A multi-system integrated support casing and aero-engine

Abstract

This invention discloses a multi-system integrated support casing and an aero-engine. The casing is located inside the combustion chamber and needs to operate stably and reliably under high temperature and high pressure conditions (maximum operating pressure exceeding 2.4 MPa, maximum operating temperature exceeding 1300℃). The support casing includes a casing body, within which a bearing cavity, a cooling air cavity, and an internal cavity are formed. One end of the internal cavity connects to the back cavity of the centrifugal impeller, and the other end connects to the high-pressure turbine for cooling. A sealing element separates the cooling air cavity and the internal cavity, forming a pressure relief chamber between them. A nozzle support supplies lubricating oil to the bearings. An elastic support supports the bearings and adjusts the fulcrum stiffness. The support casing of this application has a high degree of integration, and the designed secondary air system, heat insulation system, and support system can meet the requirements for stable and reliable operation of the rotor support structure under high temperature and high pressure conditions.

Description

Technical Field

[0001] This invention relates to the field of aero engines, and in particular to a multi-system integrated support casing located in a high-temperature and high-pressure environment inside the combustion chamber, and an aero engine containing the casing. Background Technology

[0002] For multi-rotor aero engines, a support point is often placed between the high-pressure compressor and the high-pressure turbine to support the high-pressure rotor. The engine combustion chamber is also typically located between the high-pressure compressor and the high-pressure turbine. Therefore, this support point needs to operate stably and reliably under high-temperature and high-pressure conditions. The support point requires a corresponding support casing, which houses bearings to support the rotor. To ensure stable operation of the bearings, they need to be lubricated with lubricating oil. In a certain type of turboprop engine, the highest temperature in the combustion chamber exceeds 1300℃, and the gas temperature in the high-pressure compressor on the left side of the combustion chamber and the high-pressure turbine on the right side exceeds 550℃. Therefore, to prevent coking of the lubricating oil (the coking temperature of lubricating oil is around 210℃), a heat insulation system and an air system are needed to isolate or reduce the high-temperature radiation from the combustion chamber and the heat transfer from the high-temperature and high-pressure gases in the compressor and turbine. Furthermore, due to the high turbine temperature, air needs to be drawn from the relatively cooler compressor to cool the turbine. The support casing located between the compressor and the turbine becomes an ideal air bleed channel. Traditional support casings often employ a combination of precision casting and welding processes, resulting in a complex structure, a large number of parts, and complex forming processes, leading to a low product qualification rate. Summary of the Invention

[0003] This invention provides a multi-system integrated support casing, designed and manufactured based on additive manufacturing processes, to solve the technical problem of stable operation of rotor support systems under high temperature and high pressure environments.

[0004] According to one aspect of the present invention, a multi-system integrated support casing is provided, comprising a support casing body, one end of which is connected to a high-pressure compressor, and the other end of which is connected to a high-pressure turbine. The support casing body contains a bearing cavity, a cooling gas cavity, and an internal cavity. The cooling gas cavity is located on the side of the support casing body near the combustion chamber and is used to communicate with the high-pressure compressor. The bearing cavity is located on the side of the support casing body away from the combustion chamber. One end of the internal cavity is used to communicate with the back cavity of a centrifugal impeller, and the other end is used to communicate with the interior of the high-pressure turbine. A sealing element is located inside the support casing body, with one sealing element at the end near the high-pressure compressor and one at the end near the high-pressure turbine. The sealing element separates the cooling gas cavity C1 and the internal cavity C3 of the support casing, forming a pressure relief cavity C2 between the cooling gas cavity C1 and the internal cavity C3. The pressure relief cavity C2 is used to communicate with a low-pressure turbine casing. Each sealing element has two first dynamic seals for sealing the pressure relief cavity C2.

