Axial diffuser structure, aero-engine and aircraft

Abstract

The invention discloses an axial diffuser structure, an aero-engine and an aircraft, and the axial diffuser structure comprises a base body structure, a mounting base which is arranged in the base body structure and is coaxial with the base body structure, and support plate structures which are arranged in the radial direction and are uniformly distributed in the circumferential direction, the two ends of the supporting plate structures are connected to the outer wall of the mounting base and the inner wall of the base body structure correspondingly, and the number of the supporting plate structures is at least three; a first mounting structure and a second mounting structure are respectively arranged at two ends of the mounting base; the mounting base is provided with an inner cavity, the first mounting structure is used for being connected with a bearing seat, and the second mounting structure is used for being connected with a guider. A support plate structure is provided with an oil return channel communicated to the inner cavity of the mounting base; and the other supporting plate structure is provided with an oil supply channel communicated to the inner cavity of the mounting base. On the basis of the axial diffuser structure, mounting interfaces are provided for a bearing seat and a guider, integrated arrangement of an oil inlet channel and an oil return channel is achieved, high structure integration is achieved, and oil injection cooling, lubrication and oil return of a power device are achieved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of auxiliary power units of aero-engines, and particularly relates to an axial diffuser structure. BACKGROUND

[0002] The axial diffuser is one of the important components of the auxiliary power unit of an aero-engine. The existing axial diffuser of the auxiliary power unit is usually a single-function part, and reference Figure 1 Although the structure is simple and easy to process, it usually only has the function of speed reduction and pressure increase. With the increasing requirements of the single-stage centrifugal auxiliary power unit in function and performance, the existing single-function axial diffuser is usually difficult to meet the requirements of the auxiliary power unit in oil feeding and returning, air sealing, and other functions, and a relatively complex mechanical system with a large number of parts is needed to meet the above-mentioned functions, which increases the weight and production cost.

[0003] The existing axial diffuser is usually designed as a simple blade diffuser, which is mainly used to change the direction of airflow and reduce the speed of airflow to meet the air intake requirement of the combustion chamber. The existing axial diffuser generally does not have a lubricating oil injection channel, a lubricating oil pump suction oil return channel, and a gravity oil return channel. In order to meet the requirements of weight and structural layout, the existing axial diffuser generally does not have a bearing lubrication, cooling and air sealing structure. When the power of the auxiliary power unit is large and the working condition is complex, the transmission requirement of the axial force is also high. The existing axial diffuser generally does not have a bearing seat structure, so it cannot transmit the axial force to the casing and mounting section, and usually only transmits the force through the bearing seat or other structures. In order to meet these functions and requirements, a large number of parts are needed, which is heavy in weight, high in cost, complex in disassembly and assembly process, and poor in reliability. SUMMARY

[0004] The present application provides an axial diffuser structure, an aero-engine and an aircraft to solve the technical problem that the compressor in the prior art needs to be designed with a relatively complex mechanical system with a large number of parts before and after the axial diffuser to meet the functions of the auxiliary power unit in oil feeding and returning, air sealing, and the like.

[0005] According to one aspect of the present application, an axial diffuser structure is provided for a single-stage centrifugal compressor of an aero-engine auxiliary power unit, comprising a base structure, a mounting base arranged in the base structure and coaxially arranged with the base structure, and a plurality of radially arranged and circumferentially uniformly distributed support plate structures, both ends of each support plate structure being connected to the outer wall of the mounting base and the inner wall of the base structure, and at least three support plate structures being provided; both ends of the mounting base are provided with a first mounting structure and a second mounting structure; the mounting base has an inner cavity for arranging a bearing seat, the first mounting structure is used for connecting with the bearing seat, and the second mounting structure is used for connecting with a guide; one of the support plate structures is provided with an oil return channel communicated with the inner cavity of the mounting base; another of the support plate structures is provided with an oil supply channel communicated with the inner cavity of the mounting base.

