to the relative directions of fluid flow in a fluid channel. For example, "upstream" refers to the direction of fluid flow and "downstream" refers to the direction of fluid flow.

As used herein, the terms "axial" and "axially" refer to directions and orientations extending substantially parallel to a gas turbine engine centerline. Furthermore, the terms "radial" and "radially" refer to directions and orientations extending substantially perpendicular to a gas turbine engine centerline. Furthermore, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations extending in an arc about a gas turbine engine centerline.

Unless otherwise specified herein, the terms "coupled," "fixed," "attached to," and the like are intended to both direct and indirect coupling, fixing, or attaching via one or more intermediate components or features.

As used herein, the terms "first," "second," "third," and the like may be used interchangeably to distinguish one component from another and are not intended to represent the location or importance of the various components.

The term "adjacent" as used herein with respect to two walls and/or surfaces means that the two walls and/or surfaces are in contact with each other, or that the two walls and/or surfaces are separated by only one or more non-structural layers and that the two walls and/or surfaces are in series contacting relationship with the one or more non-structural layers (i.e., a first wall/surface contacts one or more non-structural layers and one or more non-structural layers contacts a second wall/surface).

Throughout the specification and claims, approximating language may be applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by one or more terms (e.g., "about," "approximately," and "substantially") is not limited to the precise value specified. In at least some cases, the approximating language may correspond to the precision of an instrument for measuring the value or the precision of a method or machine for constructing or manufacturing a part and/or system. For example, approximating language may refer to the remaining amount of 1%, 2%, 4%, 10%, 15%, or 20%. These approximate margins may be applied to individual values, to any or both of the endpoints of a defined numerical range, and/or to range margins between the endpoints.

Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other.

In many engines, exhaust gas is extracted from the compressor flow path for cabin pressurization and turbine blade cooling. Typically, the pressure requirements result in extraction of exhaust gas from adjacent stages to maintain a desired flow rate. The arrangement of the exhaust gas on adjacent stages results in packaging related challenges. Accordingly, the present disclosure is directed to a compressor assembly for multi-stage exhaust extraction that addresses packaging challenges without compromising exhaust pressure recovery. For example, in one embodiment, the present disclosure addresses packaging challenges by creating multiple chambers within a given exhaust chamber volume with minimal complexity. In certain embodiments, multiple exhaust extractions are achieved by nested exhaust arrangements in both the axial and circumferential segmented directions. In further embodiments, exhaust may be actively and alternately switched to meet various mission requirements. For example, in one embodiment, exhaust mass flow may be controlled by opening/closing one or more external valves via control logic based on mission requirements.

Referring now to the drawings, in which like numerals represent like elements throughout, FIG. 1 illustrates a cross-sectional view of a gas turbine engine embodiment, also referred to herein as an engine 10, which may incorporate various aspects of the disclosed technology. As shown, engine 10 has a fan 14, a booster 16, a high pressure compressor or "HPC"18, a combustor 20, a high pressure turbine or "HPT"22, and a low pressure turbine or "LPT"24 arranged in series flow relationship. In operation, pressurized air from the outlet 26 of the HPC 18 is mixed with fuel in the combustor 20 and ignited, thereby generating combustion gases. The HPT 22 extracts some work from these gases, and the HPT 22 drives the HPC 18 via the outer shaft 28. The combustion gases then flow into the low pressure turbine 24, and the low pressure turbine 24 drives the fan 14 and the supercharger 16 via the inner shaft 29.

HPC 18 includes a plurality of stages of blades, for example, a typical compressor may include 6-14 stages. In operation, the static air pressure is gradually increased through each subsequent compressor stage, with the last stage discharging air at a desired compressor discharge pressure ("CDP") for subsequent flow into combustor 20. Each compressor stage represents an increasing input of mechanical work. The illustrated example shows an axial stage, but the principles described herein are also applicable to centrifugal or shaft centrifugal compressors. It is also noted that air may be exhausted or extracted from any portion of HPC 18, or indeed from any portion of engine 10 upstream of the point where fuel is introduced into the air stream. The concepts described herein are particularly relevant to structures for extracting or exhausting air from an intermediate location that is located at a stage upstream of the outlet 26 of the HPC 18.

