A gas turbine engine high pressure compressor bleed air duct assembly

Abstract

The application belongs to the technical field of aero-engine high-pressure compressor bleed air casing assembly design, and particularly relates to an aero-engine high-pressure compressor bleed air casing assembly. A valve housing is welded on a casing shell through a support, so that the casing shell and the bleed valve are connected through welding, a large number of rivet holes in the casing shell are not needed, the mechanical properties of the casing shell can be protected, in addition, the valve housing is in a cylindrical shape and lies on the casing shell, so that the bleed valve is arranged in an axial direction of the high-pressure compressor casing, the occupied space in the radial direction is reduced, the stress area exposed in the outer channel is reduced, and the oil supply pipe is arranged at one end of the valve housing, facilitating pipeline arrangement.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of high-pressure compressor bleed air casing assembly design of an aero-engine, and particularly relates to a high-pressure compressor bleed air casing assembly of an aero-engine. BACKGROUND

[0002] In the high-pressure compressor of an aero-engine, the bleed air casing assembly is connected to the outer periphery of the high-pressure compressor casing, and is provided with a bleed air valve and an air bleed pipe for bleed air and air bleed.

[0003] In the current high-pressure compressor bleed air casing assembly of an aero-engine, the bleed air valve is fixed by radial riveting in a vertical structure on the casing shell, a large number of rivet holes need to be arranged on the casing shell, the mechanical properties of the casing shell are greatly damaged, the rivets are easily damaged by vibration fatigue, in addition, the vertical fixing of the bleed air valve occupies a large space in the radial direction, the force area exposed in the outer duct is large, the rivets bear a large shear and impact force, which further increases the possibility of fatigue damage of the rivets, and the bleed air valve is driven by hydraulic pressure, the oil supply pipe is installed on the top, and the pipeline layout is complex.

[0004] The present application is proposed in view of the above technical defects.

[0005] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0006] The purpose of the present application is to provide a high-pressure compressor bleed air casing assembly of an aero-engine to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of the present application is:

[0008] A high-pressure compressor bleed air casing assembly of an aero-engine, comprising:

[0009] a casing shell in the shape of a ring, sleeved on the outer periphery of the high-pressure compressor casing, forming an annular gas collecting cavity with the high-pressure compressor casing, having a first bleed air hole thereon, and having an air bleed port; the high-pressure compressor casing has a communication hole;

[0010] an air bleed connector arranged in the air bleed port and connected to the air bleed pipe;

[0011] a bleed air valve, comprising:

[0012] The valve housing is welded to the outer casing of the gearbox, and is cylindrical in shape, lying on the outer casing of the gearbox. The side wall has a third vent hole and a fourth vent hole. One end face has an oil supply interface, and the other end face has a vent hole; the third vent hole is connected to the first vent hole.

[0013] Two valve partitions are installed inside the valve housing, dividing the interior of the valve housing into an end oil supply chamber, a middle spring chamber, and an end venting chamber; the end oil supply chamber is connected to the oil supply interface, and the end venting chamber is connected to the third venting hole, the fourth venting hole, and the vent hole.

[0014] The oil supply connector is connected to the oil supply interface and then to the oil supply pipe.

[0015] A hydraulic piston is installed inside the oil supply chamber;

[0016] A venting piston is installed inside the venting chamber;

[0017] The piston rod passes through two valve partitions and is connected to the hydraulic piston and the venting piston at both ends. The outer wall of the part located in the middle spring cavity has a protruding part.

[0018] A spring is installed in the middle spring cavity and connected between the protruding part and a valve partition. It uses its elastic force to press the protruding part against another valve partition, and the venting piston blocks the third venting hole and the fourth venting hole.

[0019] According to at least one embodiment of this application, in the above-mentioned high-pressure compressor venting casing assembly of an aero-engine, the venting valve housing is divided into three sections, and a valve partition is provided between two connected sections, with the connecting edges connected by bolts.

[0020] According to at least one embodiment of this application, the above-described high-pressure compressor bleeder casing assembly for an aero-engine further includes:

[0021] Two supports are welded between the outer casing of the casing and the inner valve housing of the vent valve. One of the supports has a second vent hole; the second vent hole is connected to the first vent hole and the third vent hole.

