CN111219251B - Rear bearing frame of aero-engine - Google Patents
Rear bearing frame of aero-engine Download PDFInfo
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- CN111219251B CN111219251B CN201811414864.2A CN201811414864A CN111219251B CN 111219251 B CN111219251 B CN 111219251B CN 201811414864 A CN201811414864 A CN 201811414864A CN 111219251 B CN111219251 B CN 111219251B
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- flow passage
- mounting edge
- bearing frame
- bearing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Support Of The Bearing (AREA)
Abstract
The invention provides a rear bearing frame of an aircraft engine, which comprises an outer casing, a front-section inner flow passage, a rear-section inner flow passage and an elastic bearing seat, wherein the outer casing is provided with a plurality of bearing support plates penetrating through the flow passages, the front end of the inner side of each bearing support plate is provided with a front-end mounting edge, and the rear end of each bearing support plate is provided with a rear-end mounting edge; the lower end of the front end mounting edge is connected with one end of the elastic bearing seat, and the upper end of the front end mounting edge is connected with the front section inner flow passage; the lower end of the rear end mounting edge is connected with the other end of the elastic bearing seat, and the upper end of the rear end mounting edge is connected with the rear section inner flow passage. The rear bearing frame of the aero-engine can keep stable rigidity and thermal matching of various states through a large temperature gradient region, and ensures stable operation of the engine in various states and requirements of long service life and high reliability.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to a rear bearing frame of an aircraft engine.
Background
In the field of aero-engines, a rear bearing frame of an aero-engine is a key part of the engine, is positioned at a hot end of the rear part of the engine and mainly plays a role in transmitting the gravity and impact of a rear fulcrum of a rotor to an external casing.
The rear bearing frame is a main bearing structure of the engine and is important for stable and reliable operation of the engine. Because the rear bearing frame is positioned at the rear hot end of the engine and needs to pass through a high-temperature runner, the working environment is harsh, and the structural scheme of the rear bearing frame is always a key technology in the design field of all aeroengine companies.
Because the rear bearing frame is a main bearing structure of the engine, the stability of the rigidity of the rear bearing frame is important for the stable operation of the whole engine. The rear bearing frame penetrates through a high-temperature engine runner, the temperature gradient of a passing area is large, and the thermal matching problem of the rear bearing frame is also important to the long service life and the reliability of the engine.
The rigidity of the large temperature gradient area passed by the rear bearing frame is stable, and the thermal matching problem of the large temperature gradient area passed by the rear bearing frame can ensure the stable operation of each state of the engine and meet the requirements of long service life and high reliability of the engine.
In view of this, various aircraft engine research organizations are searching for design schemes for overcoming the thermal stability of the rear bearing frame, so as to overcome the technical problems.
Disclosure of Invention
The invention aims to overcome the defect that the thermal stability of a rear bearing frame of an aircraft engine in the prior art needs to be improved, and provides the rear bearing frame of the aircraft engine.
The invention solves the technical problems through the following technical scheme:
the rear bearing frame of the aircraft engine is characterized by comprising an outer casing, a front section inner flow passage, a rear section inner flow passage and an elastic bearing seat, wherein the outer casing is provided with a plurality of bearing support plates penetrating through the flow passages, the front end of the inner side of each bearing support plate is provided with a front end mounting edge, and the rear end of each bearing support plate is provided with a rear end mounting edge;
the lower end of the front end mounting edge is connected with one end of the elastic bearing seat, and the upper end of the front end mounting edge is connected with the front section inner flow passage; the lower end of the rear end mounting edge is connected with the other end of the elastic bearing seat, and the upper end of the rear end mounting edge is connected with the rear section inner flow passage.
According to one embodiment of the invention, the rear force-bearing frame of the aircraft engine further comprises a front section outer flow passage and a rear section outer flow passage, and the front section outer flow passage and the rear section outer flow passage are respectively installed on the installation edges of the front end surface and the rear end surface of the outer casing.
According to one embodiment of the invention, the rear bearing frame of the aircraft engine further comprises an elastic baffle, the upper end of the elastic baffle is connected with the rear end mounting edge, and the lower end of the elastic baffle is connected with the other end of the elastic bearing seat.
