Axial diffuser structure, aeroengine and aircraft

Abstract

The application discloses an axial diffuser structure, an aero-engine and an aircraft. The axial diffuser structure comprises 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. The two ends of each support plate structure are respectively connected to the outer wall of the mounting base and the inner wall of the base structure, and at least three support plate structures are arranged. The two ends of the mounting base are respectively provided with a first mounting structure and a second mounting structure. The mounting base has an inner cavity. The first mounting structure is used for connecting with a bearing seat, and the second mounting structure is used for connecting with a guide. One support plate structure is provided with an oil return channel which is communicated to the inner cavity of the mounting base. Another support plate structure is provided with an oil supply channel which is communicated to the inner cavity of the mounting base. The axial diffuser structure provides mounting interfaces for the bearing seat and the guide, realizes integrated arrangement of the oil inlet and return channels, realizes structural height integration, and realizes oil injection cooling, lubrication and oil return of the power device.

Description

Technical Field

[0001] This invention relates to the field of auxiliary power unit technology for aero engines, and in particular, to an axial diffuser structure. Furthermore, this invention also relates to an aero engine and aircraft comprising the aforementioned axial diffuser structure. Background Technology

[0002] Axial diffusers are a crucial component of auxiliary power units (APUs) for aero engines. Existing APU axial diffusers are mostly single-function parts, as referenced... Figure 1 Although simple in structure and easy to manufacture, it usually only has the function of speed reduction and pressure boosting. As the functional requirements of single-stage centrifugal auxiliary power units continue to be strengthened and enriched, and the performance requirements continue to improve, the existing single-function axial diffusers are usually unable to meet the many other functions of auxiliary power units, such as oil inlet / return and bleed air sealing. It is necessary to design a more complex mechanical system with more parts to meet the above-mentioned functions, which will increase the weight and the production cost.

[0003] Existing axial diffusers are typically designed as simple blade-type diffusers, primarily used to change the airflow direction and simultaneously decelerate and pressurize the airflow to meet the intake requirements of the combustion chamber. Existing axial diffusers generally lack injection lubrication supply channels, oil pump suction return channels, and gravity return channels. To meet weight and structural layout requirements, existing axial diffusers generally also lack bearing lubrication, cooling, and bleed air sealing structures. When the auxiliary power unit has high power and complex operating conditions, the requirements for axial force transmission are also higher. Existing axial diffusers generally lack bearing housing structures, therefore they cannot transmit axial force to the casing and mounting section, and usually can only transmit force through bearing housings or other structures. To meet these functions and requirements, a large number of parts are needed, resulting in heavy weight, high cost, complex disassembly and assembly processes, and poor reliability. Summary of the Invention

[0004] This invention provides an axial diffuser structure, an aero-engine, and an aircraft to solve the technical problem that existing compressors require complex mechanical systems with a large number of parts at the front and rear ends of the axial diffuser to meet the functions of auxiliary power unit oil inlet / return and bleed air sealing.

[0005] According to one aspect of the present invention, an axial diffuser structure is provided for use in a single-stage centrifugal compressor of an aero-engine auxiliary power unit. The structure includes a base structure, a mounting base disposed within the base structure and coaxially arranged with respect to the base structure, and support plate structures arranged radially and uniformly distributed circumferentially. The two ends of each support plate structure are respectively connected to the outer wall of the mounting base and the inner wall of the base structure. At least three support plate structures are provided. The two ends of the mounting base are respectively provided with a first mounting structure and a second mounting structure. The mounting base has an inner cavity for accommodating a bearing seat. The first mounting structure is used to connect with the bearing seat, and the second mounting structure is used to connect with a guide. One support plate structure is provided with a return oil channel communicating to the inner cavity of the mounting base. Another support plate structure is provided with a supply oil channel communicating to the inner cavity of the mounting base.

[0006] As a further improvement to the above technical solution, the axial diffuser structure also includes a bearing housing installed in the inner cavity of the mounting base and connected to the first mounting structure. The bearing housing is provided with a lubrication oil supply passage and a return oil passage. The lubrication oil supply passage is used to cooperate with the oil supply channel and the bearing mounting position on the inner ring surface of the bearing housing, respectively. The return oil passage is used to cooperate with the return oil channel and the bearing mounting position on the inner ring surface of the bearing housing.

[0007] As a further improvement to the above technical solution, one end of the bearing housing is provided with a connecting flange for connecting with the first mounting structure.