[0022] According to at least one embodiment of this application, in the above-mentioned high-pressure compressor venting casing assembly of the aero-engine, there are multiple first venting holes distributed circumferentially, which are divided into front venting holes and rear venting holes. The front venting holes and rear venting holes are angularly staggered from each other in the circumferential direction.

[0023] There are multiple sets of supports and their vent valves corresponding to each first vent hole;

[0024] The oil supply nozzle of the vent valve corresponding to the front vent is positioned backward, while the oil supply nozzle of the vent valve corresponding to the rear vent is positioned forward.

[0025] According to at least one embodiment of this application, in the above-mentioned high-pressure compressor venting casing assembly of the aero-engine, the venting valve corresponding to the front venting port shares a valve housing and valve partition with the venting valve corresponding to the adjacent rear venting port.

[0026] According to at least one embodiment of this application, in the above-mentioned high-pressure compressor venting casing assembly of the aero-engine, the end oil supply chamber, the intermediate spring chamber, the end venting chamber, the hydraulic piston, and the venting piston of each venting valve are elliptical.

[0027] According to at least one embodiment of this application, in the above-mentioned high-pressure compressor vent casing assembly of the aero-engine, there are multiple connecting holes on the high-pressure compressor casing, which are distributed circumferentially and are divided into front connecting holes and rear connecting holes.

[0028] The high-pressure compressor bleed casing assembly of the aero-engine also includes:

[0029] Two outer casing partitions, arranged inside the casing, divide the annular gas collecting chamber into an end process chamber, an intermediate gas collecting chamber, and an end gas collecting chamber.

[0030] The intermediate air collection chamber is connected to the front connecting hole and the front air outlet;

[0031] The end gas collection chamber is connected to the rear exhaust port and the rear exhaust port.

[0032] According to at least one embodiment of this application, in the above-described high-pressure compressor vent casing assembly for an aero-engine, the casing outer shell is bolted to the high-pressure compressor casing.

[0033] The two outer shell partitions are divided into an inner partition section and an outer partition section that are joined together by folded edges. The inner partition section is connected to the outer casing of the casing by folded edges, and the outer partition section is connected to the high-pressure compressor casing by folded edges. The inner partition section and the outer partition section are fitted with a small clearance by bending.

[0034] According to at least one embodiment of this application, in the above-mentioned high-pressure compressor venting casing assembly of the aero-engine, there are multiple first venting ports distributed circumferentially, which are divided into front venting ports and rear venting ports.

[0035] There are multiple vent valves corresponding to each first vent hole;

[0036] Each vent valve is located in an annular gas collection chamber, wherein the valve housing is connected to the inner side of the casing housing;

[0037] In the vent valves corresponding to the front and rear vent ports respectively, adjacent vent valves share a single oil supply nozzle, which extends to the outside of the casing.

[0038] According to at least one embodiment of this application, in the above-mentioned high-pressure compressor venting casing assembly of the aero-engine, the end oil supply chamber, the intermediate spring chamber, the end venting chamber, the hydraulic piston, and the venting piston of each venting valve are fan-shaped.

[0039] In each venting valve, the piston rod is curved and hinged at both ends to a hydraulic piston and a venting piston. Attached Figure Description

[0040] Figure 1 This is a schematic diagram of the venting piston sealing the third and fourth venting holes in the venting casing assembly of the high-pressure compressor of an aero-engine provided in this application embodiment;

[0041] Figure 2 This is a schematic diagram of the third and fourth vent holes in the vent piston of the vent casing assembly of the high-pressure compressor of an aero-engine provided in this application embodiment;

[0042] Figure 3 This is a schematic diagram showing the circumferential distribution of the support and its vent valve provided in the embodiments of this application on the outer casing of the casing;

[0043] Figure 4 This is a schematic diagram of the venting valves arranged side by side according to an embodiment of this application;

[0044] Figure 5 This is a schematic diagram of the integrated design of the vent valve provided in the embodiments of this application;

[0045] Figure 6 yes Figure 5 Side view;

[0046] Figure 7 This is a schematic diagram of the design of the vent valve inside the casing according to an embodiment of this application;

[0047] in:

[0048] 1-Casing outer shell; 2-High-pressure compressor casing; 3-Bleed air connector; 4-Support; 5-Bleed air valve; 6-Valve housing; 7-Valve partition; 8-Oil supply nozzle; 9-Hydraulic piston; 10-Bleed air piston; 11-Piston rod; 12-Spring; 13-Outer shell partition.

