CN115182818A - Supporting structure for inner ring of intermediate fulcrum of engine - Google Patents
Supporting structure for inner ring of intermediate fulcrum of engine Download PDFInfo
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- CN115182818A CN115182818A CN202210376751.8A CN202210376751A CN115182818A CN 115182818 A CN115182818 A CN 115182818A CN 202210376751 A CN202210376751 A CN 202210376751A CN 115182818 A CN115182818 A CN 115182818A
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- ring
- bearing
- support
- inner ring
- bearing inner
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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
- F02C7/06—Arrangements of bearings; Lubricating
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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
- F02C7/28—Arrangement of seals
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Mounting Of Bearings Or Others (AREA)
Abstract
The application belongs to the field of intermediate casing design, and relates to an intermediate fulcrum inner ring supporting structure of an engine, which comprises a high vortex disc, a second sealing comb tooth ring, a bearing inner ring and a retainer; axial compression between the support ring and the support piece is realized through a fastening bolt, a high-vortex rear journal is cancelled, radial positioning between the support piece and the support ring is realized through spigot matching, and radial matching tightness is ensured, and the axial compression and the radial positioning of the second sealing comb tooth ring are provided by the support ring and the support piece together; the minimum distance from the bearing inner ring to the axis of the low-pressure rotor is the same as the minimum distance from the high-vortex disc to the axis of the low-pressure rotor, and the structure of the high-pressure rotor is not arranged on the inner side of the bearing inner ring any more, so that the bearing inner ring, the retainer and the bearing outer ring are all closer to the axis of the low-pressure rotor, the radial space of the intermediate fulcrum inner ring supporting structure is compressed, the diameter of the bearing inner ring is reduced, the rotation speed of the bearing roller is reduced, and a space is provided for reducing the heating value of the bearing.
Description
Technical Field
The application belongs to the field of intermediate fulcrum design, and particularly relates to an inner ring supporting structure of an intermediate fulcrum of an engine.
Background
The intermediate fulcrum is a fulcrum form commonly adopted by the current double-rotor aviation turbofan engine and comprises a fulcrum bearing, a lubricating oil supply and return structure for cooling and lubricating the bearing and a bearing cavity sealing structure. The advantage of the intermediate fulcrum compared with the bearing frame between the turbine stages is compact structure. However, as the intermediate fulcrum is supported between the high-pressure rotor and the low-pressure rotor, the reliability of the supporting structure is higher by the intermediate fulcrum bearing, so that the coupled vibration of the high-pressure rotor and the low-pressure rotor caused by the deflection of the inner ring and the outer ring of the bearing is prevented; because the intermediate fulcrum is positioned between the high-pressure rotor and the low-pressure rotor, the bearing and the lubricating oil related to the intermediate fulcrum are limited in oil supply and return and sealing structure space. Therefore, the design difficulty of the intermediate fulcrum supporting structure is large.
The intermediate fulcrum can be divided into the following parts according to the bearing inner and outer ring supporting modes: the inner ring is supported on the high-pressure rotor, and the outer ring is supported on the low-pressure rotor; the outer ring is supported on the high-pressure rotor, and the inner ring is supported on the low-pressure rotor, and the two supporting modes have advantages and disadvantages respectively.
As shown in fig. 1, a roller 5 and a retainer 7 are disposed outside a bearing inner ring 4, the bearing inner ring 4 is supported on a high-vortex rear journal 2, and the high-vortex rear journal 2 is connected to a high-vortex disc 1 through a first bolt 8 and a first nut 9. The compression nut 7 realizes the axial compression of the bearing inner ring 4. To ensure the sealing of the bearing chamber, a first sealing comb ring 3 is mounted on the high-vortex rear journal 2.