Referring now to FIG. 2, a cross-sectional view of a portion of HPC18 is shown incorporating an embodiment of a flow extraction apparatus 100 for multi-stage exhaust extraction from HPC 18. Specifically, as shown, fig. 2 shows only two compressor stages. For ease of description, one of the stages will be referred to as an "upstream stage" 30 and the other stage will be referred to as a "downstream stage" 32, with both the upstream and downstream stages 30, 32 being located upstream of the outlet 26 of the HPC 18.

The upstream stage 30 includes a first blade row 34 of circumferentially-spaced airfoil-shaped rotor blades 36 and a first stator row 40 of circumferentially-spaced stationary airfoil-shaped stator vanes 42, the first blade row 34 being mechanically coupled to the compressor rotor 38, which in turn is mechanically coupled to the outer shaft 28. The downstream stage 32 includes a second blade row 44 of circumferentially spaced airfoil-shaped rotor blades 36 and a second stator row 46 of circumferentially spaced stationary airfoil-shaped stator vanes 42.

HPC 18 is surrounded by a compressor casing 48 that supports stator vanes 42. The compressor housing 48 has a radially inner surface 50 and an opposite radially outer surface 52. Further, as shown, the compressor housing 48 includes a forward section 66 that terminates at its aft end in an annular, radially extending first flange 68. The compressor housing 48 also includes a rear section 70 that terminates at its forward end in an annular, radially extending second flange 72. Thus, as shown, the first and second flanges 68, 72 abut one another and are clamped together by a plurality of fasteners (e.g., by bolts 74) to form a bolted joint 76.

Still referring to fig. 2, the flow extraction device 100 utilizes a compressor housing 48, the compressor housing 48 including a first exhaust port 54 through the thickness of the compressor housing 48 and a second exhaust port 78 downstream of the first exhaust port 54. The first exhaust port 54 may extend in all or part of the circumference of the compressor housing 48. In the illustrated example, the first exhaust port 54 is a full 360 ° slot about the longitudinal axis 11.

In a particular embodiment, as shown, the first exhaust port 54 extends along a first slot axis 64, the first slot axis 64 being disposed at a non-parallel, non-perpendicular angle θ with respect to the longitudinal axis 11 of the engine 10. For example, the first slot axis 64 may be disposed at an angle greater than 0 ° and less than 90 ° relative to the longitudinal axis of the engine 10. More specifically, in certain embodiments, the angle θ is selected to reduce pressure losses by rotating the exhaust gas through a lower angle than prior art exhaust ports (disposed in a nearly radial orientation, e.g., 90 degrees from the longitudinal axis 11). This feature may be referred to as a "flat" or "low angle" vent. As used herein, the term "low angle" refers to an angle of about 65 ° or less. For example, the angle θ may be in the range of about 30 ° to about 65 °. In the illustrated example, the angle θ is about 30 °.

Further, as shown, in the embodiment of fig. 2, the flow extraction device 100 also includes a first discharge chamber 60 (or plenum) defined in part by the compressor housing 48. Further, as shown, the first exhaust chamber 60 is located at a first axial position A ₁ of the engine 10. Further, as shown, the flow extraction device 100 includes a second exhaust chamber 61 at a second axial location a ₂ that at least partially overlaps the first axial location a ₁ of the first exhaust chamber 60 in the axial direction a of the engine 10. Thus, as shown in the illustrated embodiment, the second exhaust chamber 61 is nested within the first exhaust chamber 60 (e.g., inside the first exhaust chamber 60).

Further, the first exhaust port 54 is defined by a wall 86. Further, as shown, the first exhaust port 54 defines a first inlet 56 that leads to a first exhaust chamber 60. Further, as shown, the second exhaust port 78 defines a second inlet 80 to the second exhaust chamber 61. Thus, during engine operation, a portion 57 of the compressed air from the first compressor stage of engine 10 passes through first inlet 56 and into first exhaust cavity 60. Further, as shown, a portion 59 of the compressed air from the second compressor stage of engine 10 passes through second inlet 80 and into second exhaust chamber 61. The air entering the first and second exhaust chambers 60, 61 may be redirected or routed as desired through appropriate plumbing, valves, etc. for various end uses.

