Compressor bleed air supercharging system
By installing an impeller tube and an air flow guide in the air bleed chamber, the pressure drop caused by eddy currents during rotor shaft rotation is solved, the air bleed pressure is increased, and the cooling or heating efficiency is enhanced.
Patent Information
- Application Number
- CN202511732095.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2024-11-25
- Filing Date
- 2025-11-24
- Publication Date
- 2026-05-26
Smart Images
Figure CN122082874A_ABST
Abstract
Description
Technical Field
[0001] This disclosure relates to compressors for gas turbine engines. More specifically, this disclosure relates to a bleed air booster system for a compressor in a gas turbine engine. Background Technology
[0002] Air flowing through the main flow path of a gas turbine engine is pressurized in a compressor and mixed with fuel in a combustor to produce hot combustion gases, which flow downstream through the turbine stage. A portion of this air, commonly referred to as "bleed air," can be discharged from the compressor to cool or heat various sections or components of the gas turbine engine. Bleed air can be guided from the main flow path through discrete orifices defined in a drive arm connected to axially adjacent compressor rotor discs. This bleed air chamber is defined between axially adjacent compressor rotor discs and is at least partially defined by the rotor shaft. As the bleed air enters the bleed air chamber, the rotation of the rotor shaft and rotor discs causes vortices to form in the direction of rotor shaft rotation, resulting in a pressure drop within the bleed air chamber and consequently a loss of bleed air cooling or heating efficiency. Attached Figure Description
[0003] The specification with reference to the accompanying drawings sets forth a complete and enabling disclosure for those skilled in the art, including its best mode, wherein:
[0004] Figure 1 This is a schematic cross-sectional view of a gas turbine engine according to an exemplary aspect of this disclosure.
[0005] Figure 2 This is based on exemplary embodiments of the present disclosure. Figure 1 An enlarged side cross-sectional view of a portion of the gas turbine engine shown, including parts that can be incorporated into... Figure 1 An exemplary high-pressure compressor in the turbine shown.
[0006] Figure 3 As per exemplary embodiments of this disclosure Figure 2 An enlarged detailed cross-sectional view of a portion of the high-pressure compressor shown.
[0007] Figure 4 According to one embodiment of this disclosure, such as Figure 3 The impeller tube shown is a side view.
[0008] Figure 5 According to embodiments of this disclosure, such as Figure 4 A perspective view of a portion of the impeller tube shown, including the second end, the outlet, and the bleed air flow guide.
[0009] Figure 6 It is a top view of the first end, especially Figure 4 The inlet of the impeller tube shown.
[0010] Figure 7 According to an embodiment of this disclosure Figure 4 The cross-sectional top view of the impeller tube taken by section line 7-7 is shown.
[0011] Figure 8 This is based on exemplary embodiments of the present disclosure. Figure 4 The bottom view of the impeller tube is shown.
[0012] Figure 9 According to embodiments of this disclosure, such as Figure 4 The side view shown is of a portion of the impeller tube, including the second end, the outlet, and the bleed air flow guide.
[0013] Figure 10 As per exemplary embodiments of this disclosure Figure 3 The bottom view of the impeller tube is shown.
[0014] Figure 11 According to another embodiment of this disclosure, such as Figure 3 The image shows a cross-sectional side view of the impeller tube.
[0015] Figure 12 Another embodiment of the present disclosure is provided, such as Figure 3 The image shows a cross-sectional side view of the impeller tube. Detailed Implementation
[0016] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. Detailed descriptions use numbers and letters to designate features in the drawings. The same or similar designations in the drawings and descriptions have been used to designate the same or similar parts in this disclosure.
[0017] As used herein, the term “exemplary” means “as an example, instance, or illustration.” Any implementation described herein as “exemplary” is not necessarily to be construed as superior to or advantageous to other implementations.
[0018] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and do not imply the position or importance of the components.
[0019] 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.
[0020] Unless otherwise stated herein, the terms “connection,” “fixed,” “attached to,” etc., refer to direct connection, fixation, or attachment, as well as indirect connection, fixation, or attachment via one or more intermediate components or features.
[0021] Unless the context clearly indicates otherwise, the singular forms “a,” “one,” and “the” include plural references.
[0022] The approximate language used throughout the specification and claims is applied to modify any quantitative expression that may allow for variation without altering its underlying function. Therefore, values modified by one or more terms such as “about,” “approximately,” and “substantially” are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of 10%.