The intermediate fulcrum inner ring supporting structure of the traditional scheme is characterized in that a bearing inner ring is sleeved on a high-vortex rear shaft neck, and effective positioning of the inner ring is realized through the radial fit tightness of the bearing inner ring and the high-vortex rear shaft neck and the axial pressing force of a pressing nut. Because the materials of the bearing inner ring and the high-vortex rear shaft neck are different, the thermal expansion amount of the shaft and the radial direction at the same temperature is different; meanwhile, in the working process, the ambient temperature around the fulcrum and the heat productivity of the bearing change along with the working condition of the engine, and especially under the complex working conditions of quick push-up, pull-down and the like, the ambient temperature and the heat productivity of the bearing change greatly. The above factors cause different axial and radial deformation of the bearing inner ring and the high-vortex rear journal, and the radial matching and axial compression states of the bearing inner ring and the high-vortex rear journal are changed. The bearing inner ring is separated from the high vortex rear shaft neck possibly, so that the bearing inner ring is loosened, the problems of vibration of the whole machine, damage of the bearing and the like are caused, and the safe work of the engine is influenced.
Because the labyrinth ring is assembled on the high vortex rear shaft neck, the labyrinth ring is also positioned by radial tightness and axial compression. After the comb-tooth ring is assembled, the journal deforms after high vortex due to the radial tightness fit, and the fit state of the bearing inner ring is influenced. Meanwhile, the comb-tooth ring is axially compressed by a compression nut on an axial compression path of the bearing inner ring, and axial compression of the bearing inner ring can be influenced by axial deformation of the comb-tooth ring in a working state.
The intermediate bearing roller has high autorotation speed, the bearing has large heat productivity, and certain influence on the service life of the bearing. Due to the structural size limitation of the high-vortex rear shaft neck, the size of the intermediate bearing cannot be reduced, and the rotation speed of the bearing roller and the heat productivity of the bearing can be reduced.
The high vortex rear shaft neck and the high vortex disc are connected and installed, the radial height of the edge is higher, the rigidity of the high vortex rear shaft neck is stronger, and the fulcrum dynamic load born by the intermediary bearing is higher; the rigidity of the shaft neck is stronger after the high vortex, which also causes the deformation of the high vortex to have larger influence on the medium bearing.
Therefore, how to improve the positioning accuracy and the installation stability of the bearing inner ring is a problem to be solved.
Disclosure of Invention
The application aims to provide an intermediate fulcrum inner ring supporting structure of an engine, and aims to solve the problems that in the prior art, the bearing inner ring is easy to loosen and the axial compression is difficult to stabilize due to different axial and radial deformation of a bearing inner ring and a high-vortex rear shaft neck.
The technical scheme of the application is as follows: the utility model provides a fulcrum inner circle bearing structure in engine, includes high whirlpool dish, the sealed comb tooth ring of second, bearing inner circle and holder, the holder is coaxial to be located the bearing inner circle outside, the bearing inner circle stretches out the annular support piece that has integrative setting to one side of high whirlpool dish, be equipped with the support ring that corresponds the setting with support piece on the high whirlpool dish, the sealed comb tooth ring of second is located between the support piece of support ring and bearing inner circle, support ring, the sealed comb tooth ring of second and support piece are through the fastening bolt connection along axial direction, support piece and the radial tang cooperation of support ring, the last an organic whole of high whirlpool dish is connected with annular support frame, the bearing inner circle sets up side by side with annular support frame.
Preferably, the annular support frame comprises a support arm (5) and a rotating sleeve; the rotating sleeve is coaxially arranged on the outer side of the low-pressure rotor, the supporting arm (5) is obliquely connected between the high-vortex disk and the rotating sleeve, and the supporting ring is integrally and coaxially connected to the outer annular surface of the rotating sleeve.
Preferably, the support piece comprises a transverse connecting ring and a longitudinal connecting ring, the transverse connecting ring and the longitudinal connecting ring are L-shaped in cross section, the longitudinal connecting ring is connected with the support ring and the second sealing comb-tooth ring through bolts, and the transverse connecting ring is matched with the radial seam allowance of the rotating sleeve.
Preferably, the distance from the inner ring surface of the transverse connecting ring to the axis of the low-pressure rotor is greater than the distance from the inner ring surface of the axial inner ring to the axis of the low-pressure rotor, a spigot boss is arranged on the outer ring surface of the rotating sleeve, one end of the transverse connecting ring, which is close to the longitudinal connecting ring, is matched with a radial spigot of the spigot boss, and the transverse connecting ring is in interference fit with the radial spigot of the rotating sleeve.