[0008] As a further improvement to the above technical solution, the axial diffuser structure also includes a third mounting structure disposed on the end face of the axial diffuser structure. A plurality of the third mounting structures are evenly distributed along the circumference of the axial diffuser, and the third mounting structure is used to connect to the combustion chamber large bend.

[0009] As a further improvement to the above technical solution, a grate sealing structure is provided between the axial diffuser and the centrifugal impeller, and an air induced sealing structure is provided on the mounting base. This structure is used to guide the gas from the combustion chamber to the position of the grate sealing structure between the axial diffuser structure and the centrifugal impeller, so as to form a pressure difference at both ends of the grate sealing structure to prevent oil leakage.

[0010] As a further improvement to the above technical solution, the induced gas sealing structure includes induced gas channels that are axially opened on the mounting base and uniformly distributed along the circumference of the mounting base. The induced gas channels are used to guide the gas from the combustion chamber to the grate sealing structure position between the axial diffuser structure and the centrifugal impeller.

[0011] As a further improvement to the above technical solution, the support plate structure with the oil return channel is located in the lower half-ring range of the axial diffuser structure in its installation state.

[0012] As a further improvement to the above technical solution, the inner wall of the axial diffuser structure is provided with a fourth mounting structure evenly distributed around the circumference for connecting with the combustion chamber generator casing.

[0013] According to another aspect of the invention, an aircraft engine is also provided, which includes the above-described axial diffuser structure.

[0014] According to another aspect of the invention, an aircraft is also provided, which includes the aforementioned axial diffuser structure.

[0015] The present invention has the following beneficial effects: This axial diffuser structure features a mounting base coaxially arranged within the base structure. A first mounting structure and a second mounting structure are respectively located at both ends of the mounting base. The first mounting structure connects to the bearing housing, and the second mounting structure connects to the guide vane. The bearing housing supports the centrifugal impeller shaft, and the connection to the guide vane is achieved based on the mounting base. This eliminates the need for a complex structure on the casing, omitting the casing structure between the axial diffuser and the guide vane. The structure is compact with fewer parts, further contributing to the lightweighting of aero-engines. At least three radially arranged support plates connect the base structure and the mounting base, providing stable support for the mounting base. The mounting base ensures coaxiality and further guarantees the installation accuracy of shaft connections and even structures such as the casing and guide vanes. On the other hand, based on the support plate structure, oil supply and return channels are set within the support plate structure. These two sets of channels are located on different support plates and are connected to the oil passage of the bearing housing within the mounting base cavity to reach the bearing position. This axial diffuser structure achieves integrated inlet and return oil channels, further realizing a high degree of structural integration. It enables the auxiliary power unit to achieve oil injection cooling, lubrication, and oil return. This axial diffuser structure also provides more axial space for the aero-engine, reduces the number of components, and makes it lighter, which is more conducive to the design improvement of the aero-engine power section. In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0016] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of the structure of an axial diffuser in the prior art; Figure 2This is a front view of the axial diffuser structure of a preferred embodiment of the present invention; Figure 3 yes Figure 2 Sectional view along direction A; Figure 4 yes Figure 2 Sectional view along direction B; Figure 5 yes Figure 2 Sectional view along line C; Figure 6 This is a schematic diagram of the axial diffuser installation state of a preferred embodiment of the axial diffuser structure of the present invention; Figure 7 This is a schematic diagram of the bleed-out seal of the axial diffuser structure according to a preferred embodiment of the present invention.

[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. Air intake channel; 300. Support plate structure; 301. Oil return channel; 302. Oil supply channel; 303. Oil tank; 400. Bearing housing; 401. Connecting flange; 500. Centrifugal impeller; 600. Grate sealing structure. Detailed Implementation

[0018] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0019] Figure 1 This is a schematic diagram of the structure of an axial diffuser in the prior art; Figure 2 This is a front view of the axial diffuser structure of a preferred embodiment of the present invention; Figure 3 yes Figure 2 Sectional view along direction A; Figure 4 yes Figure 2 Sectional view along direction B; Figure 5 yes Figure 2 Sectional view along line C; Figure 6 This is a schematic diagram of the axial diffuser installation state of a preferred embodiment of the axial diffuser structure of the present invention; Figure 7 This is a schematic diagram of the bleed-out seal of the axial diffuser structure according to a preferred embodiment of the present invention.