[0005] By adopting the above technical solution, an independent cooling gas chamber C1 is established between the bearing cavity C0 and the external environment. Cooling gas can be introduced from a suitable pressure section of the high-pressure compressor through pipelines to cool the support casing. Gas is drawn from the back cavity of the centrifugal impeller of the high-pressure compressor through the internal cavity C3 of the support casing, and the gas introduced from the back cavity of the centrifugal impeller is used for internal cooling of the high-pressure turbine. The pressure relief chamber C2 is led to the low-pressure turbine casing through pipelines to cool the low-pressure turbine casing. The pressure of the pressure relief chamber C2 is lower than that of the cooling gas chamber C1, and the pressure of the cooling gas chamber C1 is lower than that of the back cavity of the centrifugal impeller C3. The temperature of the cooling gas chamber C1 is lower than that of the pressure relief chamber C2, and the temperature of the pressure relief chamber C2 is lower than that of the back cavity of the centrifugal impeller C3. The setting of the pressure relief chamber C2 avoids the direct influence of the high-temperature gas in the back cavity of the centrifugal impeller on the cooling gas chamber C1, thereby improving the cooling effect of the C1 chamber on the C0 chamber. While ensuring the cooling effect, the structure is relatively simple and easy to process and form.

[0006] Optionally, a lubrication system is provided within the support housing body. The lubrication system includes: a lubricating oil chamber located within the support housing body, with an oil supply pipe mounting seat located directly above the support housing body, the oil supply pipe mounting seat being connected to an oil supply pipe connected to the lubricating oil chamber; a nozzle bracket fixedly connected to the support housing, with a liquid guiding channel formed within the nozzle bracket, one end of the liquid guiding channel communicating with the lubricating oil chamber, and the other end of the liquid guiding channel opening towards the lubricating oil collector of the bearing; and a return oil pipe located on a return oil pipe mounting seat directly below the support housing, the return oil pipe communicating with the bearing cavity, and the return oil pipe being used to connect to an external oil pump.

[0007] By adopting the above technical solution, external lubricating oil can enter the lubricating oil chamber through the oil supply pipe, then enter the liquid guiding channel, and then be sprayed into the bearing's lubricating oil collector through the liquid guiding channel to lubricate the bearing under the ring. The lubricating oil finally collects in the bearing cavity under the action of gravity, and then the lubricating oil in the bearing cavity is extracted from the return oil pipe by the external oil pump to complete the circulation of the lubricating oil, which can lubricate the bearing and remove the heat in the bearing.

[0008] Optionally, the support housing body is provided with an elastic support for supporting the bearing. The elastic support includes: a mounting flange connected to the nozzle bracket and the support housing; a support seat, which is annular, with its inner wall cooperating with the outer ring of the bearing to support the bearing, and a 0.2mm gap between its outer wall and the support housing; and ribs connecting the mounting flange and the support seat, with multiple ribs arranged circumferentially along the support seat.

[0009] By adopting the above technical solution, the rib structure reduces the stiffness of the elastic support, thereby adjusting the support stiffness of the fulcrum to meet the stiffness requirements of the rotor dynamics for the fulcrum; the gap between the outer wall of the support seat and the support casing flows with the lubricating oil cavity to form a squeezed oil film layer, which can absorb the vibration energy of the rotor and play a role in reducing the vibration of the rotor.

[0010] Optionally, a heat shield is provided on the side of the support casing body near the combustion chamber, forming a first protective layer. The side wall of the cooling gas chamber forms a second protective layer, and the side wall of the bearing cavity forms a third protective layer. An elastic support for supporting the bearing is provided in the support casing body, forming a fourth protective layer. The heat radiation from the combustion chamber passes through the first, second, third, and fourth protective layers in sequence before entering the bearing.

[0011] By adopting the above technical solution, the outer heat shield and the side wall structure of the air system cavity are used to form four protective layers between the bearing and the combustion chamber, which attenuate the heat radiation from the combustion chamber layer by layer. The radiant heat reaching the bearing can be basically ignored. Combined with the air system cooling, the bearing operating temperature can be guaranteed to meet the design requirements, and the lubricating oil in the bearing cavity will not coke.

[0012] Optionally, the support casing body has a first mounting edge at the end near the high-pressure compressor, which is used to connect to the high-pressure compressor; the support casing body has a fifth mounting edge at the end near the high-pressure turbine, which is connected to the high-pressure turbine; a second mounting edge, a third mounting edge, and a fourth mounting edge are distributed sequentially between the first and fifth mounting edges, the second and third mounting edges are used to fix the sealing element, and the fourth mounting edge is used to fix the nozzle bracket and the elastic support.

[0013] By adopting the above technical solution, the high-speed rotation of the rotor will apply a dynamic load to the bearing, and the dynamic load will be transmitted to the fourth mounting side through the elastic support; the pressure load on the two sealing parts will be transmitted to the support casing body through the second and third mounting sides; part of the load of the high-pressure turbine will be transmitted to the support casing body through the fifth mounting side; and the bearing capacity of the second, third, fourth, and fifth mounting sides will finally be transmitted to the high-pressure compressor through the first mounting side.