[0049] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0050] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0051] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0052] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0053] The following is in conjunction with the appendix Figures 1 to 7 This application will be described in further detail.

[0054] A high-pressure compressor bleed gas casing assembly for an aero-engine includes:

[0055] The casing 1 is annular and fits around the outer periphery of the high-pressure compressor casing 2, forming an annular gas collecting cavity between it and the high-pressure compressor casing 2. It has a first vent hole and an air intake port. The high-pressure compressor casing 2 has a connecting hole that connects to the annular gas collecting cavity.

[0056] Air intake connector 3 is installed in the air intake port and connected to the air intake tube for air intake;

[0057] vent valve 5 includes:

[0058] The valve housing 6 is welded to the outer casing 1 of the casing. It is cylindrical and lies on the outer casing (1). The side wall has a third vent hole and a fourth vent hole. One end face has an oil supply interface and the other end face has a vent hole. The third vent hole is connected to the first vent hole.

[0059] Two valve partitions 7 are installed inside the valve housing 6, dividing the interior of the valve housing 6 into an end oil supply chamber, a middle spring chamber, and an end venting chamber; the end oil supply chamber is connected to the oil supply interface, and the end venting chamber is connected to the third venting hole, the fourth venting hole, and the vent hole.

[0060] Oil supply connector 8 is connected to the oil supply interface and connected to the oil supply pipe;

[0061] Hydraulic piston 9 is installed inside the oil supply chamber;

[0062] The venting piston 10 is installed inside the venting chamber;

[0063] The piston rod 11 is set through the two valve partitions 7 and is connected to the hydraulic piston 9 and the venting piston 10 at both ends. The outer wall of the part located in the middle spring cavity has a protruding part.

[0064] Spring 12, located within the intermediate spring cavity, can be sleeved around the outer periphery of piston rod 11, connecting the protruding part to a valve partition 7. Its elastic force presses the protruding part against another valve partition 7, and the vent piston 10 blocks the third and fourth vent holes. Figure 1 As shown.

[0065] Regarding the high-pressure compressor venting casing assembly of the aero-engine disclosed in the above embodiments, those skilled in the art will understand that when venting is required, hydraulic oil can be introduced into the oil supply chamber through the oil supply pipe to increase the pressure in the oil supply chamber, pushing the hydraulic piston 9 to move towards the intermediate spring chamber. This, in turn, drives the venting piston 10 to move away from the intermediate spring chamber via the piston rod, gradually offsetting the third and fourth venting holes, thus releasing the blockage of the third and fourth venting holes. Figure 2As shown, the gas inside the high-pressure compressor casing 2 can enter the annular gas collecting chamber through the connecting hole, enter the end gas venting chamber through the first and third gas venting holes, and then be discharged through the fourth gas venting hole. After the gas venting is completed, the hydraulic oil in the oil supply chamber can be reduced through the oil supply pipe to reduce the pressure in the oil supply chamber. This causes the piston rod 11 to move towards the oil supply chamber under the elastic force of the spring 12, which in turn drives the hydraulic piston 9 to move away from the middle spring chamber and drives the gas venting piston 10 to move towards the middle spring chamber, thus restoring the sealing of the third and fourth gas venting holes.