[0020] like Figure 1 and Figure 2As shown, the axial diffuser structure of this embodiment is applied to a single-stage centrifugal compressor of an aero-engine auxiliary power unit. It includes a base structure 100, a mounting base 200 disposed within the base structure 100 and coaxially arranged with it, and support plate structures 300 arranged radially and evenly distributed circumferentially. The two ends of the support plate structures 300 are respectively connected to the outer wall of the mounting base 200 and the inner wall of the base structure 100. At least three support plate structures 300 are provided. The two ends of the mounting base 200 are respectively provided with a first mounting structure 201 and a second mounting structure 202. The mounting base 200 has an inner cavity for mounting a bearing seat 400. The first mounting structure 201 is used to connect with the bearing seat 400, and the second mounting structure 202 is used for guide connection. One support plate structure 300 is provided with a return oil channel 301 communicating with the inner cavity of the mounting base 200; the other support plate structure 300 is provided with an oil supply channel 302 communicating with the inner cavity of the mounting base 200.

[0021] The base structure 100 can be implemented with reference to the existing axial diffuser structure, and will not be described in detail. It is understood that this axial diffuser structure uses a mounting base 200 coaxially arranged within the base structure 100. A first mounting structure 201 and a second mounting structure 202 are respectively provided at both ends of the mounting base 200. The first mounting structure 201 is used to connect with the bearing housing 400, which is located within the cavity of the mounting base 200. The second mounting structure 202 is used for guide connection. The bearing housing 400 supports the shaft of the centrifugal impeller 500, and the connection with the guide is achieved based on the mounting base 200. This eliminates the need for a complex structure on the casing for installation, omitting the casing structure between the axial diffuser and the guide. The structure is compact with fewer parts, further contributing to the lightweighting of aero-engines. The base structure is connected by at least three radially arranged support plate structures 300. The axial diffuser structure 100 and the mounting base 200 provide stable support for the mounting base 200 to ensure coaxiality and further guarantee the installation accuracy of shaft connections and even structures such as the casing and guide. On the other hand, based on the support plate structure 300, an oil supply channel 302 and an oil return channel 301 are set on the support plate structure 300. The two sets of channels are located on different support plates and are connected to the oil passage of the bearing seat 400 in the inner cavity of the mounting base 200 to connect to the bearing position. Based on this axial diffuser structure, the oil inlet and return channels 301 are integrated to further achieve a high degree of structural integration, realizing the oil injection cooling, lubrication and oil return of the auxiliary power unit. Based on this axial diffuser structure, the axial space of the aero-engine is more abundant, the number of parts is reduced, making it lighter and more conducive to the optimized design of the aero-engine power section.

[0022] In some preferred embodiments, reference Figure 3 and Figure 4The axial diffuser structure also includes a bearing housing 400 installed within the inner cavity of the mounting base 200 and connected to the first mounting structure 201. The bearing housing 400 is provided with a lubrication oil supply passage and a return oil passage. The lubrication oil supply passage is used to mate with the oil supply channel 302 and the bearing mounting position on the inner annular surface of the bearing housing 400, respectively. The return oil passage is used to mate with the return oil channel 301 and the bearing mounting position on the inner annular surface of the bearing housing 400. It can be understood that the bearing housing 400, by providing the lubrication oil supply passage and the return oil passage, mates with the oil supply channel 302 and the bearing mounting position on the inner annular surface of the bearing housing 400. The bearing mounting position of the bearing housing 400 is matched with the bearing mounting position of the bearing housing 400 and the bearing housing 200, so that the oil supply channel 302 and the lubrication oil supply circuit are connected and matched after the bearing housing 400 is installed. The structure is compact. Furthermore, the inner ring surface of the mounting base 200 and / or the outer wall of the bearing housing 400 are provided with an oil groove 303 of a certain arc along the circumference, so that the oil supply channel 302 and the lubrication oil supply circuit can be connected and matched after the bearing housing 400 is installed. Similarly, two sets of oil groove 303 structures can be provided, respectively for the connection and matching of the oil supply channel 302 and the lubrication oil supply circuit and the connection and matching of the return oil circuit and the return oil channel 301.

[0023] In some preferred embodiments, reference Figure 6 One end of the bearing housing 400 extends radially and is provided with a connecting flange 401 for connecting with the first mounting structure 201. The bearing housing 400 is embedded in the inner cavity of the mounting base 200, and the connecting flange 401 is provided on the outer wall of the end of the bearing housing 400. The bearing housing 400 is installed into the inner cavity of the mounting base 200 until the connecting flange 401 mates with the first mounting structure 201, and the connection is fastened by bolts. The structure is simple, compact and reasonable. It can be understood that the first mounting structure 201 is the mounting hole provided on one end face of the mounting base 200; similarly, the second mounting structure 202 is the mounting hole provided on the other end face of the mounting base 200 and matches the guide.