[0014] Optionally, two second dynamic seals are provided between the bearing cavity and the cooling gas cavity. One second dynamic seal is located at the end of the bearing near the high-pressure compressor, and the other second dynamic seal is located at the end of the bearing near the high-pressure turbine. The second dynamic seals are carbon seals.

[0015] By adopting the above technical solution, the two carbon sealing devices isolate the bearing cavity and the cooling gas cavity. The pressure in the cooling gas cavity is higher than that in the bearing cavity, which avoids the leakage of lubricating oil from the bearing cavity. The carbon sealing on both sides of the bearing eliminates the risk of metal shavings entering the bearing raceway and causing damage that may be caused by the grate sealing. While sealing the bearing cavity, it can also protect the bearing.

[0016] Optionally, mounting grooves are formed on the nozzle bracket and the support housing body, respectively, and the second dynamic seal is respectively disposed in the mounting groove.

[0017] By adopting the above technical solution, the nozzle bracket and the support casing body can respectively support and fix the second dynamic seal, so that the second seal can remain stable when the rotor rotates at high speed and seal the bearing cavity C0.

[0018] Optionally, an annular groove is provided on the side of the nozzle bracket that contacts the mounting flange of the elastic support, and an end face sealing ring is provided in the annular groove.

[0019] By adopting the above technical solution, the annular groove can play a positioning role for the end face sealing ring, and the end face sealing ring can seal between the nozzle bracket and the mounting flange to prevent lubricating oil from leaking into the cooling air chamber C2.

[0020] Optionally, the first dynamic seal includes a stepped honeycomb ring disposed on the sealing member and sealing grates disposed on the rotor, with the honeycomb ring and sealing grates in clearance fit.

[0021] By adopting the above technical solution, the first dynamic seal is a non-contact seal, which limits the leakage of bleed air while ensuring a certain pressure difference.

[0022] Optionally, the support casing body is manufactured using additive manufacturing technology, forming a single piece with a simple structure, high integration, and short development cycle.

[0023] Another aspect of the invention discloses an aircraft engine including the aforementioned support casing.

[0024] In summary, this application includes at least one of the following beneficial technical effects:

[0025] 1. The support casing body adopts additive manufacturing process and is integrally formed, resulting in high integration of the casing, fewer overall parts, and high reliability;

[0026] 2. The bleed air cooling system can effectively cool the support casing. Combined with the multi-layer heat radiation isolation of the support casing, it can enable the bearing to work stably and reliably in a low-temperature environment under high temperature and high pressure, and prevent the lubricating oil in the bearing cavity from coking.

[0027] 3. This air system can meet the compressor's bleed air requirements for turbine cooling.

[0028] 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

[0029] 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:

[0030] Figure 1 This is a schematic diagram of the position of the support casing inside the engine according to an embodiment of the present invention;

[0031] Figure 2 This is a schematic diagram of the overall structure of the support casing according to an embodiment of the present invention;

[0032] Figure 3 This is a cross-sectional structural schematic diagram of the support casing according to an embodiment of the present invention;

[0033] Figure 4 This is a schematic diagram of the path of cooling induced air from the high-pressure compressor into the support casing according to an embodiment of the present invention;

[0034] Figure 5 This is a schematic diagram of the gas discharge path from the pressure relief chamber in an embodiment of the present invention;

[0035] Figure 6 This is a schematic diagram of the path of gas from the back cavity of the centrifugal impeller of the high-pressure compressor into the support casing, and then into the high-pressure turbine, according to an embodiment of the present invention.

[0036] Figure 7 This is a schematic diagram of the nozzle bracket supporting the housing according to an embodiment of the present invention;

[0037] Figure 8This is a schematic diagram of the elastic support structure of the support casing in an embodiment of the present invention;

[0038] Figure 9 This is a schematic diagram of the heat insulation structure of the support casing in an embodiment of the present invention;

[0039] Figure 10 This is a schematic diagram of the support casing mounting structure according to an embodiment of the present invention.