[0066] Regarding the high-pressure compressor venting casing assembly of the aero-engine disclosed in the above embodiments, those skilled in the art will understand that its valve housing 6 is designed to be welded to the casing outer shell 1 via a support 4, so that the casing outer shell 1 and the venting valve 5 are connected by welding. This eliminates the need to open numerous rivet holes on the casing outer shell 1, thus protecting the mechanical properties of the casing outer shell 1. In addition, the valve housing 6 is designed to be cylindrical and rests on the casing outer shell 1, so that the venting valve 5 is arranged along the axial direction of the high-pressure compressor casing 2, which can reduce the space occupied in the radial direction and reduce the stress area exposed in the outer bypass duct. Furthermore, the fuel supply pipe is designed to be located at one end of the valve housing 6, which can be set close to the casing shell to avoid the fuel supply pipe being suspended, making the stress on the fuel supply pipe more reasonable and reducing the possibility of interference with other pipelines. This facilitates pipeline layout, and the connecting hole on the high-pressure compressor casing 2, as well as the venting valve 5 and the venting hole on the casing shell 1, can be used as inspection holes, eliminating the need to open additional inspection holes.

[0067] In some optional embodiments, in the above-mentioned high-pressure compressor venting casing assembly of the aero-engine, the valve housing 6 of the venting valve 5 is divided into three sections, and a valve partition 7 is provided between two connected sections, so that the connecting edges are connected by bolts for easy assembly.

[0068] In some optional embodiments, in the above-mentioned high-pressure compressor venting casing assembly of the aero-engine, two supports 4 are welded between the casing shell 1 and the valve housing 6 of the venting valve 5, or they can be integrally formed with the valve housing 6. One of the supports 4 has a second venting hole; the second venting hole is connected to the first venting hole and the third venting hole.

[0069] In some optional embodiments, in the above-mentioned high-pressure compressor venting casing assembly of the aero-engine, there are multiple first venting ports distributed circumferentially, which are divided into front venting ports and rear venting ports. The front venting ports and rear venting ports are angularly staggered from each other in the circumferential direction.

[0070] Corresponding to each first vent hole, the support 4 and its vent valve 5 have multiple sets, such as Figure 3 As shown;

[0071] The oil supply nozzle 8 of the vent valve 5 corresponding to the front vent outlet faces backward, and the oil supply nozzle 8 of the vent valve 5 corresponding to the rear vent outlet faces forward. The vent valves 5 corresponding to adjacent front and rear vent outlets are arranged side by side, such as... Figure 4 As shown, this facilitates pipeline layout.

[0072] In some optional embodiments, in the above-described high-pressure compressor vent casing assembly of the aero-engine, the vent valve 5 corresponding to the front vent port shares the valve housing 6 and valve partition 7 with the vent valve 5 corresponding to the adjacent rear vent port, and may also share the support 4, for integrated design, such as... Figure 5 As shown, this design aims to make the overall structure of the component compact, easy to assemble, and reduce disturbances to the external flow path.

[0073] In some optional embodiments, in the above-described high-pressure compressor bleed casing assembly of the aero-engine, the end oil supply chamber, intermediate spring chamber, end bleed chamber, hydraulic piston 9, and bleed piston 10 of each bleed valve 5 are elliptical in shape, such as... Figure 6 As shown, due to space constraints, it is not convenient to sleeve the spring 12 on the piston rod 11. Instead, two springs 12 can be designed in each vent valve 5, distributed on both sides of the piston rod 11.

[0074] In some optional embodiments, in the above-mentioned high-pressure compressor venting casing assembly of the aero-engine, the high-pressure compressor casing 2 has multiple connecting holes distributed circumferentially, which are divided into front connecting holes and rear connecting holes.

[0075] The high-pressure compressor bleed casing assembly of the aero-engine also includes:

[0076] Two outer casing partitions 13 are arranged inside the casing 1, dividing the annular gas collecting chamber into an end process chamber, an intermediate gas collecting chamber, and an end gas collecting chamber.

[0077] The intermediate air collection chamber is connected to the front connecting hole and the front air outlet;

[0078] The end gas collection chamber is connected to the rear exhaust port and the rear exhaust port.