[0023] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and specifically to the normal operating posture of the gas turbine engine or vehicle. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.
[0024] The following disclosure relates to a compressor bleed air booster system for a gas turbine engine. Compressor exhaust in the later stage is achieved through discrete orifices on a drive arm, which create vortices in the bleed air as it flows into bleed air chambers defined between adjacent rotor discs. As air exits those orifices in the drive arm, the pressure within the bleed air pressure chambers begins to decrease due to conservation of angular momentum, thereby reducing the pressure of the bleed air supplied to the turbine section for cooling. The bleed air booster system provided herein includes bleed air flow guides located at the impeller tube outlet within the bleed air chambers to allow more bleed air and less drag in the circumferential (rotational) direction of the rotor shaft, thereby reducing pressure drop and increasing the pressure of the bleed air supplied to the turbine or other components of the gas turbine engine.
[0025] Now refer to the attached diagram, Figure 1 This is a schematic diagram of an exemplary gas turbine engine 10 according to various embodiments of the present disclosure. Figure 1As shown, the gas turbine engine 10 generally defines an axial direction (A) extending parallel to the longitudinal centerline 12 of the gas turbine engine 10 and a radial direction (R) extending perpendicular to the longitudinal centerline 12 and the axial direction A. The gas turbine engine 10 includes a turbine 14. The turbine 14 generally includes, in series flow sequence, a fan assembly 16, a turbocharger or low-pressure compressor 18, a high-pressure compressor 20, a combustor 22, a high-pressure turbine 24, and a low-pressure turbine 26. The fan assembly 16 includes an array of fan blades 28 extending radially outward from a fan rotor disk 30. The gas turbine engine 10 includes an inlet end 32 and an exhaust end or outlet end 34. The low-pressure compressor 18, the high-pressure compressor 20, the combustor 22, the high-pressure turbine 24, and the low-pressure turbine 26 at least partially define a main flow path 36 through the gas turbine engine 10, and more specifically, through the turbine 14.
[0026] In operation, air flows through fan assembly 16. A portion of the air is directed through low-pressure compressor 18 and compressed therein. The compressed air is then supplied to high-pressure compressor 20 for further compression. The relatively highly compressed air is delivered to combustor 22, where it mixes with fuel and burns to produce combustion gases. The combustion gases from combustor 22 ( Figure 1 (Not shown) drives the high-pressure turbine 24 and the low-pressure turbine 26, such that the high-pressure turbine 24 drives the high-pressure compressor 20 through the high-pressure rotor shaft 38, and the low-pressure turbine 18 drives the low-pressure compressor 18 and the fan assembly 16 through the low-pressure shaft 40.
[0027] It should be understood that Figure 1 The gas turbine engine 10 shown is provided as an example only, and in other exemplary embodiments, the gas turbine engine 10 may have other configurations. For example, although the gas turbine engine 10 shown is configured as a ducted high-bypass gas turbine engine (e.g., including the outer nacelle 42), in other embodiments, the gas turbine engine 10 may be a ductless or non-ducted gas turbine engine, such that the fan assembly 16 is a ductless fan. It should also be understood that, in other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable gas turbine engine. For example, in other exemplary embodiments, aspects of this disclosure may (where appropriate) be incorporated into, for example, a turboprop gas turbine engine, a turboshaft gas turbine engine, or a turbojet gas turbine engine.
[0028] Figure 2 Exemplary embodiments according to this disclosure are provided. Figure 1 An enlarged side cross-sectional view of a portion of the gas turbine engine 10 shown, including parts that can be incorporated into... Figure 1 An exemplary high-pressure compressor 20 in the turbine 14. (e.g.) Figure 2As shown, the high-pressure compressor 20 includes multiple compressor stages (S). Although Figure 2 The diagram shows nine compressor stages S, but it should be understood that the high-pressure compressor 20 may include any number of compressor stages S greater than two. 1+n .
[0029] like Figure 2 As shown, each compressor stage S includes a row of rotor blades 44 attached to a rotor disk 46. During operation of the gas turbine engine 10, each rotor disk 46 is coupled to and rotates together with the high-pressure rotor shaft 38 about a longitudinal centerline 12. The rotor disk 46 and rotor blades 44 can be integrally formed, referred to as an integral bladed disk, or they can be connected via a dovetail joint as shown. Each compressor stage S also includes a row of stator blades 48. Each row of stator blades 48 is positioned relative to the axial direction A between two rows of axially adjacent rotor blades 44. The rotor disks 46 are connected or coupled together via a drive arm 50 or other connecting device.