[0006] As a further improvement of the above technical solution, the axial diffuser structure further comprises a bearing seat arranged in the inner cavity of the mounting base and connected with the first mounting structure, the bearing seat is provided with a lubricating oil supply oil path and an oil return oil path, the lubricating oil supply oil path is used for cooperating with the oil supply channel and the bearing mounting position of the inner ring surface of the bearing seat respectively, and the oil return oil path is used for cooperating with the oil return channel and the bearing mounting position of the inner ring surface of the bearing seat.

[0007] As a further improvement of the above technical solution, one end of the bearing seat is radially extended and provided with a connecting flange used for cooperating with the first mounting structure.

[0008] As a further improvement of the above technical solution, the axial diffuser structure further comprises a third mounting structure arranged on the end face of the axial diffuser structure, a plurality of third mounting structures are uniformly distributed along the circumference of the axial diffuser, and the third mounting structure is used for connecting with a combustion chamber large elbow.

[0009] As a further improvement of the above technical solution, a labyrinth seal structure is arranged between the axial diffuser and the centrifugal impeller, the mounting base is provided with an air bleeding seal structure for bleeding the gas in the combustion chamber to the position of the labyrinth seal structure between the axial diffuser structure and the centrifugal impeller to form a pressure difference at both ends of the labyrinth seal structure and prevent oil leakage.

[0010] As a further improvement of the above technical solution, the air bleeding seal structure comprises an air bleeding channel axially arranged in the mounting base and uniformly distributed along the circumference of the mounting base, and the air bleeding channel is used for bleeding the gas in the combustion chamber to the position of the labyrinth seal structure between the axial diffuser structure and the centrifugal impeller.

[0011] As a further improvement of the above technical solution, the branch plate structure provided with the oil return channel is located in the lower half ring range of the axial diffuser structure in the mounted state.

[0012] As a further improvement of the above technical solution, the inner wall of the axial diffuser structure is uniformly distributed with fourth mounting structures for connecting with the combustor generator casing.

[0013] According to another aspect of the present application, an aero-engine is also provided, which comprises the above axial diffuser structure.

[0014] According to another aspect of the present application, an aircraft is also provided, which comprises the above axial diffuser structure.

[0015] The present application has the following beneficial effects: The axial diffuser structure is coaxially arranged with a mounting base in the base structure, the first mounting structure and the second mounting structure are arranged at both ends of the mounting base, the first mounting structure is used for connecting with the bearing seat, the second mounting structure is used for connecting with the guide, the bearing is installed by the bearing seat to support the rotating shaft of the centrifugal impeller, and the connection with the guide is realized based on the mounting base, without relying on the complex structure arranged on the casing for installation, the casing structure between the axial diffuser and the guide is omitted, the structure is compact, the number of parts is small, and the lightweight of the aero-engine is further realized; at least three branch plate structures are arranged along the radial direction to connect the base structure and the mounting base, on the one hand, the mounting base is stably supported to ensure the coaxiality and further ensure the installation accuracy of the shaft connection and even the casing, the guide and other structures, and on the other hand, the oil supply channel and the oil return channel are arranged based on the branch plate structure, the two groups of channels are located in different branch plates and are communicated to the oil way of the bearing seat in the inner cavity of the mounting base to be communicated to the bearing position, the integrated arrangement of the oil supply channel and the oil return channel is realized based on the axial diffuser structure, the structure is further integrated, the oil injection cooling, lubrication and oil return of the auxiliary power device are realized, the axial space of the aero-engine is more abundant based on the axial diffuser structure, the number of parts is reduced, the weight is lighter, and the design improvement of the power part of the aero-engine is more beneficial In addition to the objects, features, and advantages described above, the present application has other objects, features, and advantages. Hereinafter, the present application will be described in further detail with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0016] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application, and are incorporated in and constitute a part of this application. The embodiments of the application illustrated in the drawings are provided to explain the present application and are not intended to limit the present application. In the drawings: Figure 1 is a structural schematic diagram of an axial diffuser in the prior art; Figure 2is the front view of the axial diffuser structure of the preferred embodiment of the present application; Figure 3 is the A-direction sectional view of Figure 2 Figure 4 is the B-direction sectional view of Figure 2 Figure 5 is the C-direction sectional view of Figure 2 Figure 6 is the schematic diagram of the axial diffuser mounting state of the axial diffuser structure of the preferred embodiment of the present application; Figure 7 is the schematic diagram of the bleed air sealing of the axial diffuser structure of the preferred embodiment of the present application.