[0040] Legend:

[0041] 1. First protective layer; 2. Second protective layer; 3. Third protective layer; 4. Fourth protective layer; 5. Support casing body; 6. Sealing element; 7. High-pressure compressor; 8. Combustion chamber; 9. High-pressure turbine; 10. Oil supply pipe; 11. Lubricating oil chamber; 12. Nozzle support; 13. Oil return pipe; 14. Elastic support; 15. Mounting flange; 16. Support seat; 17. Rib; 18. End face sealing ring; 19. Heat insulation cover; 20. First dynamic seal; 21. Second 22. Dynamic sealing; 23. First mounting edge; 24. Bearing; 25. Fluid guide channel inlet; 26. Nozzle; 27. Second mounting edge; 28. Third mounting edge; 29. ​​Fourth mounting edge; 20. Fifth mounting edge; 31. Pressure relief channel; 32. Cooling gas inlet channel; 33. High-pressure turbine cooling gas channel; 34. Oil supply pipe mounting seat; 35. Oil return pipe mounting seat; C0. Bearing cavity; C1. Cooling gas cavity; C2. Pressure relief cavity; C3. Internal cavity of the support casing. Detailed Implementation

[0042] 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.

[0043] The following is in conjunction with the appendix Figure 1-10 This application will be described in further detail.

[0044] On one hand, embodiments of this application disclose a multi-system integrated support casing placed in a high-temperature and high-pressure environment inside the combustion chamber, referring to... Figure 1The support casing is located inside the combustion chamber 8, between the high-pressure compressor 7 and the high-pressure turbine 9, providing support for the high-pressure rotor pivot and cooling channels for the high-pressure and low-pressure turbines. This support casing is applied to a civilian turboprop engine with a compressor outlet maximum pressure exceeding 2.4 MPa and a high-pressure turbine 9 inlet maximum operating temperature exceeding 1300°C. This support casing provides an advanced solution for the load-bearing, lubrication, cooling, sealing, bleed air, and vibration damping functions required for supporting a gas turbine engine under high temperature and high pressure conditions. To ensure safe rotor operation, the support casing requires a support and vibration damping system with a certain rigidity. To ensure the safe operation of the pivot bearing 23, the support casing needs to circulate lubricating oil for cooling. To prevent lubricating oil coking, the support casing needs to isolate or reduce the high-temperature radiation from the combustion chamber 8 and the heat transfer from the high-temperature gases of the high-pressure compressor 7 and high-pressure turbine 9. To prevent lubricating oil leakage, the support casing needs to be equipped with an effective sealing structure. To reduce the operating temperature of the high-pressure and low-pressure turbines, the support casing needs to provide air source cooling channels.

[0045] Reference Figure 2 and Figure 3 The support housing includes a support housing body 5 and a sealing element 6, an elastic support 14, and a nozzle bracket 12 disposed within the support housing body 5. The support housing body 5 is designed and manufactured using additive manufacturing technology, which can improve product yield and development cycle while reducing structural complexity.

[0046] Reference Figure 4-6 The support casing body 5 is separated by two carbon seals 21 to form a bearing cavity C0, and by two sealing members 6 to form a cooling air cavity C1 and an internal cavity C3. The cooling air cavity C1 is located on the side of the support casing body 5 near the combustion chamber 8 and is used to communicate with the high-pressure compressor 7. The bearing cavity C0 is located on the side of the support casing body 5 away from the combustion chamber 8. One end of the internal cavity C3 is used to communicate with the back cavity of the centrifugal impeller, and the other end is used to communicate with the interior of the high-pressure turbine 9. One sealing member 6 is provided at the end near the high-pressure compressor 7 and one at the end near the high-pressure turbine 9. The sealing member 6 separates the internal space of the support casing, so that a pressure relief cavity C2 is formed in the support casing body 5 between the cooling air cavity C1 and the internal cavity C3. The pressure relief cavity C2 is used to communicate with the low-pressure turbine casing.