Preferably, the rotating sleeve and one end of the bearing inner ring close to the high scroll are provided with an axial gap.
Preferably, the second sealing grate ring comprises a connecting portion and a sealing portion; the connecting portion are arranged along the radial direction of the low-pressure rotor and tightly attached between the support ring and the support piece, the sealing portion is arranged on the outer side of the connecting portion, a sealing labyrinth is arranged on the sealing portion, and the inner side of the sealing portion is matched with a radial spigot on the outer side of the support ring.
Preferably, the sealing labyrinth comprises a first labyrinth and a second labyrinth, the first labyrinth is used for sealing the bearing cavity, and the second labyrinth is used for forming a sealing cavity.
Preferably, a gap is formed between the second grate and the annular support frame, and a nut of the fastening bolt is arranged at the gap between the second grate and the annular support frame.
Preferably, an annular first boss and an annular second boss are arranged on the inner ring surface of the bearing inner ring, the first boss and the second boss are respectively arranged at two ends of the bearing inner ring, and a lubricating oil containing cavity is formed between the first boss and the second boss.
Preferably, the bearing inner ring is provided with a hook groove on the outer ring surface of one end far away from the high scroll.
The utility model provides an engine intermediary fulcrum inner circle bearing structure, including high whirlpool dish, second obturating comb tooth ring, bearing inner circle and holder; the axial compression between the support ring and the support piece is realized through the fastening bolt, a high-vortex rear journal is cancelled, the radial positioning between the support piece and the support ring is realized through the spigot matching, and the radial matching tightness is ensured; the structure of the high-pressure rotor is not arranged on the inner side of the bearing inner ring any more, but the high-pressure rotor and the bearing inner ring are arranged side by side in the axial direction, so that the bearing inner ring, the retainer and the bearing outer ring are closer to the axial position of the low-pressure rotor, the radial space of the intermediate fulcrum inner ring supporting structure is compressed, the diameter of the bearing inner ring is reduced, the rotation speed of the bearing roller is reduced, and a space is provided for reducing the heating amount of the bearing.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a cross-sectional view of a medium fulcrum in the prior art;
FIG. 2 is a schematic view of the overall structure of the intermediate fulcrum bearing of the present application;
FIG. 3 is a schematic cross-sectional view of the inner race support of the subject disclosure.
1. A high-speed scroll pan; 2. a high vortex aft journal; 3. a first sealing comb-tooth ring; 4. a bearing inner race; 5. a roller; 6. a holder; 7. a compression nut; 8. a first bolt; 9. a first nut; 10. an annular support frame; 11. a second sealing comb-tooth ring; 12. a support ring; 13. fastening a bolt; 14. hooking a groove; 15. a support arm; 16. rotating the sleeve; 17. a transverse connecting ring; 18. longitudinal connecting rings; 19. a low pressure rotor; 20. a connecting portion; 21. a sealing part; 22. a first comb tooth; 23. a second comb tooth; 24. a first boss; 25. a second boss.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
An intermediate fulcrum inner ring supporting structure of an engine, as shown in figures 2 and 3, comprises a high scroll 1, a second sealing grate ring 11, a bearing inner ring 4 and a retainer 6. The high-pressure vortex disc 1 is a high-pressure rotor part and is connected with a high-pressure turbine, a bearing is arranged between the high-pressure rotor part and a low-pressure rotor 19, the bearing is preferably a cylindrical roller bearing and comprises a bearing outer ring, a retainer 6, a bearing inner ring 4 and other structures, the retainer 6 is coaxially arranged between the bearing outer ring and the bearing inner ring 4, the low-pressure rotor 19 is arranged at the inner sides of the high-pressure rotor part and the bearing inner ring 4, and the high-pressure rotor part, the high-pressure turbine and the low-pressure rotor are coaxially arranged; the second sealing grate ring 11 is used on the one hand for sealing the bearing and on the other hand for forming a sealing cavity.