More specifically, as shown in the illustrated embodiment, the flow extraction device 100 may further include at least one exhaust flow extraction tube 102 disposed with the outlet 82 of the second exhaust chamber 61. In such an embodiment, the exhaust flow extraction tube 102 is configured to convey the compressed air 104 in the second exhaust chamber 61 through the compressor housing 48 (as indicated by arrow 104) such that the compressed air 104 may be redirected or conveyed as desired for various end uses. More specifically, as shown, the exhaust flow extraction tube 102 generally defines a longitudinal axis 106, which may be disposed at an angle of about 90 ° relative to the longitudinal axis 11 of the engine 10.

Still referring to fig. 2, the flow extraction device 100 defines a length L extending from the first end 110 and the second end 112. Thus, as shown in the illustrated embodiment, the first end 110 is located within the second discharge chamber 61, while the second end 112 is located on the compressor housing 48. Further, as shown, at least a portion of the length L of the flow extraction device 100 extends through the first exhaust chamber 60. Further, in certain embodiments, the first and second exhaust chambers 60, 61 are fluidly separated from one another.

Further, as shown in fig. 2 and 3, the exhaust flow extraction tube 102 is supported by one or more flexible/compliant couplings (e.g., nipple (spoolie), slip joint, or the like) to allow free thermal extension thereof. As used herein, a nipple generally refers to a flexible joint that allows rotation about the joint. More specifically, as shown, the exhaust flow extraction tube 102 is supported by a compliant joint 108, the compliant joint 108 being disposed on the compressor housing 48 at a second end 112 of the exhaust flow extraction tube 102. As used herein, a flexible or compliant joint generally refers to a joint that allows for relative movement of the connecting members.

In a further embodiment, as shown, the first end 110 of the exhaust flow extraction tube 102 extends within a recess 114 defined within the second exhaust cavity 61. Thus, in such embodiments, the first end 110 of the exhaust flow extraction tube 102 is capable of sliding within the groove 114 to allow radial movement of the exhaust flow extraction tube 102. In certain embodiments, as shown, the groove 114 may also include at least one flange 116 for restricting movement of the exhaust flow extraction tube 102 within the groove 114.

While fig. 2 and 3 show a single exhaust flow extraction tube 102 for purposes of illustration, it is to be understood that the flow extraction apparatus 100 described herein may also include a plurality of discrete exhaust flow extraction tubes 102, with the discrete exhaust flow extraction tubes 102 being disposed circumferentially about the HPC 18, for example, as shown in fig. 4. In such embodiments, the discrete exhaust flow extraction pipes 102 may be evenly or unevenly circumferentially spaced about the HPC 18 as desired.

Referring now to fig. 5A-5C, it should be appreciated that the exhaust flow extraction tube 102 may have any suitable cross-sectional shape. More specifically, in embodiments, the cross-sectional shape of exhaust flow extraction tube 102 may be circular 118 (FIG. 5A), stadium 120 (FIG. 5B), or oval 122 (FIG. 5C), as well as any other suitable shape. Further, the cross-sectional shape of the exhaust flow extraction tube 102 may be oriented at any suitable angle relative to the longitudinal axis 11 of the engine 10.

Referring now to FIGS. 6-9, various schematic diagrams of further embodiments of a stream extraction apparatus for multi-stage exhaust stream extraction from the HPC 18 are shown. More specifically, FIG. 6 illustrates a schematic diagram of an embodiment of a flow extraction apparatus 200 according to the present disclosure, wherein multi-stage exhaust extraction from HPC 18 is enabled by a circumferential staging direction. Specifically, FIG. 6 shows a cross-sectional view of a portion of HPC 18, and an expanded view of flow extraction apparatus 200 looking radially inward to illustrate exhaust gas flows from two compressor stages, in accordance with an embodiment of the disclosure. For example, as shown in FIG. 6, the continuous exhaust slot 207 is interrupted by a segmented plenum fed by exhaust ports 206, which may include back-to-back exhaust on the HPC 18 (e.g., from the third and fourth stages), the plenums being separated (e.g., tangentially separated) by an axial wall. However, in other embodiments, the semi-continuous tank 207 may be replaced by a separate exhaust port.