[0047] Reference Figure 4-6By establishing an independent cooling gas chamber C1 between the bearing cavity C0 and the external environment, cooling gas can be introduced from the appropriate pressure part of the high-pressure compressor 7 through pipeline to cool the support casing. There are two induced gas intake points on the circumference of the support casing body 5, located at the 1 o'clock and 7 o'clock positions respectively. Gas is introduced from the back cavity of the centrifugal impeller of the high-pressure compressor 7 through the internal cavity C3 of the support casing. There are two induced gas intake points on the circumference of the support casing body 5, located at the 3 o'clock and 9 o'clock positions respectively. The gas introduced from the back cavity of the centrifugal impeller is used for internal cooling of the high-pressure turbine 9. The pressure relief chamber C2 is introduced to the low-pressure turbine casing through pipeline as cooling gas. There are two induced gas intake points on the circumference of the support casing body 5, located at the 4 o'clock and 10 o'clock positions respectively. The pressure in the pressure relief chamber C2 is lower than that in the cooling gas chamber C1, and the pressure in the cooling gas chamber C1 is lower than that in the centrifugal impeller back cavity pressure C3. The temperature in the cooling gas chamber C1 is lower than that in the pressure relief chamber C2, and the temperature in the pressure relief chamber C2 is lower than that in the centrifugal impeller back cavity pressure C3. The design of chamber C2 avoids the direct influence of the high-temperature gas in the centrifugal impeller back cavity on the cooling gas chamber C1, thereby improving the cooling effect of chamber C1 on chamber C0.

[0048] Reference Figure 3 and Figure 7 The bearing cavity C0 houses a bearing 23 for supporting the rotor. The bearing 23 is a high-speed bearing that generates a lot of heat during operation, requiring a supply of lubricating oil for cooling. The support casing body 5 houses a lubrication system, which includes an oil supply pipe 10, a lubricating oil chamber 11, a nozzle bracket 12, and a return oil pipe 13. The lubricating oil chamber 11 is located inside the support casing body 5. An oil supply pipe 10 connected to the lubricating oil chamber 11 is mounted on the oil supply pipe mounting seat 33 directly above the support casing body 5. The nozzle bracket 12 is fixedly connected to the support casing. A liquid guiding channel is formed inside the nozzle bracket 12. One end of the liquid guiding channel has a liquid guiding channel inlet 24, which communicates with the lubricating oil chamber 11. A nozzle 25 is provided at the other end of the liquid guiding channel, facing the lubricating oil collector to lubricate the bearing 23 under the ring. The return oil pipe 13 is located on the return oil pipe mounting seat 34 directly below the support casing body 5. The return oil pipe 13 communicates with the bearing cavity C0 and is used to connect to an external oil pump.

[0049] External lubricating oil enters the lubricating oil chamber 11 through the oil supply pipe 10, then enters the liquid guiding channel, and finally is sprayed onto the lubricating oil collector through the liquid guiding channel nozzle 25, providing ring lubrication for the bearing 23. The lubricating oil eventually collects in the bearing cavity C0 under gravity, and then the lubricating oil in the bearing cavity C0 is drawn out from the return oil pipe 13 by an external oil pump, completing the circulation of the lubricating oil. This lubrication of the bearing 23 and removal of heat from the bearing 23 are achieved. Most of the lubricating oil is sprayed into the bearing 23 through the lubricating oil collector of the rotor via the nozzle 25, a small portion directly enters the bearing cavity C0, and a small portion enters the oil film cavity formed by the support casing 5 and the elastic support 14. The lubricating oil after cooling the bearing 23 and the lubricating oil in the oil film cavity both eventually enter the bearing cavity C0, where a mixture of oil gas and liquid oil coexists. Due to gravity, it accumulates directly below and is drawn back to the oil tank by the oil pump through the return oil pipe 13 directly below. To prevent lubricating oil from leaking to the outside of the oil chamber, O-ring rubber seals are designed at each interface. Due to the high temperature, the oil supply pipe 10, the oil return pipe 13 and the support casing body 5 are sealed by the end face of the C-type metal sealing ring.

[0050] Reference Figure 8 The support casing 5 contains an elastic support 14 for supporting the bearing 23. The elastic support 14 includes a mounting flange 15, a support seat 16, and ribs 17. The mounting flange 15 is fixedly connected to the nozzle bracket 12. The support seat 16 is annular, and its inner wall mates with the outer ring of the bearing 23 to support it. The ribs 17 connect the mounting flange 15 and the support seat 16. Multiple ribs 17 are arranged circumferentially along the support seat 16. By selecting appropriate ribs 17 in terms of quantity, width, and thickness, the stiffness of the elastic support 14 can be changed, thereby adjusting the support stiffness of the fulcrum to meet the rotor dynamics requirements for the fulcrum. There is a 0.2mm gap between the outer wall of the support seat 16 and the support casing 5. This gap communicates with the lubrication cavity to allow lubricating oil to enter the gap, forming a squeezed oil film layer to absorb the vibration energy of the rotor and reduce the rotor vibration amplitude. An annular groove is provided on the side of the nozzle bracket 12 that contacts the mounting flange 15 of the elastic support 14. An end face sealing ring 18 is provided in the annular groove to prevent lubricating oil from leaking from the end face into the cooling air chamber C2.