[0024] In some preferred embodiments, reference Figure 2 The axial diffuser structure also includes a third mounting structure 101 disposed on the end face of the axial diffuser. Multiple third mounting structures 101 are evenly distributed along the circumference of the axial diffuser. The third mounting structure 101 is used to connect with the combustion chamber large bend. It should be understood that the third mounting structure 101 is disposed on the end face of the base structure 100 facing the centrifugal impeller 500 for connection with the combustion chamber large bend, providing support for the combustion chamber large bend, so that the axial diffuser structure integrates the fixed casing structure, further simplifying the overall structure and reducing the number of parts.

[0025] In some preferred embodiments, reference Figure 5 and Figure 7A grate seal structure 600 is provided between the axial diffuser and the centrifugal impeller 500, and an air induced sealing structure is provided on the mounting base 200. These structures are used to draw gas from the combustion chamber to the grate seal structure 600 between the axial diffuser and the centrifugal impeller 500, creating a pressure difference across the two ends of the grate seal structure 600 to prevent oil leakage. It should be understood that by providing the grate seal structure 600 and the air induced sealing structure, high-pressure gas is drawn from the combustion chamber to the grate seal structure 600, creating a pressure difference across the two ends of the grate seal structure 600 to prevent oil leakage. Simultaneously, the drawn gas can re-enter the centrifugal impeller 500 for circulation. The grate seal structure 600 can be implemented with reference to the existing grate seal ring, and will not be elaborated upon further.

[0026] In some preferred embodiments, reference Figure 5 and Figure 7 The induced draft sealing structure includes induced draft channels 203 that are axially opened on the mounting base 200 and uniformly distributed circumferentially along the mounting base 200. The induced draft channels 203 are used to guide the gas from the combustion chamber to the position of the grate sealing structure 600 between the axial diffuser and the centrifugal impeller 500. It can be understood that the mounting base 200 has a certain thickness. By opening the induced draft channels 203 that are uniformly distributed circumferentially along the mounting base 200 and penetrate the mounting base 200 axially, the high-pressure gas from the combustion chamber near the guide end enters the induced draft channels 203 under pressure and is guided to the position of the grate sealing structure 600, thereby achieving induced draft sealing. A pressure difference is formed at both ends of the grate sealing structure 600 to prevent lubricating oil leakage from the power part.

[0027] In some preferred embodiments, reference Figures 2 to 4 The support plate structure 300 with the return oil channel 301 is located in the lower half-ring range of the axial diffuser structure installation state, and the support plate structure 300 with the supply oil channel 302 is preferably arranged in the upper half-ring range of the axial diffuser structure installation state. It can be understood that by arranging the support plate structure 300 with the return oil channel 301 in the lower half-ring range of the axial diffuser structure installation state, and preferably in a vertical position, the return oil channel 301 within the support plate structure 300 can return oil under gravity, eliminating the need for additional pumping equipment and further simplifying the structure. Similarly, although the sliding... The oil supply has a supply pressure, but the oil supply pressure requirement can also be reduced by arranging the support plate structure 300 with the oil supply channel 302 in the upper half ring range of the axial diffuser structure during installation. In this embodiment, three support plate structures 300 are set to meet the support requirements and simplify the structure. The circumferential angle between the three support plates is 120°. Therefore, when the support plate structure 300 with the return oil channel 301 is set vertically in the lower half ring range of the axial diffuser structure, the support plate structure 300 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, reference Figure 2 and Figure 3 The inner wall of the axial diffuser structure is uniformly provided with a fourth mounting structure 102 for connecting to the combustion chamber generator casing. The fourth mounting structure 102 penetrates the wall of the base structure 100 of the axial diffuser structure to connect with the combustion chamber generator casing located outside its outer wall. That is, this axial diffuser structure realizes the connection of the combustion chamber large bend, the combustion chamber generator casing, and the auxiliary power unit, as well as the integrated arrangement of bleed air sealing and oil supply and return. The structure is highly integrated, 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 practical application testing. The mounting base and support plate structure of the axial diffuser structure can be set without affecting the performance of the original foundation structure of the axial diffuser.