[0030] The bleed chamber 52 is defined between one or more rotor disks 46 of stage S. The bleed chamber 52 may also be defined by drive arm 50 and high-pressure rotor shaft 38. In an exemplary embodiment, impeller tube 54 is at least partially disposed within one of the bleed chambers 52. In operation, the bleed chamber 52 receives bleed air 56 from a portion of the main flow path 36 defined by the high-pressure compressor 20. It should be understood that, although... Figure 2 Only one impeller tube 54 is shown, but the high-pressure compressor 20 may include any number of impeller tubes 54 as needed or as beneficial to the operation of the high-pressure compressor 20.
[0031] Figure 3 Exemplary embodiments provided according to this disclosure are as follows: Figure 2 An enlarged detailed cross-sectional view of a portion of the high-pressure compressor 20 is shown. (See attached image.) Figure 3 As shown, the high-pressure compressor 20 includes a compressor bleed air booster system 100. The compressor bleed air booster system 100 includes a first rotor disk 146(a), a second rotor disk 146(b), a drive arm 150, and an impeller tube 154. The second rotor disk 146(b) is axially adjacent to and spaced apart from the first rotor disk 146(a) relative to the axial direction A and the axial centerline 112 of the high-pressure compressor 20. The axial centerline 112 of the high-pressure compressor 20 may be aligned with the longitudinal centerline 12 (…) of the gas turbine engine 10. Figure 1 Coaxial alignment.
[0032] exist Figure 3In the illustrated embodiment, the first rotor disk 146(a) and the second rotor disk 146(b) are connected together via a drive arm 150. The first rotor disk 146(a) and the second rotor disk 146(b) are also connected to the high-pressure rotor shaft 38. The first rotor disk 146(a), the second rotor disk 146(b), and the high-pressure rotor shaft 38 are configured to rotate in a rotational direction (RD) about the axial centerline 112 of the high-pressure compressor 20. The rotational direction RD can rotate clockwise or counterclockwise about the axial centerline 112 of the high-pressure compressor 20.
[0033] The first rotor disk 146(a) and the second rotor disk 146(b) at least partially define an air bleed chamber 152 therebetween. The drive arm 150 defines an air bleed passage 158 that provides fluid communication of bleed air 56 from a portion of the main flow path 36 defined within the high-pressure compressor 20 to the air bleed chamber 152. The bleed air 56 is subsequently used as cooling or heating air for cooling or heating other components of the turbine 14, or may be directed to the gas turbine engine 10 (… Figure 1 Other locations.
[0034] like Figure 3 As shown, the impeller tube 154 is disposed within the air intake chamber 152 and axially positioned between the first rotor disk 146(a) and the second rotor disk 146. The impeller tube 154 includes a first end 160 defining an inlet 162 and an impeller tube flow channel 164 (e.g., Figure 6 (As shown) and a second end 166 defining the outlet 168. The inlet 162, impeller tube flow passage 164, and outlet 168 are in fluid communication with the bleed chamber 152. (As shown) Figure 3 As shown, the impeller tube 154 also includes a bleed air flow guide 170. The bleed air flow guide 170 is oriented or configured to guide bleed air 56 out of outlet 168 in a counter-current direction (CFD) opposite to the rotation direction RD of the high-pressure rotor shaft 38, thereby reducing or preventing pressure drop in bleed air 56 as it leaves outlet 168 within the bleed air chamber 152 near the high-pressure rotor shaft 38. As used herein, the term "counter-current direction" is intended to include a flow direction opposite to or at least perpendicular to or orthogonal to (e.g., not in the same or similar directions) the rotation direction RD of the high-pressure rotor shaft 38, regardless of whether the rotation direction RD is clockwise or counter-clockwise.
[0035] Figure 4 Provided such as Figure 3 The impeller tube 154 shown is a side view. Figure 5 Embodiments according to this disclosure are provided as follows: Figure 4 A perspective view of a portion of the impeller tube 154 shown, including a second end 166, an outlet 168, and an airflow guide 170. Figure 4In the exemplary embodiment shown, the impeller tube 154 can taper inward along the radial direction R from the second end 166 to the first end 160. Figure 3 , Figure 4 and Figure 5 In the exemplary embodiment shown together, the airflow guide 170 is formed as a shovel-shaped portion 172. The shovel-shaped portion 172 may have a generally hemispherical shape. Figure 3 and Figure 4 As shown, the shovel-shaped portion 172 extends radially inward from the second end 166 relative to the radial direction R, toward the axial centerline 112 of the high-pressure compressor 120 and the high-pressure rotor shaft 38. Figure 3 The shovel-shaped portion 172 also extends through the second end 166 in the axial direction A.