[0017] Legend: 100, base structure; 200, mounting base; 201, first mounting structure; 202, second mounting structure; 101, third mounting structure; 102, fourth mounting structure; 203, bleed air passage; 300, support plate structure; 301, oil return passage; 302, oil supply passage; 303, oil groove; 400, bearing seat; 401, connecting flange; 500, centrifugal impeller; 600, gill sealing structure. DETAILED DESCRIPTION

[0018] The embodiments of the present application are described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered by the following.

[0019] Figure 1 is the schematic diagram of the structure of the axial diffuser in the prior art; Figure 2 is the front view of the axial diffuser structure of the preferred embodiment of the present application; Figure 3 is the A-direction sectional view of Figure 2 Figure 4 is the B-direction sectional view of Figure 2 Figure 5 is the C-direction sectional view of Figure 2 Figure 6 is the schematic diagram of the axial diffuser mounting state of the axial diffuser structure of the preferred embodiment of the present application; Figure 7 is the schematic diagram of the bleed air sealing of the axial diffuser structure of the preferred embodiment of the present application.

[0020] As Figure 1 and Figure 2 ​​​​​​As shown, the axial diffuser structure of the embodiment is applied to an auxiliary power device single-stage centrifugal compressor of an aero-engine, and comprises a base structure 100, a mounting base 200 arranged in the base structure 100 and coaxially arranged with the base structure 100, and a plurality of support plate structures 300 arranged in a radial direction and uniformly distributed in a circumferential direction. Two ends of each support plate structure 300 are connected to an outer wall of the mounting base 200 and an inner wall of the base structure 100, respectively, and at least three support plate structures 300 are arranged. The mounting base 200 is provided with a first mounting structure 201 and a second mounting structure 202 at two ends thereof. The mounting base 200 has an inner cavity for arranging a bearing seat 400. The first mounting structure 201 is used for connecting the bearing seat 400, and the second mounting structure 202 is used for connecting a guide vane. One support plate structure 300 is provided with an oil return channel 301 connected to the inner cavity of the mounting base 200. Another support plate structure 300 is provided with an oil supply channel 302 connected to the inner cavity of the mounting base 200.

[0021] The base structure 100 can be implemented according to the prior art axial diffuser structure, and will not be described in detail. It can be understood that, by coaxially arranging the mounting base 200 in the base structure 100, arranging the first mounting structure 201 and the second mounting structure 202 at two ends of the mounting base 200, arranging the bearing seat 400 in the inner cavity of the mounting base 200 and connecting the guide vane based on the mounting base 200, the bearing is arranged to support the rotating shaft of the centrifugal impeller 500 through the bearing seat 400, and the connection with the guide vane is realized based on the mounting base 200, without relying on a complex structure arranged on the casing for mounting. The casing structure between the axial diffuser and the guide vane is omitted, the structure is compact, the number of components is small, and the weight of the aero-engine is further reduced. By arranging at least three support plate structures 300 in a radial direction to connect the base structure 100 and the mounting base 200, on the one hand, the mounting base 200 is stably supported to ensure coaxial arrangement and further ensure the mounting precision of the shaft system and structures such as the casing and the guide vane, and on the other hand, the oil supply channel 302 and the oil return channel 301 are arranged based on the support plate structure 300, the two groups of channels are located in different support plates and are connected to the oil circuit of the bearing seat 400 in the inner cavity of the mounting base 200 to be connected to the bearing position. The integrated arrangement of the oil supply channel 302 and the oil return channel 301 based on the axial diffuser structure further realizes the structural height integration, realizes the oil injection cooling, lubrication and oil return of the auxiliary power device, and simultaneously makes the axial space of the aero-engine more abundant based on the axial diffuser structure. The reduction in the number of components makes the weight of the aero-engine lighter, and is more conducive to the optimization design of the power part of the aero-engine.