According to one embodiment of the invention, the rear force-bearing frame of the aircraft engine further comprises a ring segment, and the ring segment is installed between the rear end installation edge and the rear section inner flow passage.
According to one embodiment of the invention, the resilient bearing block is Y-shaped.
According to one embodiment of the invention, the outer casing is provided with eight bearing support plates, and the bearing support plates are uniformly distributed in the outer casing and adopt a hollow structure.
According to one embodiment of the invention, the front-section outer flow passage and the rear-section outer flow passage are outer layers of a flow passage cavity, and a first notch is formed in the position, corresponding to the bearing support plate, of the rear-section outer flow passage.
According to one embodiment of the invention, the front-section inner flow passage and the rear-section inner flow passage are inner layers of a flow passage cavity, and a second notch is formed in the position, corresponding to the bearing support plate, of the rear-section inner flow passage.
According to one embodiment of the invention, the mounting edges of the front and rear end faces of the outer casing are in the form of segments.
According to one embodiment of the invention, the rigidity of the elastic bearing seat is one third of the rigidity of the outer casing and the bearing support plate.
The positive progress effects of the invention are as follows:
the rear bearing frame of the aero-engine can keep stable rigidity and thermal matching of various states through a large temperature gradient region, and ensures stable operation of the engine in various states and requirements of long service life and high reliability.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings in which like reference numerals denote like features throughout the several views, wherein:
fig. 1 is a structural schematic diagram of a rear bearing frame of an aircraft engine.
FIG. 2 is a front view of the outer case in the aft bearing frame of the aircraft engine of the present invention.
FIG. 3 is a top view of an outer case in the aft bearing frame of the aircraft engine of the present invention.
FIG. 4 is a front view of the outer layer of the runner cavity in the rear bearing frame of the aircraft engine of the present invention.
FIG. 5 is a top view of the outer layer of the runner cavity in the aft bearing frame of the aircraft engine of the present invention.
FIG. 6 is a front view of the inner layer of the runner cavity in the rear bearing frame of the aircraft engine of the present invention.
FIG. 7 is a top view of the inner layer of the runner cavity in the aft bearing frame of the aircraft engine of the present invention.
[ reference numerals ]
| |
10 |
| Front section |
20 |
| Rear section |
30 |
| |
40 |
| |
11 |
| Front |
12 |
| Rear |
13 |
| Front section |
50 |
| Rear-section |
60 |
| |
70 |
| |
80 |
| |
61 |
| |
31 |
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts.
Further, although the terms used in the present invention are selected from publicly known and used terms, some of the terms mentioned in the description of the present invention may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein.
Furthermore, it is required that the present invention is understood, not simply by the actual terms used but by the meaning of each term lying within.
Fig. 1 is a structural schematic diagram of a rear bearing frame of an aircraft engine. FIG. 2 is a front view of the outer case in the aft bearing frame of the aircraft engine of the present invention. FIG. 3 is a top view of an outer case in the aft bearing frame of the aircraft engine of the present invention. FIG. 4 is a front view of the outer layer of the runner cavity in the rear bearing frame of the aircraft engine of the present invention. FIG. 5 is a top view of the outer layer of the runner cavity in the aft bearing frame of the aircraft engine of the present invention. FIG. 6 is a front view of the inner layer of the runner cavity in the rear bearing frame of the aircraft engine of the present invention. FIG. 7 is a top view of the inner layer of the runner cavity in the aft bearing frame of the aircraft engine of the present invention.
As shown in fig. 1 to 7, the invention discloses a rear force-bearing frame of an aircraft engine, which comprises an outer casing 10, a front-section inner flow passage 20, a rear-section inner flow passage 30 and an elastic bearing seat 40, wherein a plurality of force-bearing support plates 11 penetrating through the flow passages are arranged in the outer casing 10, the front end of the inner side of each force-bearing support plate 11 is provided with a front-end mounting edge 12, and the rear end is provided with a rear-end mounting edge 13. The lower end of the front end mounting edge 12 is connected to one end of the elastic bearing seat 40, and the upper end of the front end mounting edge 12 is connected to the front section inner flow passage 20. The lower end of the rear end mounting edge 13 is connected to the other end of the elastic bearing seat 40, and the upper end of the rear end mounting edge 13 is connected to the rear-section inner flow passage 30.