[0036] Figure 6 A top view of the first end at 160 degrees is provided, in particular Figure 4 The inlet 162 of the impeller tube 154 shown. Figure 7 Provided along Figure 4 The top view of the cross-section of the impeller tube 154 taken by section line 7-7, near the second end 166, shows the outlet 168 in detail. Figure 8 A bottom view of an impeller tube 154 according to an exemplary embodiment of the present disclosure is provided.
[0037] Reference Figure 6 Entrance 162 limits the entrance flow area to 174, such as Figure 7 As shown, outlet 168 defines an outlet flow area of 176. In this embodiment, as... Figure 6 and Figure 7 As shown in the figure, the inlet flow area 174 can be smaller than the outlet flow area 176.
[0038] In an exemplary embodiment, such as Figure 6 and Figure 7 As shown, the impeller tube 154, and particularly the impeller tube flow passage 164 defined by the impeller tube 154, may have a non-circular cross-section at the first end 160 or inlet 162. Furthermore, or alternatively, the impeller tube 154 may have a non-circular cross-section at the second end 166 or outlet 168. The term non-circular can include, but is not limited to, elliptical, teardrop-shaped, oval, flat-sided elliptical, or racetrack cross-sectional shapes. For example, as... Figure 6 and Figure 7 As shown, the impeller tube 154 can be formed as a flat-edged elliptical or "elliptical racetrack" shaped tube, including a pair of opposing flat edges 178(a), 178(b) and a pair of opposing curved edges 180(a) and 180(b).
[0039] In an exemplary embodiment, such as Figure 8As shown, the shovel-shaped portion 172 extends at least partially around the outlet 168 at the second end 166. For example, in the illustrated embodiment, the shovel-shaped portion 172 extends at least partially along the arcuate edge 180(a) (shown as a hidden line). In a particular embodiment, the shovel-shaped portion 172 may extend between approximately 10% and approximately 90% of the outlet flow area 176.
[0040] Figure 9 Embodiments according to this disclosure are provided as follows: Figure 4 The side view of a portion of the impeller tube 154 shown includes a second end 166, an outlet 168, and an airflow guide 170. Figure 10 A bottom view of an impeller tube 154 according to an exemplary embodiment of the present disclosure is provided, including a second end 166, an outlet 168, and an airflow guide 170. In the exemplary embodiment, as... Figure 9 and Figure 10 As shown, the airflow guide 170 may include at least one wall 182 that extends radially inward relative to the radial direction R from the second end 166 toward the axial centerline 112 of the high-pressure compressor 20 and extends in the axial direction A.
[0041] The wall 182 can extend from the shovel-shaped portion 172 along either of the opposing flat edges 178(a) and 178(b) along any one axis. In a particular embodiment, such as Figure 10 As shown, the airflow guide 170 may include a first wall 182(a) extending along a flat side 178(a). Alternatively, the airflow guide 170 may include a second wall 182(b) extending along the flat side wall 178(b). In operation, wall 182 or walls 182(a), 182(b) facilitates... Figure 9 As shown, bleed air 56 is guided in axial direction A through outlet 168 from impeller tube flow passage 164. Figure 7 Discharged, the axial direction A is equivalent to Figure 3 The reverse rotation direction CRD is shown.
[0042] Figure 11 A cross-sectional side view of an impeller tube 154 according to another embodiment of this disclosure is provided. Figure 11 As shown, the bleed air flow guide 170 can be formed along the inner surface 184 of the impeller tube 154 near the second end 166 and the outlet 168. As previously described, the bleed air flow guide 170 is formed or oriented to guide the bleed air 56 through the impeller tube flow passage 164 and out of the outlet 168 in a counter-current direction (CFD) opposite to the rotation direction RD of the high-pressure rotor shaft 38, thereby guiding the bleed air 56 out of the bleed air chamber 152 ( Figure 3 ) inside near the high-pressure rotor shaft 38 ( Figure 3Reduce or prevent pressure drop of bleed air 56 when the outlet 168 is reached.