Furthermore, fig. 7 shows a circumferential view of the exhaust cavity arrangement of the flow extraction device 200 of fig. 6, in particular showing that the exhaust gases from the two compressor stages are diverted to the respective exhaust ports. More specifically, as shown, flow extraction device 200 includes a first exhaust chamber 202 located at a first axial position A ₁ of engine 10. In addition, as shown, the flow extraction device 200 includes a second exhaust chamber 204 located at a second axial location a ₂ that at least partially overlaps the first axial location a ₁ of the first exhaust chamber 202 in the axial direction a of the engine 10.

Further, as shown, the flow extraction device 200 includes a first exhaust port 206, the first exhaust port 206 defining a first inlet 208 to the first exhaust cavity 202. Further, as shown, the flow extraction device 200 includes a second exhaust port 210, the second exhaust port 210 defining a second inlet 212 to the second exhaust cavity 204. Thus, during engine operation, a portion of compressed air 214 from a first compressor stage (e.g., third stage; S3) of engine 10 passes through first inlet 208 and into first exhaust cavity 202. Further, as shown, a portion of the compressed air 216 from the second compressor stage (e.g., fourth stage; S4) of the engine 10 passes through the second inlet 80 and into the second exhaust plenum 204.

More specifically, as shown in fig. 7, the first exhaust chamber 202 is located at a first circumferential position C ₁ and the second exhaust chamber 204 is located at a second circumferential position C ₂. Further, as shown in fig. 7, the first and second circumferential positions C ₁ and C ₂ are arranged in an alternating pattern. Accordingly, the compressed air 214, 216 entering the first and second exhaust chambers 202, 204 may be redirected or routed through the first and second exhaust ports 218, 220, respectively, as desired, via appropriate piping, valves, etc., for various end uses.

Similarly, referring now to fig. 8 and 9, a schematic diagram of another embodiment of a stream extraction apparatus 200 is shown. More specifically, FIG. 8 illustrates a schematic diagram of an embodiment of a flow extraction apparatus 200 according to the present disclosure, wherein multi-stage exhaust extraction from the HPC 18 is enabled by a circumferential staging direction. Specifically, FIG. 8 illustrates a cross-sectional view of a portion of HPC 18, and an expanded view of flow extraction apparatus 200 looking radially inward to illustrate exhaust gas flow from three compressor stages, in accordance with an embodiment of the disclosure. Similar to the embodiment shown in fig. 6, another configuration of a flow extraction device 200 is shown in fig. 8, wherein one or more continuous exhaust slots 207 are shown with back-to-back exhaust (e.g., from the second, third, and fourth stages) with the plenums fed by exhaust ports 206 and 222 interrupted. Further, in fig. 6 and 8, the second exhaust port 210 is shown generally as an oval with a circle in the middle to represent a VSV stem and a cowling structure around it to allow passage of plenum air between cowls (e.g., oval). Furthermore, fig. 9 shows a circumferential view of the exhaust cavity arrangement of the flow extraction device 200 of fig. 8, in particular showing that the exhaust gases from the three compressor stages are diverted to the respective exhaust ports.

Thus, the flow extraction apparatus 200 in fig. 8 and 9 is similar to the embodiment shown in fig. 6 and 7, but adds a third exhaust port 222 at a third circumferential position C ₃ of a third compressor stage (e.g., second stage, S2). In such an embodiment, as particularly shown in fig. 9, the first, second and third circumferential positions C ₁、C₂、C₃ are arranged in an alternating pattern. Thus, the flow extraction device 200 in fig. 8 and 9 also provides multi-exhaust extraction by a nested exhaust arrangement in the circumferential direction. Accordingly, the compressed air 214, 216, 217 (i.e., exhaust gas) entering the first, second, and third exhaust chambers 202, 204, 205 may be redirected or routed through the first, second, and third exhaust ports 218, 220, 221, respectively, as desired, via appropriate piping, valves, etc., for various end uses.

Thus, the embodiments shown in FIGS. 8 and 9 provide high pressure compressor cascade bleed extraction on multiple stages of HPC 18. Further, scoop-type exhaust extraction from the trailing edges of the second and third stages may be accomplished by exhaust stream extraction pipes.

The various embodiments described herein provide many advantages not present in the prior art. In particular, the flow extraction device of the present disclosure does not require an increase in the axial length of the compressor. Furthermore, the flow extraction device of the present disclosure maintains negligible leakage to adjacent chambers. In addition, by not increasing the overall size requirements of the compressor, the bleed recovery is improved and the bleed port packaging challenges at each stage are improved.