[0051] Reference Figure 9A heat insulation cover 19 is provided on the side of the support casing body 5 near the combustion chamber 8, forming a first protective layer 1. The side wall of the cooling air chamber C1 forms a second protective layer 2, and the side wall of the bearing cavity C0 forms a third protective layer 3. An elastic support 14 for supporting the bearing 23 is provided inside the support casing body 5, forming a fourth protective layer 4. The heat radiation from the combustion chamber 8 passes through the first protective layer 1, the second protective layer 2, the third protective layer 3, and the fourth protective layer 4 in sequence before entering the bearing 23. The four protective layers formed between the bearing 23 and the combustion chamber 8 attenuate the heat radiation from the combustion chamber 8 layer by layer. The radiant heat reaching the bearing 23 is negligible. Combined with air system cooling, it can be ensured that the operating temperature of the bearing 23 meets the design requirements, and the lubricating oil in the bearing cavity C0 does not coke.

[0052] Each sealing element is provided with two first dynamic seals 20 for sealing the pressure relief chamber C2. The first dynamic seal 20 includes a honeycomb ring disposed on the sealing element 6 and sealing grates disposed on the rotor, with the honeycomb ring and sealing grates in clearance fit. Two second dynamic seals 21 are disposed between the bearing chamber C0 and the cooling gas chamber C1. An installation groove is formed on the nozzle bracket 12, and the second dynamic seals 21 are disposed in the installation groove. One second dynamic seal 21 is located at the end of the bearing 23 near the high-pressure compressor 7, and the other second dynamic seal 21 is located at the end of the bearing 23 near the high-pressure turbine 9. The second dynamic seals 21 are carbon seals. The carbon seal uses a graphite ring in direct contact with the rotor to seal, which can both prevent leakage and avoid damage to the rotating parts.

[0053] Reference Figure 10 The support casing body 5 has a first mounting edge 22 at the end near the high-pressure compressor 7. All the load on the support casing body 5 is transmitted to the high-pressure compressor 7 through the first mounting edge 22. The support casing body 5 has a fifth mounting edge 29 at the end near the high-pressure turbine 9, which connects to the high-pressure turbine 9 and transmits part of the load of the high-pressure turbine 9 to the support casing body 5. Between the first mounting edge 22 and the fifth mounting edge 29, the second mounting edge 26, the third mounting edge 27 and the fourth mounting edge 28 are distributed in sequence. The second mounting edge 26 and the third mounting edge 27 are used to fix the two sealing parts 6 and transmit the pressure load on the sealing parts; the fourth mounting edge (28) is used to fix the nozzle bracket (12) and the elastic support (14). The rotor radial load is transmitted to the elastic support 14 and the support casing body 5 through the bearing 23. The rotor radial vibration energy can be absorbed by the oil film in the oil film cavity and play a role in vibration reduction.

[0054] This application also discloses an aircraft engine, including the aforementioned multi-system integrated support casing.

[0055] 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. A multi-system integrated support housing, characterized in that, include: The support casing body (5) has one end for connection to the high-pressure compressor (7) and the other end for connection to the high-pressure turbine (9). The support casing body (5) has a bearing cavity (C0), a cooling gas cavity (C1) and an internal cavity (C3) formed inside. The cooling gas cavity (C1) is located on the side of the support casing body (5) near the combustion chamber (8) and is used to communicate with the high-pressure compressor (7). The bearing cavity (C0) is located on the side of the support casing body (5) away from the combustion chamber (8). One end of the internal cavity (C3) is used to communicate with the back cavity of the centrifugal impeller of the high-pressure compressor (7) and the other end is used to communicate with the inside of the high-pressure turbine (9). A sealing element (6) is located inside the support casing body (5). One sealing element (6) is provided at one end near the high-pressure compressor (7) and one end near the high-pressure turbine (9). The sealing element (6) separates the cooling air chamber (C1) and the internal cavity (C3) of the support casing, so that a pressure relief chamber (C2) is formed between the cooling air chamber (C1) and the internal cavity (C3) of the support casing. The pressure relief chamber (C2) is used to communicate with the low-pressure turbine casing. Each sealing element (6) is provided with a first dynamic seal (20) for sealing the pressure relief chamber (C2). The pressure relief chamber is used to communicate with the low-pressure turbine casing or the external low-pressure area of ​​the engine. Under working conditions, the pressure in the pressure relief chamber is less than the pressure in the cooling air chamber, and the pressure in the cooling air chamber is less than the pressure in the back cavity of the centrifugal impeller connected to the internal cavity of the support casing.