[0043] Figure 12 A cross-sectional side view of an impeller tube 154 according to another embodiment of this disclosure is provided. Figure 12 As shown, the bleed air flow guide 170 can be formed as a curved portion 186 of the impeller tube 154 near the second end 166 and the outlet 168. As previously described, the bleed air flow guide 170 is formed or oriented to guide bleed air 56 through the impeller tube flow passage 164 and out of the outlet 168 in a counter-current direction (CFD) opposite to the rotation direction RD of the high-pressure rotor shaft 38, thereby guiding bleed air 56 out of the bleed air chamber 152 ( Figure 3 ) inside near the high-pressure rotor shaft 38 ( Figure 3 Reduce or prevent pressure drop of bleed air 56 when the outlet 168 is reached.
[0044] During operation, the bleed air flow guide 170 of the impeller tube 154 will work to force the bleed air leaving the impeller tube 154 to flow in a direction opposite to or opposite to the rotation direction RD of the high-pressure rotor shaft 38. In this way, the highly swirling air will be braked, and the inherent pressure loss of the highly swirling air due to the conservation of angular momentum will be alleviated. In other words, the bleed air flow guide 170 or the shovel-shaped portion 172 acts as a deswirler, and works best when used in conjunction with an impeller tube having an enlarged outlet flow area 176. Enlarging the outlet flow area 176 prevents or avoids tangential acceleration of the bleed air flow at the outlet. Furthermore, the wall 182 or walls 182(a), 182(b) can help guide the bleed air flow backward toward the second rotor disk 146(b) to prevent bleed air recirculation, thereby improving aerodynamics and reducing pressure loss within the bleed air chamber 152.
[0045] Further aspects are provided by the following topics:
[0046] A compressor bleed air booster system includes: a high-pressure compressor including a first rotor disk and a second rotor disk, wherein the first rotor disk and the second rotor disk are connected together via a drive arm and a rotor shaft, wherein the rotor shaft is configured to rotate in a rotational direction about an axial centerline of the high-pressure compressor, wherein the first rotor disk and the second rotor disk at least partially define a bleed air chamber therebetween, and wherein the drive arm defines a bleed air passage providing fluid communication between the main flow path of the high-pressure compressor and the bleed air chamber; and an impeller tube at least partially disposed within the bleed air chamber, wherein the impeller tube includes a first end defining an inlet and a second end defining an outlet, wherein the inlet and the outlet are in fluid communication with the bleed air chamber, wherein the outlet includes a bleed air flow guide.
[0047] According to the compressor bleed air booster system described above or any subsequent clause, wherein the bleed air flow guide is oriented to guide the bleed air in a counter-current direction opposite to the direction of rotation.
[0048] According to any of the foregoing or subsequent clauses of the compressor bleed air booster system, wherein the bleed air flow guide is formed as a shovel-shaped portion extending radially inward from the second end toward the axial centerline of the high-pressure compressor.
[0049] According to any of the foregoing or subsequent clauses, the compressor bleed air booster system wherein the impeller tube has a non-circular cross-section.
[0050] According to any of the foregoing or subsequent clauses, the compressor bleed air booster system wherein the impeller tube has a teardrop-shaped cross-section at the second end.
[0051] According to any of the foregoing or subsequent clauses, the compressor bleed air booster system wherein the impeller tube has a flat-sided elliptical cross-section at the second end.
[0052] According to any of the foregoing or subsequent clauses of the compressor bleed air booster system, wherein the bleed air flow guide is formed as a shovel-shaped portion extending radially inward from the second end toward the axial centerline of the high-pressure compressor.
[0053] According to any of the foregoing or subsequent clauses, the compressor bleed air booster system includes a wall extending radially inward from the second end toward the axial centerline of the high-pressure compressor.
[0054] According to any of the foregoing or subsequent clauses of the compressor bleed air booster system, wherein the impeller tube defines an inner surface, and wherein the bleed air flow guide is formed along the inner surface near the second end.
[0055] According to any of the foregoing or subsequent clauses, the compressor bleed air booster system wherein the impeller tube is tapered between the second end and the first end.
[0056] According to any of the foregoing or subsequent clauses of the compressor bleed air booster system, wherein the impeller tube includes a curved portion defined near the second end, wherein the bleed air flow guide is defined by the curved portion of the impeller tube.