[0022] In some preferred embodiments, reference is made to Figure 3 and Figure 4The axial diffuser structure further comprises a bearing seat 400 mounted in the inner cavity of the mounting base 200 and connected with the first mounting structure 201. The bearing seat 400 is provided with a lubricating oil supply oil way and an oil return oil way. The lubricating oil supply oil way is used to cooperate with the oil supply channel 302 and the bearing mounting position of the inner ring surface of the bearing seat 400 respectively. The oil return oil way is used to cooperate with the oil return channel 301 and the bearing mounting position of the inner ring surface of the bearing seat 400. It can be understood that the bearing seat 400 realizes oil supply from the outside to the internal bearing position through the axial diffuser and oil return by cooperating with the oil supply channel 302 and the bearing mounting position of the inner ring surface of the bearing seat 400 and cooperating with the oil return channel 301 and the bearing mounting position of the inner ring surface of the bearing seat 400. The structure is compact. Further, the inner ring surface of the mounting base 200 and / or the outer wall of the bearing seat 400 is provided with an oil groove 303 with a certain arc along the circumference, so that the oil supply channel 302 and the lubricating oil supply oil way are connected and cooperated after the bearing seat 400 is mounted. Similarly, two groups of oil grooves 303 can be provided to be connected and cooperated with the oil supply channel 302 and the lubricating oil supply oil way and the oil return oil way and the oil return channel 301 respectively.

[0023] In some preferred embodiments, with reference to Figure 6 One end of the bearing seat 400 is provided with a connecting flange 401 for cooperating and connecting with the first mounting structure 201. The bearing seat 400 is embedded in the inner cavity of the mounting base 200. The connecting flange 401 is arranged on the outer wall of the end of the bearing seat 400. The bearing seat 400 is embedded in the inner cavity of the mounting base 200 until the connecting flange 401 cooperates with the first mounting structure 201, and is fastened and connected by bolt locking. The structure is simple, compact and reasonable. It can be understood that the first mounting structure 201 is a mounting hole arranged on one end surface of the mounting base 200. Similarly, the second mounting structure 202 is a mounting hole arranged on the other end surface of the mounting base 200 and matched with the guide.

[0024] In some preferred embodiments, with reference to Figure 2 The axial diffuser structure further comprises a third mounting structure 101 arranged on the end surface of the axial diffuser. A plurality of third mounting structures 101 are uniformly distributed along the circumference of the axial diffuser. The third mounting structure 101 is used to connect with the combustion chamber large elbow. It should be understood that the third mounting structure 101 is arranged on the end surface of the base structure 100 facing the centrifugal impeller 500 to be connected with the combustion chamber large elbow, so as to provide support for the combustion chamber large elbow, fix the integrated part of the axial diffuser structure to the parting box structure, and further simplify the overall structure and reduce the number of parts.

[0025] In some preferred embodiments, with reference to Figure 5 and Figure 7, the labyrinth seal structure 600 is arranged between the axial diffuser and the centrifugal impeller 500, the mounting base 200 is provided with a bleed air seal structure for guiding the gas in the combustion chamber to the position of the labyrinth seal structure 600 between the axial diffuser and the centrifugal impeller 500 to form a pressure difference at both ends of the labyrinth seal structure 600 to prevent oil leakage; it should be understood that by arranging the labyrinth seal structure 600 and the bleed air seal structure, high-pressure gas is guided from the combustion chamber to the labyrinth seal structure 600, a pressure difference is formed at both ends of the labyrinth seal structure 600 to prevent oil leakage, and the guided gas can be recycled in the centrifugal impeller 500 again; wherein the labyrinth seal structure 600 can be realized by referring to the labyrinth seal ring in the prior art, and will not be described in detail.