2. The multi-system integrated support housing according to claim 1, characterized in that, The support housing body (5) is provided with a lubrication system, which includes: The lubricating oil chamber is located inside the support casing body (5). The support casing body (5) is provided with an oil supply pipe mounting seat (33) and an oil return pipe mounting seat (34). The oil supply pipe mounting seat (33) is connected to an oil supply pipe that is connected to the lubricating oil chamber. The nozzle bracket (12) is fixedly connected to the support housing body (5). A liquid guiding channel is formed inside the nozzle bracket (12). One end of the liquid guiding channel is connected to the lubricating oil chamber (11), and the other end of the liquid guiding channel is opened for the lubricating oil collector facing the bearing (23). The oil return pipe (13) is installed on the oil return pipe (13) mounting seat of the supporting casing body (5). The oil return pipe (13) is connected to the bearing (23) cavity and is used to connect to an external oil pump.

3. The multi-system integrated support housing according to claim 1, characterized in that, The support housing body (5) is provided with an elastic support (14) for supporting the bearing (23), the elastic support (14) comprising: Mounting flange (15) is connected to nozzle bracket (12) and support housing; The support seat (16) is annular. The inner wall of the support seat (16) is fitted with the outer ring of the bearing (23) to support the bearing (23). There is a gap between the outer wall and the support housing. Ribs (17) are connected to the mounting flange (15) and the support (16). Multiple ribs (17) are provided around the support (16).

4. The multi-system integrated support housing according to claim 1, characterized in that: A heat shield (19) is provided on the side of the support casing body (5) near the combustion chamber (9). The heat shield (19) forms a first protective layer (1). The side wall of the cooling air chamber (C1) forms a second protective layer (2). The side wall of the bearing chamber (C0) forms a third protective layer (3). An elastic support (14) for supporting the bearing (23) is provided inside the support casing body (5). The elastic support (14) forms a fourth protective layer (4). The heat radiation in the combustion chamber (9) passes through the first protective layer (1), the second protective layer (2), the third protective layer (3) and the fourth protective layer (4) in sequence before entering the bearing (23).

5. The multi-system integrated support housing according to claim 1, characterized in that, The support casing body (5) has a first mounting edge (22) at one end near the high-pressure compressor (7), which is used to connect with the high-pressure compressor (7); the support casing body (5) has a fifth mounting edge (29) at one end near the high-pressure turbine (9), which is connected with the high-pressure turbine (9); a second mounting edge (26), a third mounting edge (27) and a fourth mounting edge (28) are distributed between the first mounting edge (22) and the fifth mounting edge (29), the second mounting edge (26) and the third mounting edge (27) are used to fix the two sealing parts (6), and the fourth mounting edge (28) is used to fix the nozzle bracket (12) and the elastic support (14).

6. The multi-system integrated support housing according to claim 1, characterized in that, Optionally, two second dynamic seals (21) are provided between the bearing cavity (C0) and the cooling gas cavity (C1). One second dynamic seal (21) is located at the end of the bearing (23) near the high-pressure compressor (7), and the other second dynamic seal (21) is located at the end of the bearing (23) near the high-pressure turbine (8). The second dynamic seal (21) is a carbon seal.

7. The multi-system integrated support housing according to claim 6, characterized in that, Mounting grooves are formed on the nozzle bracket (12) and the support housing body (5), respectively, and the second dynamic seal (21) is respectively disposed in the mounting groove.

8. The multi-system integrated support housing according to claim 1, characterized in that, The first dynamic seal (20) includes a stepped honeycomb ring disposed on the sealing member (6) and sealing grates disposed on the rotor, with the honeycomb ring and sealing grates in clearance fit.

9. The multi-system integrated support housing according to claim 4, characterized in that, The support casing body (5) is manufactured using additive manufacturing technology.

10. An aircraft engine, characterized in that, Includes the multi-system integrated support housing as described in any one of claims 1-9.

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