[0057] A gas turbine engine includes: a high-pressure compressor, a combustion section, and a turbine section arranged in series along a rotor shaft, the high-pressure compressor, combustion section, and turbine section defining a main flow path through the gas turbine engine; the high-pressure compressor including: a first rotor disk; a second rotor disk, wherein the first rotor disk and the second rotor disk are connected together with the rotor shaft via a drive arm, wherein the rotor shaft is configured to rotate in a rotational direction about an axial centerline of the high-pressure compressor, wherein the first rotor disk and the second rotor disk at least partially define a bleed chamber therebetween, and wherein the drive arm defines a bleed passage, the bleed passage providing fluid communication of bleed air between the main flow path of the high-pressure compressor and the bleed chamber; and an impeller tube, the impeller tube at least partially disposed within the bleed chamber, wherein the impeller tube includes a first end defining an inlet and a second end defining an outlet, wherein the inlet and the outlet are in fluid communication with the bleed chamber, wherein the outlet includes a bleed air flow guide.
[0058] According to the gas turbine engine described above or any subsequent clause, the bleed air flow guide is oriented to guide the bleed air flow in a counter-current direction opposite to the direction of rotation.
[0059] According to any of the preceding or subsequent clauses of the gas turbine engine, wherein the bleed air flow guide is formed as a shovel-shaped portion extending radially inward from the second end toward the axial centerline of the high-pressure compressor.
[0060] According to any of the preceding or subsequent clauses, the gas turbine engine wherein the impeller tube has a non-circular cross-section.
[0061] According to any of the preceding or following clauses, the gas turbine engine wherein the impeller tube has a teardrop-shaped cross-section.
[0062] According to any of the preceding or subsequent clauses, the gas turbine engine wherein the impeller tube has a flat-sided elliptical cross-section.
[0063] According to any of the preceding or subsequent clauses of the gas turbine engine, wherein the bleed air flow guide is formed as a shovel-shaped portion extending radially inward from the second end toward the axial centerline of the high-pressure compressor.
[0064] According to any of the foregoing or subsequent clauses of the gas turbine engine, wherein the bleed air flow guide further includes a wall extending radially inward from the second end toward the axial centerline of the high-pressure compressor.
[0065] According to any of the preceding or following clauses of the gas turbine engine, wherein the bleed air flow guide is formed along the inner surface of the impeller tube near the second end.
Claims
1. A compressor bleed air booster system, characterized in that, include: A high-pressure compressor includes a first rotor disk and a second rotor disk, wherein the first rotor disk and the second rotor disk are connected together via a drive arm and a rotor shaft, wherein the rotor shaft is configured to rotate in a rotational direction about an axial centerline of the high-pressure compressor, wherein the first rotor disk and the second rotor disk at least partially define a bleed chamber therebetween, and wherein the drive arm defines a bleed passage that provides fluid communication between the main flow path of the high-pressure compressor and the bleed chamber for bleed air; and An impeller tube, at least partially disposed within the air intake chamber, wherein the impeller tube includes a first end defining an inlet and a second end defining an outlet, wherein the inlet and the outlet are in fluid communication with the air intake chamber, wherein the outlet includes an air intake flow guide.
2. The compressor bleed air booster system according to claim 1, characterized in that, The airflow guide is oriented to guide the airflow in a counter-current direction opposite to the direction of rotation.
3. The compressor bleed air booster system according to claim 1, characterized in that, The airflow guide is formed in the shape of a shovel, which extends radially inward from the second end toward the axial centerline of the high-pressure compressor.
4. The compressor bleed air booster system according to claim 1, characterized in that, The impeller tube described therein has a non-circular cross-section.
5. The compressor bleed air booster system according to claim 1, characterized in that, The impeller tube has a teardrop-shaped cross-section at the second end.
6. The compressor bleed air booster system according to claim 1, characterized in that, The impeller tube has a flat-sided elliptical cross-section at the second end.
7. The compressor bleed air booster system according to claim 1, characterized in that, The airflow guide is formed in the shape of a shovel, which extends radially inward from the second end toward the axial centerline of the high-pressure compressor.
8. The compressor bleed air booster system according to claim 1, characterized in that, The airflow guide includes a wall that extends radially inward from the second end toward the axial centerline of the high-pressure compressor.
9. The compressor bleed air booster system according to claim 1, characterized in that, The impeller tube defines an inner surface, and the airflow guide is formed along the inner surface near the second end.
10. The compressor bleed air booster system according to claim 1, characterized in that, The impeller tube is tapered between the second end and the first end.