In addition, the rear force-bearing frame of the aircraft engine further includes a front-section outer runner 50 and a rear-section outer runner 60, and the front-section outer runner 50 and the rear-section outer runner 60 are respectively installed on the installation edges of the front and rear end faces of the outer casing 10. The mounting edges of the front and rear end faces of the outer casing 10 are preferably in the form of segments.
Furthermore, the rear force-bearing frame of the aircraft engine further comprises an elastic baffle sheet 70, the upper end of the elastic baffle sheet 70 is connected with the rear end mounting edge 13, and the lower end of the elastic baffle sheet 70 is connected with the other end of the elastic bearing seat 40.
Preferably, the rear force-bearing frame of the aircraft engine further comprises a ring segment 80, and the ring segment 80 is installed between the rear end installation edge 13 and the rear section inner flow passage 30.
In particular, the elastic bearing block 40 is here Y-shaped. The Y-shaped elastic bearing seat 40 is positioned in the lower temperature area of the rear bearing frame, the rigidity of the Y-shaped elastic bearing seat has relative stability, and the rigidity of the Y-shaped elastic bearing seat 40 is preferably one third of the rigidity of the outer casing and the bearing support plate. According to the principle of rigid connection of the components, the Y-shaped elastic bearing seat 40 is rigid and stable, and the rigidity of the whole frame can be kept stable. The Y-shaped structure of the Y-shaped elastic bearing seat 40 can provide certain elasticity to coordinate the thermal deformation of the elastic support plate structurally.
Furthermore, the outer casing 10 is provided with eight bearing support plates 11, and the bearing support plates 11 are uniformly distributed in the outer casing 10 and adopt a hollow structure. The front end and the rear end of the inner side of each bearing support plate 11 are respectively provided with a sector section mounting edge.
More preferably, the front section outer flow passage 50, the rear section outer flow passage 60, the front section inner flow passage 20 and the rear section inner flow passage 30 form a flow passage chamber through which a high temperature gas flow passes. In order to meet the installation requirements, the front-section outer runner 50 and the rear-section outer runner 60 are outer layers of the runner cavity, and a first notch 61 is formed in the position, corresponding to the bearing support plate 11, of the rear-section outer runner 60. The front section inner flow passage 20 and the rear section inner flow passage 30 are inner layers of the flow passage cavity, and high-temperature airflow is prevented from impacting the bearing seat of the inner cavity. A second gap 31 is arranged at the position of the rear-section inner runner 30 corresponding to the bearing support plate 11.
In conclusion, the rear bearing frame of the aircraft engine can realize the purposes of keeping stable rigidity and thermal matching of various states through a large temperature gradient area, ensuring stable operation of the engine in various states, and meeting the requirements of long service life and high reliability.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (7)
1. The rear bearing frame of the aircraft engine is characterized by comprising an outer casing, a front section inner flow passage, a rear section inner flow passage and an elastic bearing seat, wherein the outer casing is provided with a plurality of bearing support plates penetrating through the flow passages, the front end of the inner side of each bearing support plate is provided with a front end mounting edge, and the rear end of each bearing support plate is provided with a rear end mounting edge;
the lower end of the front end mounting edge is connected with one end of the elastic bearing seat, and the upper end of the front end mounting edge is connected with the front section inner flow passage; the lower end of the rear end mounting edge is connected with the other end of the elastic bearing seat, and the upper end of the rear end mounting edge is connected with the rear section inner flow passage;
the elastic bearing seat is Y-shaped, the outer casing is provided with eight bearing support plates, and the bearing support plates are uniformly distributed in the outer casing and adopt a hollow structure; the rigidity of the elastic bearing seat is one third of the rigidity of the outer casing and the bearing support plate.
2. The rear force-bearing frame of an aircraft engine of claim 1, further comprising a front-section outer runner and a rear-section outer runner, wherein the front-section outer runner and the rear-section outer runner are respectively mounted on mounting edges of front and rear end faces of the outer casing.