[0079] In some optional embodiments, in the above-described high-pressure compressor bleed casing assembly for aero-engines, the casing housing 1 is bolted to the high-pressure compressor casing 2;

[0080] The two outer shell partitions 13 are divided into an inner partition section and an outer partition section that are joined by folded edges. The inner partition section is connected to the outer shell of the casing 1 by folded edges, and the outer partition section is connected to the high-pressure compressor casing 2 by folded edges. The inner partition section and the outer partition section are bent with a small clearance to facilitate the assembly of components.

[0081] In some optional high-pressure compressor venting casing assemblies for aero engines, there are multiple first venting ports distributed circumferentially, which are divided into front venting ports and rear venting ports.

[0082] There are multiple vent valves 5 corresponding to each first vent hole;

[0083] Each vent valve 5 is located in the annular gas collection chamber, wherein the valve housing 6 is connected to the inner side of the casing housing 1, specifically through a connecting edge and bolts;

[0084] In the vent valves 5 corresponding to the front vent and the rear vent respectively, adjacent vent valves 5 share a common oil supply nozzle 8. The oil supply nozzle 8 extends to the outside of the casing 1. A communication gap can be formed between the valve housing 6 and the casing 1 in adjacent vent valves 5, connecting the first vent and the third vent.

[0085] Among the vent valves 5 corresponding to the front and rear vent ports respectively, adjacent vent valves 5 share a single oil supply nozzle 8, which extends to the outside of the casing 1. Figure 7 As shown, two first, third, and fourth vent holes can be controlled simultaneously through one oil supply pipe, making the venting more uniform and reducing the disturbance to the airflow in the inner and outer flow channels. Multiple vent valves 5 can be connected end to end in sequence to form a complete ring.

[0086] Regarding the high-pressure compressor venting casing assembly of the aero-engine disclosed in the above embodiments, those skilled in the art will understand that when venting is required, hydraulic oil can be introduced into the oil supply chamber through the oil supply pipe to increase the pressure in the oil supply chamber, pushing the hydraulic piston 9 to move towards the intermediate spring chamber. The piston rod drives the venting piston 10 to move away from the intermediate spring chamber, gradually offsetting the third and fourth venting holes, thus releasing the blockage of the third and fourth venting holes. Gas in the high-pressure compressor casing 2 can enter the annular gas collecting chamber through the connecting hole, enter the end venting chamber through the fourth venting hole, and then be discharged through the third and first venting holes. After venting is completed, the hydraulic oil in the oil supply chamber can be reduced through the oil supply pipe to lower the pressure in the oil supply chamber. Under the elastic force of the spring 12, the piston rod 11 moves towards the oil supply chamber, driving the hydraulic piston 9 to move away from the intermediate spring chamber and driving the venting piston 10 to move towards the intermediate spring chamber, restoring the blockage of the third and fourth venting holes.

[0087] For the high-pressure compressor venting casing assembly of the aero-engine disclosed in the above embodiments, those skilled in the art will understand that its design allows each venting valve 5 to be located inside the casing shell 1, which can make full use of the internal space of the casing shell 1, reduce the radial dimension, and avoid being exposed in the outer bypass duct, thus avoiding interference with the flow path of the outer bypass duct. In addition, the venting valves 5 that are adjacent to the front venting port and the rear venting port are designed to share a single oil supply nozzle 8, making the overall structure compact and easy to assemble.

[0088] In some optional high-pressure compressor venting casing assemblies for aero engines, the end oil supply chamber, intermediate spring chamber, end venting chamber, hydraulic piston 9, and venting piston 10 of each venting valve 5 are fan-shaped.

[0089] In each of the venting valves 5, the piston rod 11 is curved and is hinged at both ends to the hydraulic piston 9 and the venting piston 10. Specifically, the hinge can be made through a spherical bearing to avoid jamming.