Further aspects are provided by the subject matter of the following clauses:

A compressor assembly for an engine for multi-stage exhaust extraction includes an annular compressor housing, a row of blades mounted for rotation about a longitudinal axis within the compressor housing, a first exhaust plenum defined at a first axial location in the annular compressor housing of the engine, a second exhaust plenum defined at a second axial location in the annular compressor housing that at least partially overlaps the first axial location of the first exhaust plenum in an axial direction of the engine, a first exhaust plenum defining a first inlet to the first exhaust plenum, the first exhaust plenum extending from a first compression stage of the engine to the first exhaust plenum to direct compressed air from the first compression stage through the first inlet to the first exhaust plenum, and a second exhaust plenum downstream of the first exhaust plenum defining a second inlet to the second exhaust plenum, the second exhaust plenum extending from the second compressor stage of the engine to the second exhaust plenum to direct compressed air from the second compressor stage through the second inlet to the second exhaust plenum.

The compressor assembly of any preceding claim, wherein the second discharge chamber is nested within the first discharge chamber.

The compressor assembly of any preceding clause, further comprising at least one exhaust flow extraction tube disposed with the outlet of the second exhaust chamber, the exhaust flow extraction tube configured to convey compressed air in the second exhaust chamber through an annular outer wall of the compressor assembly.

The compressor assembly of any preceding claim, wherein the exhaust flow extraction tube defines a longitudinal axis disposed at an angle of about 90 ° relative to a longitudinal axis of the engine.

The compressor assembly of any preceding claim, wherein the exhaust flow extraction tube defines a length extending from a first end and a second end, wherein the first end is positioned within the second exhaust chamber, the second end is positioned at an annular outer wall of the compressor assembly, and at least a portion of the length extends through the first exhaust chamber.

The compressor assembly of any preceding clause, further comprising a compliant joint disposed at the second end of the exhaust extraction pipe on the annular outer wall of the compressor assembly.

The compressor assembly of any preceding clause, wherein the first end extends within a groove defined within the second exhaust cavity, and wherein the first end of the exhaust flow extraction tube is slidable within the groove to allow radial movement of the exhaust flow extraction tube.

The compressor assembly of any preceding clause, further comprising a plurality of discrete exhaust flow extraction tubes circumferentially arranged around the compressor assembly.

The compressor assembly of any preceding claim, wherein the cross-sectional shape of the exhaust extraction tube is one of circular, stadium-shaped, or oval.

The compressor assembly of any preceding claim, wherein the first discharge port is positioned at a first circumferential position and the second discharge port is positioned at a second circumferential position, and wherein the first and second circumferential positions are arranged in an alternating pattern.

The compressor assembly of any preceding claim, further comprising a third discharge port positioned at a third circumferential location, wherein the first, second, and third circumferential locations are arranged in an alternating pattern.

The compressor assembly of any preceding clause, wherein the first discharge port is defined by an inner sidewall and an outer sidewall of the annular compressor housing, and wherein the first discharge port defines a first slot axis disposed at an angle greater than 0 ° and less than 90 ° relative to a longitudinal axis of the engine.

The compressor assembly of any preceding claim, wherein the first and second discharge chambers are fluidly separated.

A gas turbine engine includes a compressor assembly, a combustor, and a turbine arranged in a serial relationship, wherein the compressor assembly includes an annular compressor housing, a stator row disposed within the compressor housing, a row of blades mounted for rotation within the annular compressor housing about a longitudinal axis, a first exhaust plenum defined at a first axial location in the annular compressor housing of the engine, a second exhaust plenum defined at a second axial location in the annular compressor housing that at least partially overlaps the first axial location of the first exhaust plenum in an axial direction of the engine, a first exhaust plenum defining a first inlet to the first exhaust plenum that extends from a first compression stage of the engine to the first exhaust plenum to direct compressed air from the first compression stage through the first inlet and into the first exhaust plenum, and a second exhaust plenum downstream of the first exhaust plenum defining a second inlet to the second exhaust plenum that extends from the second compressor stage of the engine to the second exhaust plenum to direct compressed air from the second compressor stage through the second inlet and into the second exhaust plenum.