Preferably, an annular support frame 10 is integrally connected to the high scroll 1, and the annular support frame 10 comprises a support arm 15 and a rotating sleeve 16; the rotating sleeve 16 is a cylindrical structure and the rotating sleeve 16 is coaxially arranged outside the low pressure rotor 19, the supporting arm 15 is obliquely connected between the high scroll 1 and the rotating sleeve 16, and the supporting ring 12 is integrally and coaxially connected to the outer circumferential surface of the rotating sleeve 16.
Preferably, an integrally arranged annular support member extends out of the bearing inner ring 4 towards one side of the high scroll 1, a support ring 12 arranged corresponding to the support member is arranged on the high scroll 1, a second sealing comb tooth ring 11 is arranged between the support ring 12 and the support member, the support ring 12, the second sealing comb tooth ring 11 and the support member are in threaded connection with a fastening bolt 13 along the axial direction, a nut is connected to the tail end of the fastening bolt 13, the support member is matched with a radial spigot of the support ring 12, and the bearing inner ring 4 and the annular support frame (10) are arranged side by side.
Preferably, the support comprises a transverse connecting ring 17 and a longitudinal connecting ring 18, and the transverse connecting ring 17 and the longitudinal connecting ring 18 are L-shaped in cross section. The distance from the inner ring surface of the transverse connecting ring 17 to the axis of the low-pressure rotor 19 is greater than the distance from the inner ring surface of the axial inner ring to the axis of the low-pressure rotor 19, so that the radial position of the transverse connecting ring 17 is higher than that of the bearing inner ring 4, the rotating sleeve 16 can be inserted between the transverse connecting ring 17 and the bearing inner ring 4 to support and limit, a spigot boss is arranged on the outer ring surface of the rotating sleeve 16, one end of the transverse connecting ring 17, which is close to the longitudinal connecting ring 18, is matched with the radial spigot of the spigot boss, and the spigot is matched with the radial spigot.
The accurate and reliable centering of the bearing inner ring 4 and the high vortex disc 1 is realized through the spigots of the rotating sleeve 16 and the transverse connecting ring 17. On one hand, the length of the spigot is shorter, the influence of interference fit of the spigot on the deformation of the bearing inner ring 4 and the rotating sleeve 16 is smaller, and the deformation of the bearing inner ring is reduced, so that the working environment of the bearing can be effectively improved; on the other hand, the height of the spigot is reduced, the influence of different radial deformation on spigot matching caused by different materials and temperatures of the bearing inner ring 4 and the annular support frame (10) is weakened, and the reliability of bearing centering is improved.
The axial compression between the support ring 12 and the longitudinal connecting ring 18 is realized through the fastening bolt 13, the end surface friction force brought by the axial pressing force can effectively prevent the relative movement of the bearing inner ring 4 and the rotating sleeve 16, and meanwhile, the bolt also realizes the physical rotation prevention of the bearing inner ring 4 and the rotating sleeve 16, thereby further improving the reliability of the bearing centering. The structure cancels the high vortex rear shaft neck 2 and the compression nut 7, and the structure is more compact.
The structure of the high-pressure rotor is not arranged on the inner side of the bearing inner ring 4 any longer, but the high-pressure rotor and the bearing inner ring 4 are arranged side by side in the axial direction, so that the bearing inner ring 4, the retainer 6 and the bearing outer ring are all closer to the axial position of the low-pressure rotor 19, the radial space of the intermediate fulcrum inner ring supporting structure is compressed, the diameter of the bearing inner ring 4 is reduced, the rotation speed of the bearing roller 5 is reduced, and a space is provided for reducing the heat productivity of the bearing.
Through the support ring 12 and the support piece direct connection that high whirlpool dish 1 an organic whole set up, support arm 15 is than the high whirlpool back journal 2 radial height reduction, radial rigidity weakens, and the fulcrum dynamic load and the deformation influence that high whirlpool dish 1 brought for intermediary bearing reduce, and intermediary bearing operational environment at this moment improves by a wide margin.
Preferably, rotating sleeve 16 and the end of inner bearing ring 4 close to high scroll 1 have a gap, and the existence of the gap can avoid mutual influence of rotating sleeve 16 and inner bearing ring 4 when rotating sleeve 16 is subjected to thermal expansion.