[0090] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0091] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A high-pressure compressor bleed-out casing assembly for an aero-engine, characterized in that, include: The casing (1) is annular and fits around the outer periphery of the high-pressure compressor casing (2), forming an annular gas collecting cavity between it and the high-pressure compressor casing (2). It has a first vent hole and an air intake port. The high-pressure compressor casing (2) has a connecting hole. The connecting hole connects to the annular gas collecting cavity. A priming connector (3) is installed in the priming port and connected to the priming tube; The vent valve (5) includes: The valve housing (6) is welded to the outer shell of the casing (1), and is cylindrical. It lies on the outer shell of the casing (1). The side wall has a third vent hole and a fourth vent hole. One end face has an oil supply interface, and the other end face has a vent hole. The third vent hole is connected to the first vent hole. Two valve partitions (7) are provided inside the valve housing (6), dividing the interior of the valve housing (6) into an end oil supply chamber, an intermediate spring chamber, and an end venting chamber; the end oil supply chamber is connected to the oil supply interface, and the end venting chamber is connected to the third venting hole, the fourth venting hole, and the venting hole; Oil supply connector (8) is connected to the oil supply interface and connected to the oil supply pipe; A hydraulic piston (9) is installed in the oil supply chamber; A venting piston (10) is installed inside the venting chamber; The piston rod (11) is set through the two valve partitions (7) and is connected to the hydraulic piston (9) and the venting piston (10) at both ends. The outer wall of the part located in the middle spring cavity has a protruding part. A spring (12) is installed in the middle spring cavity and connected between the protruding part and a valve partition (7). It uses its elastic force to press the protruding part onto another valve partition (7). The venting piston (10) blocks the third venting hole and the fourth venting hole. Two supports (4) are welded between the outer casing (1) and the valve housing (6) of the vent valve (5). One of the supports (4) has a second vent hole; the second vent hole is connected to the first vent hole and the third vent hole. There are multiple first vent holes, distributed circumferentially, divided into front vent holes and rear vent holes. The front vent holes and rear vent holes are staggered in circumferential angle distribution. There are multiple sets of support (4) and its vent valve (5) corresponding to each first vent hole; The oil supply nozzle (8) of the vent valve (5) corresponding to the front vent is backward, and the oil supply nozzle (8) of the vent valve (5) corresponding to the rear vent is forward. The high-pressure compressor casing (2) has multiple connecting holes, which are distributed circumferentially and are divided into front connecting holes and rear connecting holes; The high-pressure compressor bleed casing assembly of the aero-engine also includes: Two outer shell partitions (13) are arranged inside the casing shell (1), dividing the annular gas collecting chamber into an end process chamber, an intermediate gas collecting chamber, and an end gas collecting chamber, wherein, The intermediate air collection chamber is connected to the front connecting hole and the front air outlet; The end gas collection chamber is connected to the rear exhaust port and the rear exhaust port; The casing (1) is bolted to the high-pressure compressor casing (2); The two outer shell partitions (13) are divided into an inner partition section and an outer partition section connected by folded edges. The inner partition section is connected to the outer shell of the casing (1) by folded edges, and the outer partition section is connected to the high-pressure compressor casing (2) by folded edges.

2. The high-pressure compressor bleeder casing assembly for an aero-engine according to claim 1, characterized in that, The valve body (6) of the vent valve (5) is divided into three sections, and a valve partition (7) is provided between two connected sections.

3. The high-pressure compressor bleeder casing assembly for an aero-engine according to claim 1, characterized in that, The vent valve (5) corresponding to the front vent is shared with the vent valve (5) corresponding to the adjacent rear vent. It shares the valve housing (6) and valve partition (7).

4. The high-pressure compressor bleeder casing assembly for an aero-engine according to claim 1, characterized in that, In each of the vent valves (5), the end oil supply chamber, the middle spring chamber, the end vent chamber, the hydraulic piston (9), and the vent piston (10) are elliptical.

5. The high-pressure compressor bleeder casing assembly for an aero-engine according to claim 1, characterized in that, Among the vent valves (5) that correspond to the front vent and the rear vent respectively, adjacent vent valves (5) share a common oil supply nozzle (8).

6. The high-pressure compressor bleeder casing assembly for an aero-engine according to claim 1, characterized in that, In each vent valve (5), the end oil supply chamber, the middle spring chamber, the end vent chamber, the hydraulic piston (9), and the vent piston (10) are fan-shaped; In each vent valve (5), the piston rod (11) has an arc and is hinged at both ends to the hydraulic piston (9) and the vent piston (10).

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