The gas turbine engine of any preceding clause, wherein the second exhaust cavity is nested within the first exhaust cavity.

The gas turbine engine of any preceding clause, further comprising at least one exhaust flow extraction duct disposed with the outlet of the second exhaust cavity, the exhaust flow extraction duct configured to convey compressed air in the second exhaust cavity through an annular outer wall of the compressor assembly.

The gas turbine engine of any preceding clause, further comprising a compliant joint disposed on an annular outer wall of the compressor assembly at an outlet of the exhaust extraction duct.

The gas turbine engine of any preceding clause, wherein the exhaust flow extraction tube extends from a first end positioned within the second exhaust cavity and a second end positioned at the annular outer wall of the compressor assembly, the first end extending within a groove defined within the second exhaust cavity, and wherein the first end of the exhaust flow extraction tube is slidable within the groove to allow radial movement of the exhaust flow extraction tube.

The gas turbine engine of any preceding clause, further comprising a plurality of discrete exhaust flow extraction pipes circumferentially arranged around the compressor assembly.

The gas turbine engine of any preceding clause, wherein the first exhaust port is positioned at a first circumferential position and the second exhaust port is positioned at a second circumferential position, and wherein the first and second circumferential positions are arranged in an alternating pattern.

This written description uses examples to disclose the technology, including the best mode, and also to enable any person skilled in the art to practice the technology, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the technology is defined by the claims, and may include other examples that occur to those skilled in the art. These other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.

Claims (10)

1. A compressor assembly for an engine with multi-stage exhaust gas extraction, characterized in that the compressor assembly comprises: annular compressor housing; a blade row mounted for rotation about a longitudinal axis within the annular compressor housing; a first exhaust cavity defined at a first axial position in the annular compressor housing of the engine; a second discharge cavity defined at a second axial position in the annular compressor housing, the second axial position at least partially overlapping the first axial position of the first discharge cavity in the axial direction of the engine; a first exhaust port defining a first inlet to the first exhaust cavity, the first exhaust port extending from a first compressor stage of the engine to the first exhaust cavity to direct compressed air from the first compressor stage through the first inlet and into the first exhaust cavity; and a second exhaust port located downstream of the first exhaust port, the second exhaust port defining a second inlet to the second exhaust cavity, the second exhaust port extending from the second compressor stage of the engine to the second exhaust cavity to direct compressed air from the second compressor stage through the second inlet and into the second exhaust cavity. 2 . The compressor assembly of claim 1 , wherein the second discharge chamber is nested within the first discharge chamber. 3. The compressor assembly according to claim 2, further comprising an exhaust flow extraction pipe arranged together with the outlet of the second exhaust cavity, the exhaust flow extraction pipe being configured to transport the compressed air in the second exhaust cavity through the annular outer wall of the compressor assembly. 4 . The compressor assembly of claim 3 , wherein the exhaust gas flow extraction tube defines a longitudinal axis disposed at an angle of approximately 90° relative to the longitudinal axis of the engine. 5. The compressor assembly of claim 4 , wherein the exhaust flow extraction tube defines a length extending from a first end and a second end, wherein the first end is positioned within the second exhaust cavity, the second end is positioned at the annular outer wall of the compressor assembly, and at least a portion of the length extends through the first exhaust cavity. 6 . The compressor assembly of claim 5 , further comprising a compliant joint disposed at the second end of the exhaust gas flow extraction tube on the annular outer wall of the compressor assembly. 7. The compressor assembly of claim 5, wherein the first end extends within a groove defined within the second exhaust cavity, and wherein the first end of the exhaust flow extraction tube is slidable within the groove to allow radial movement of the exhaust flow extraction tube. 8 . The compressor assembly of claim 3 , further comprising a plurality of discrete exhaust flow extraction tubes arranged circumferentially around the compressor assembly. 9. The compressor assembly of claim 3, wherein the cross-sectional shape of the exhaust gas flow extraction tube is one of a circular, a stadium, or an elliptical shape. 10. The compressor assembly of claim 1, wherein the first discharge port is positioned at a first circumferential location and the second discharge port is positioned at a second circumferential location, and wherein the first circumferential location and the second circumferential location are arranged in an alternating pattern.