Preferably, the second sealing grate ring 11 comprises a connecting portion 20 and a sealing portion 21; the connecting part 20 is arranged along the radial direction of the low-pressure rotor 19, the connecting part 20 is tightly attached between the support ring 12 and the support piece, the sealing part 21 is arranged on the outer side of the connecting part 20, the sealing labyrinth is arranged on the sealing part 21, the connecting part 20 and the sealing part 21 are combined to form a T-shaped structure, one side of the T-shaped structure is convenient to fix by bolts, and the other side of the T-shaped structure can be stably sealed.
Preferably, the sealing labyrinth comprises a first labyrinth 22 and a second labyrinth 23, the first labyrinth 22 is used for sealing a bearing, the second labyrinth 23 is used for sealing the high vortex disc 1, the radial position of the second labyrinth 23 is higher than that of the first labyrinth 22, and the first labyrinth 22 and the second labyrinth 23 are integrally arranged, so that the first labyrinth 22 and the second labyrinth 23 can be positioned with each other, the positions cannot be changed, and the sealing stability is ensured.
Because the comb ring 11 that seals of second obtains the accurate location of support ring 12, the labyrinth that seals on the axle journal 2 after having got rid of the high vortex, the comb ring 11 that seals forms the chamber of sealing and provides the protection of sealing for the bearing chamber as an solitary component this moment, it is more convenient to dismouting and adjustment when guaranteeing the installation accuracy, compare in the labyrinth that seals who sets up two sets of different positions, it is more reasonable to design space layout through regarding the comb ring 11 that seals of second as a solitary component, the installation and the screwing up of the nut for fastening bolt 13 provide the space.
Preferably, sufficient space is reserved between the second grate 23 and the annular support frame 10, nuts of the fastening bolts (13) are arranged at the spaced positions between the second grate 23 and the annular support frame 10, and the arrangement of the space can ensure the installation and the screwing of the connecting nuts.
Preferably, the inner ring surface of the bearing inner ring 4 is provided with a first annular boss 24 and a second annular boss 25, the first boss 24 and the second boss 25 are respectively arranged at two ends of the bearing inner ring 4, a lubricating oil accommodating cavity is formed between the first boss 24 and the second boss 25, the lubricating oil accommodating cavity utilizes an axial space as far as possible on the premise that the depth is not increased so as to influence the rigidity of the bearing inner ring 4, and the lubricating oil accommodating cavity is as large as possible. After the lubricating oil reaches the bearing inner ring 4, the lubricating oil can be temporarily stored in the lubricating oil accommodating cavity between the first boss 24 and the second boss 25, so that the lubricating oil receiving efficiency is ensured, and the lubricating and cooling requirements of the bearing are met.
Preferably, the outer ring surface of one end of the bearing inner ring far away from the high scroll is provided with a U-shaped hook groove 14 for the assembly tool of the bearing inner ring to mount and apply force.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides an engine intermediary fulcrum inner circle bearing structure, includes high whirlpool dish (1), second sealed comb ring gear (11), bearing inner circle (4) and holder (6), the coaxial bearing inner circle (4) outside of locating of holder (6), its characterized in that: bearing inner race (4) stretches out the annular support piece that has integrative setting to one side of high whirlpool dish (1), be equipped with on high whirlpool dish (1) and correspond support ring (12) that sets up with support piece, the second is sealed and is combed between the support piece of support ring (12) and bearing inner race (4) is located tooth ring (11), support ring (12), second are sealed and are combed tooth ring (11) and support piece and are connected through fastening bolt (13) along axial direction, support piece and support ring (12) radial tang cooperation, an organic whole is connected with annular support frame (10) on the high whirlpool dish (1), bearing inner race (4) set up side by side with annular support frame (10).
2. The intermediate fulcrum inner race support structure of an engine according to claim 1, wherein: the annular support frame (10) comprises a support arm (15) and a rotating sleeve (16); the rotating sleeve (16) is coaxially arranged on the outer side of the low-pressure rotor (19), the supporting arm (15) is obliquely connected between the high-vortex disc (1) and the rotating sleeve (16), and the supporting ring (12) is integrally and coaxially connected to the outer annular surface of the rotating sleeve (16).