[0026] In some preferred embodiments, referring to Figure 5 and Figure 7 , the bleed air seal structure comprises bleed air channels 203 arranged axially on the mounting base 200 and uniformly distributed circumferentially along the mounting base 200, and the bleed air channels 203 are used to guide the gas in the combustion chamber to the position of the labyrinth seal structure 600 between the axial diffuser and the centrifugal impeller 500; it can be understood that the mounting base 200 has a certain thickness, and by arranging the bleed air channels 203 axially through the mounting base 200 and uniformly distributed circumferentially along the mounting base 200, the high-pressure gas in the combustion chamber near one end of the guide vane can be guided to the position of the labyrinth seal structure 600 through the bleed air channels 203 under the action of pressure, thereby realizing bleed air sealing and forming a pressure difference at both ends of the labyrinth seal structure 600 to prevent oil leakage in the power part.

[0027] In some preferred embodiments, referring to Figures 2 to 4 , the support plate structure 300 provided with the oil return channel 301 is arranged in the lower half ring range of the axial diffuser structure in the mounted state, and the support plate structure 300 provided with the oil supply channel 302 is preferably arranged in the upper half ring range of the axial diffuser structure in the mounted state; it can be understood that by arranging the support plate structure 300 provided with the oil return channel 301 in the lower half ring range of the axial diffuser structure in the mounted state and preferably in the vertical position, the oil return channel 301 in the support plate structure 300 can return oil under the action of gravity without the need for additional pumping equipment, further simplifying the structure; similarly, although the oil supply has a supply pressure, arranging the support plate structure 300 provided with the oil supply channel 302 in the upper half ring range of the axial diffuser structure in the mounted state can also reduce the demand for oil supply pressure; wherein three support plate structures 300 are arranged in this embodiment to meet the support requirements and simplify the structure, and the circumferential angles between the three support plates are 120°, so when the support plate structure 300 provided with the oil return channel 301 is arranged vertically in the lower half ring range of the axial diffuser structure, the support plate structure 300 provided with the oil supply channel 302 must be located in the upper half ring range of the axial diffuser structure.

[0028] In some preferred embodiments, referring to Figure 2 and Figure 3 The inner wall of the axial diffuser structure is circumferentially uniformly distributed with the fourth mounting structure 102 for connecting with the combustor generator casing, wherein the fourth mounting structure 102 penetrates the wall surface of the base structure 100 of the axial diffuser structure to connect with the combustor generator casing located outside the outer wall thereof; that is, the axial diffuser structure realizes the integrated arrangement of the connection of the combustor elbow, the combustor generator casing, and the auxiliary power device, as well as the air sealing, oil supply, and oil return, and is highly integrated in structure, replaces part of the casing structure, and reduces the number of parts.

[0029] It should be noted that the axial diffuser structure has completed simulation and actual application test, and the mounting base and the support plate structure provided by the axial diffuser structure do not affect the performance of the original base structure of the axial diffuser.

[0030] On the other hand, the preferred embodiments of the present application also provide an aero-engine which applies the above-mentioned axial diffuser structure, and it can be understood that the aero-engine realizes the integrated multifunctional auxiliary power device by applying the above-mentioned axial diffuser structure, realizes the installation of the bearing seat 400 and the connection of the guide, realizes the support of the mounting base 200 and the injection lubrication oil supply and oil return of the auxiliary power device based on the multiple support plate structures 300, also realizes the air sealing to prevent oil leakage, fixes the combustor elbow and the combustor generator casing based on the axial diffuser structure, provides the axial force transmission effect, greatly simplifies the structure, reduces the weight, and reduces the number of parts.

[0031] On the other hand, the preferred embodiments of the present application also provide an aircraft which applies the above-mentioned axial diffuser structure, and it can be understood that the aircraft realizes the integrated multifunctional auxiliary power device by applying the above-mentioned axial diffuser structure, realizes the installation of the bearing seat 400 and the connection of the guide, realizes the support of the mounting base 200 and the injection lubrication oil supply and oil return of the auxiliary power device based on the multiple support plate structures 300, also realizes the air sealing to prevent oil leakage, fixes the combustor elbow and the combustor generator casing based on the axial diffuser structure, provides the axial force transmission effect, greatly simplifies the structure, reduces the weight, and reduces the number of parts.