[0030] On the other hand, a preferred embodiment of the present invention also provides an aero-engine that utilizes the aforementioned axial diffuser structure. It is understood that by applying the aforementioned axial diffuser structure, this aero-engine integrates a multi-functional auxiliary power unit, realizes the installation of the bearing housing 400 and the connection of the guide, supports the mounting base 200 based on multiple support plate structures 300, and realizes the injection lubrication supply and return of oil to the auxiliary power unit. It also realizes the bleed air seal to prevent lubricating oil leakage. Based on this axial diffuser structure, the combustion chamber large bend and the combustion chamber generator casing are fixed, providing axial force transmission, greatly simplifying the structure, reducing weight, and reducing the number of parts.

[0031] On the other hand, a preferred embodiment of the present invention also provides an aircraft that uses the above-mentioned axial diffuser structure. It can be understood that by using the above-mentioned axial diffuser structure, the aircraft integrates a multi-functional auxiliary power unit, realizes the installation of the bearing housing 400 and the connection of the guide, supports the mounting base 200 based on multiple support plate structures 300, and realizes the injection lubrication supply and return of oil to the auxiliary power unit. It also realizes the bleed air seal to prevent lubricating oil leakage. Based on this axial diffuser structure, the combustion chamber large bend and the combustion chamber generator casing are fixed, providing axial force transmission, greatly simplifying the structure, reducing weight, and reducing the number of parts.

[0032] In the description of this invention, it should be noted that the terms "upper", "lower", "front", "rear", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0033] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0034] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An axial diffuser structure, applied to a single-stage centrifugal compressor in an aero-engine auxiliary power unit, characterized in that, The system includes a base structure (100), a mounting base (200) disposed within the base structure (100) and coaxially arranged with the base structure (100), and support plate structures (300) arranged radially and evenly distributed circumferentially. The two ends of each support plate structure (300) are respectively connected to the outer wall of the mounting base (200) and the inner wall of the base structure (100). At least three support plate structures (300) are provided. The two ends of the mounting base (200) are respectively provided with a first mounting structure (201) and a second mounting structure (202). The mounting base (200) has an inner cavity for mounting a bearing seat (400). The first mounting structure (201) is used to connect to the bearing seat (400), and the second mounting structure (202) is used for connecting to a guide. Each support plate structure (300) is provided with an oil return channel communicating with the inner cavity of the mounting base (200). (301); another support plate structure (300) is provided with an oil supply channel (302) communicating with the inner cavity of the mounting base (200); a grate sealing structure (600) is provided between the axial diffuser structure and the centrifugal impeller (500), and the mounting base (200) is provided with an air induced sealing structure for leading the gas in the combustion chamber to the grate sealing structure (600) between the axial diffuser structure and the centrifugal impeller (500). The position is such that a pressure difference is formed at both ends of the toothed sealing structure (600) to prevent oil leakage; the air duct sealing structure includes an air duct channel (203) that is opened axially on the mounting base (200) and evenly distributed circumferentially on the mounting base (200), the air duct channel (203) is used to guide the gas in the combustion chamber to the position of the toothed sealing structure (600) between the axial diffuser structure and the centrifugal impeller (500).

2. The axial diffuser structure according to claim 1, characterized in that, The axial diffuser structure also includes a bearing housing (400) installed in the inner cavity of the mounting base (200) and connected to the first mounting structure (201). The bearing housing (400) is provided with a lubrication oil supply passage and a return oil passage. The lubrication oil supply passage is used to cooperate with the oil supply channel (302) and the bearing mounting position on the inner ring surface of the bearing housing (400) respectively. The return oil passage is used to cooperate with the return oil channel (301) and the bearing mounting position on the inner ring surface of the bearing housing (400) respectively.

3. The axial diffuser structure according to claim 2, characterized in that, One end of the bearing housing (400) is provided with a connecting flange (401) for mating and connecting with the first mounting structure (201).

4. The axial diffuser structure according to claim 1, characterized in that, The axial diffuser structure has multiple third mounting structures (101) evenly distributed around its end face, which are used to connect to the combustion chamber large bend.

5. The axial diffuser structure according to claim 1, characterized in that, The support plate structure (300) with the oil return channel (301) is located in the lower half-ring range of the axial diffuser structure in the installation state.

6. The axial diffuser structure according to claim 1, characterized in that, The inner wall of the axial diffuser structure is uniformly provided with a fourth mounting structure (102) for connecting to the combustion chamber generator casing.

7. An aircraft engine, characterized in that, The application has the axial diffuser structure as described in any one of claims 1-6.

8. An aircraft, characterized in that, The application has the axial diffuser structure as described in any one of claims 1-6.

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