3. The intermediate fulcrum inner race support structure of an engine according to claim 2, wherein: support piece includes horizontal go-between (17) and longitudinal connecting ring (18), the transversal L type of personally submitting of horizontal go-between (17) and longitudinal connecting ring (18), bolted connection is passed through with support ring (12), second seal comb ring (11) in longitudinal connecting ring (18), horizontal go-between (17) and the cooperation of the radial tang of rotating sleeve (16).
4. An engine intermediate fulcrum inner ring support structure according to claim 3, wherein: the distance from the inner ring surface of the transverse connecting ring (17) to the axis of the low-pressure rotor (19) is larger than the distance from the inner ring surface of the axial inner ring to the axis of the low-pressure rotor (19), a spigot boss is arranged on the outer ring surface of the rotating sleeve (16), one end of the transverse connecting ring (17) close to the longitudinal connecting ring (18) is matched with a radial spigot of the spigot boss, and the radial spigot of the transverse connecting ring (17) and the radial spigot of the rotating sleeve (16) are in interference fit.
5. The intermediate fulcrum inner race support structure of an engine according to claim 2, wherein: and an axial gap is formed between the rotating sleeve (16) and one end, close to the high scroll (1), of the bearing inner ring (4).
6. The intermediate fulcrum inner race support structure of an engine according to claim 1, wherein: the second sealing grate ring (11) comprises a connecting part (20) and a sealing part (21); the sealing structure is characterized in that the connecting part (20) is arranged along the radial direction of the low-pressure rotor (19), the connecting part (20) is tightly attached between the support ring (12) and the supporting piece, the sealing part (21) is arranged on the outer side of the connecting part (20), the sealing labyrinth is arranged on the sealing part (21), and the inner side of the sealing part (21) is matched with the radial spigot on the outer side of the support ring (12).
7. The intermediate fulcrum inner race support structure of an engine according to claim 6, wherein: the sealing labyrinth comprises a first labyrinth (22) and a second labyrinth (23), the first labyrinth (22) is used for sealing the bearing cavity, and the second labyrinth (23) is used for forming the sealing cavity.
8. The intermediate fulcrum inner race support structure of an engine according to claim 7, wherein: and a gap is formed between the second grate tooth (23) and the annular support frame (10), and nuts of the fastening bolts (13) are arranged at the gap between the second grate tooth (23) and the annular support frame (10).
9. The intermediate fulcrum inner race support structure of an engine according to claim 1, wherein: the bearing inner race is characterized in that an annular first boss (24) and an annular second boss (25) are arranged on the inner annular surface of the bearing inner race (4), the first boss (24) and the second boss (25) are respectively arranged at two ends of the bearing inner race (4), and a lubricating oil containing cavity is formed between the first boss (24) and the second boss (25).
10. The intermediate fulcrum inner race support structure of an engine according to claim 1, wherein: and a hook groove (14) is formed in the outer ring surface of one end, away from the high vortex disc (1), of the bearing inner ring (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210376751.8A CN115182818A (en) | 2022-04-11 | 2022-04-11 | Supporting structure for inner ring of intermediate fulcrum of engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210376751.8A CN115182818A (en) | 2022-04-11 | 2022-04-11 | Supporting structure for inner ring of intermediate fulcrum of engine |
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| Publication Number | Publication Date |
|---|---|
| CN115182818A true CN115182818A (en) | 2022-10-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210376751.8A Pending CN115182818A (en) | 2022-04-11 | 2022-04-11 | Supporting structure for inner ring of intermediate fulcrum of engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115816071A (en) * | 2023-02-07 | 2023-03-21 | 成都中科翼能科技有限公司 | Assembly method of gas turbine supporting structure |
-
2022
- 2022-04-11 CN CN202210376751.8A patent/CN115182818A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115816071A (en) * | 2023-02-07 | 2023-03-21 | 成都中科翼能科技有限公司 | Assembly method of gas turbine supporting structure |
| CN115816071B (en) * | 2023-02-07 | 2023-04-28 | 成都中科翼能科技有限公司 | Assembling method of gas turbine supporting structure |
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