[0032] In the description of the present application, it should be noted that the terms “upper”, “lower”, “front”, “rear”, and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0033] In the description of the application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connecting" should be understood in a broad sense, for example, it can be fixed connection, or detachable connection, or integrally connected; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0034] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An axial diffuser structure applied to a single-stage centrifugal compressor of an aeroengine auxiliary power unit, characterized in that, The axial diffuser structure comprises a base structure (100), a mounting base (200) arranged in the base structure (100) and coaxially arranged with the base structure (100), and a plurality of radially arranged and circumferentially uniformly distributed support plate structures (300), both ends of the support plate structure (300) are connected to the outer wall of the mounting base (200) and the inner wall of the base structure (100), and the support plate structure (300) is arranged at least three; both ends of the mounting base (200) are provided with a first mounting structure (201) and a second mounting structure (202); the mounting base (200) has an inner cavity for arranging a bearing seat (400), the first mounting structure (201) is used for connecting with the bearing seat (400), and the second mounting structure (202) is used for connecting with a guide; one of the support plate structures (300) is provided with an oil return channel (301) communicated to the inner cavity of the mounting base (200); another support plate structure (300) is provided with an oil supply channel (302) communicated to the inner cavity of the mounting base (200).

2. The axial diffuser structure of claim 1, wherein, The axial diffuser structure further comprises a bearing seat (400) mounted in the inner cavity of the mounting base (200) and connected with the first mounting structure (201), the bearing seat (400) is provided with a lubricating oil supply oil way and an oil return oil way, the lubricating oil supply oil way is used for cooperating with the oil supply channel (302) and the bearing mounting position of the inner ring surface of the bearing seat (400) respectively, and the oil return oil way is used for cooperating with the bearing mounting position of the inner ring surface of the bearing seat (400) of the oil return channel (301).

3. The axial diffuser structure of claim 2, wherein, One end of the bearing seat (400) is radially extended and provided with a connecting flange (401) used for cooperating with the first mounting structure (201).

4. The axial diffuser structure of claim 1, wherein, The axial diffuser structure further comprises a third mounting structure (101) arranged on the end face of the axial diffuser structure, a plurality of third mounting structures (101) are uniformly distributed along the circumference of the axial diffuser, and the third mounting structure (101) is used for connecting with a combustion chamber large elbow.

5. The axial diffuser structure of claim 1, wherein, A labyrinth seal structure (600) is arranged between the axial diffuser and a centrifugal impeller (500), the mounting base (200) is provided with an air guide sealing structure for guiding the gas in the combustion chamber to the position of the labyrinth seal structure (600) between the axial diffuser structure and the centrifugal impeller (500) to form a pressure difference at both ends of the labyrinth seal structure (600) to prevent oil leakage.

6. The axial diffuser structure of claim 5, wherein, The air guide sealing structure comprises an air guide channel (203) arranged in the mounting base (200) along the axial direction and uniformly distributed along the circumference of the mounting base (200), and the air guide channel (203) is used for guiding the gas in the combustion chamber to the position of the labyrinth seal structure (600) between the axial diffuser structure and the centrifugal impeller (500).

7. The axial diffuser structure of claim 1, wherein, The support plate structure (300) provided with the oil return channel (301) is located in the lower half ring range of the mounting state of the axial diffuser structure.

8. The axial diffuser structure of claim 1, wherein, The inner wall of the axial diffuser structure is circumferentially uniformly distributed with fourth mounting structures (102) for connecting with a combustor generator casing.

9. An aeroengine characterised in that, The axial diffuser structure of any one of claims 1-8 is used.

10. An aircraft, characterized in that The axial diffuser structure of any one of claims 1-8 is used.

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