3. The rear force-bearing frame of an aircraft engine as claimed in claim 2, wherein the rear force-bearing frame further comprises an elastic baffle, the upper end of the elastic baffle is connected with the rear end mounting edge, and the lower end of the elastic baffle is connected with the other end of the elastic bearing seat.
4. The rear force-bearing frame of an aircraft engine of claim 2, further comprising a ring segment mounted between the rear end mounting edge and the rear section inner flow passage.
5. The rear force-bearing frame of an aircraft engine as claimed in claim 2, wherein the front-section outer flow passage and the rear-section outer flow passage are outer layers of a flow passage cavity, and a first notch is formed in the rear-section outer flow passage at a position corresponding to the force-bearing support plate.
6. The rear force-bearing frame of an aircraft engine as claimed in claim 2, wherein the front section inner flow passage and the rear section inner flow passage are inner layers of a flow passage cavity, and a second notch is formed in the rear section inner flow passage at a position corresponding to the force-bearing support plate.
7. The rear force-bearing frame of an aircraft engine as claimed in claim 2, wherein the mounting edges of the front and rear end faces of the outer case are segment-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811414864.2A CN111219251B (en) | 2018-11-26 | 2018-11-26 | Rear bearing frame of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811414864.2A CN111219251B (en) | 2018-11-26 | 2018-11-26 | Rear bearing frame of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111219251A CN111219251A (en) | 2020-06-02 |
| CN111219251B true CN111219251B (en) | 2021-05-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811414864.2A Active CN111219251B (en) | 2018-11-26 | 2018-11-26 | Rear bearing frame of aero-engine |
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| Country | Link |
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| CN (1) | CN111219251B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114165300B (en) * | 2021-10-20 | 2023-06-13 | 中国航发四川燃气涡轮研究院 | Turbine rear bearing floating structure capable of reducing thermal stress |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008215083A (en) * | 2007-02-28 | 2008-09-18 | Mitsubishi Heavy Ind Ltd | Mounting structure for variable nozzle mechanism in variable geometry exhaust turbocharger |
| CN103321753A (en) * | 2013-07-04 | 2013-09-25 | 中国航空动力机械研究所 | Force-bearing cavity structure of gas turbine main bearing |
| CN203499822U (en) * | 2013-10-19 | 2014-03-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Thermal insulation device of gas turbine supporting system |
| CN105317559A (en) * | 2014-05-29 | 2016-02-10 | 北京航空航天大学 | Turbine rear force bearing case integrally connected to rectification blade cascade |
| CN205958238U (en) * | 2016-06-28 | 2017-02-15 | 中航商用航空发动机有限责任公司 | Stiffness detection system of radially moving of aeroengine support case |
| CN106640233A (en) * | 2017-01-23 | 2017-05-10 | 中国航发沈阳发动机研究所 | Turbine bearing case heat insulation flowing channel and engine with same |
-
2018
- 2018-11-26 CN CN201811414864.2A patent/CN111219251B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008215083A (en) * | 2007-02-28 | 2008-09-18 | Mitsubishi Heavy Ind Ltd | Mounting structure for variable nozzle mechanism in variable geometry exhaust turbocharger |
| CN103321753A (en) * | 2013-07-04 | 2013-09-25 | 中国航空动力机械研究所 | Force-bearing cavity structure of gas turbine main bearing |
| CN203499822U (en) * | 2013-10-19 | 2014-03-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Thermal insulation device of gas turbine supporting system |
| CN105317559A (en) * | 2014-05-29 | 2016-02-10 | 北京航空航天大学 | Turbine rear force bearing case integrally connected to rectification blade cascade |
| CN205958238U (en) * | 2016-06-28 | 2017-02-15 | 中航商用航空发动机有限责任公司 | Stiffness detection system of radially moving of aeroengine support case |
| CN106640233A (en) * | 2017-01-23 | 2017-05-10 | 中国航发沈阳发动机研究所 | Turbine bearing case heat insulation flowing channel and engine with same |
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| Publication number | Publication date |
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| CN111219251A (en) | 2020-06-02 |
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