CN115217536B - Intermediate fulcrum bearing cavity structure of counter-rotating turbine - Google Patents

Intermediate fulcrum bearing cavity structure of counter-rotating turbine Download PDF

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Publication number
CN115217536B
CN115217536B CN202211113661.6A CN202211113661A CN115217536B CN 115217536 B CN115217536 B CN 115217536B CN 202211113661 A CN202211113661 A CN 202211113661A CN 115217536 B CN115217536 B CN 115217536B
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China
Prior art keywords
bearing
ring
sealing ring
low
pressure turbine
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CN115217536A (en
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曹茂国
刘云龙
刘美
� 崔
孙国志
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AECC Shenyang Engine Research Institute
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AECC Shenyang Engine Research Institute
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/20—Hydro energy

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The application belongs to the field of design of aero-engines and gas turbines, and relates to a medium fulcrum bearing cavity structure of a contra-rotating turbine, which comprises a high-vortex rear shaft neck, a low-pressure turbine shaft, a disc center sealing ring, a bearing sealing ring, a rear shaft sealing ring and a bearing assembly; a cooling cavity is formed among the disc center sealing ring, the bearing sealing ring and the high-vortex rear shaft neck, and a plurality of groups of vent holes communicated with the cooling cavity are arranged on the low-pressure turbine shaft cone arm at intervals along the circumferential direction; when the cooling device works, the vent hole introduces external air from a rear casing of the aircraft engine, and the external air enters the cooling cavity to cool the bearing cavity by reducing the ambient temperature outside the bearing sealing ring; the back of the outer culvert gas cooling bearing cavity enters the sealed exhaust cavity through the second labyrinth, part of the outer culvert gas enters the high-temperature low-pressure plate front gas in the first labyrinth, and the rest of the outer culvert gas is exhausted through the vent hole in the low-pressure turbine plate, so that the working reliability and safety of the contra-rotating turbine bearing cavity are comprehensively improved.

Description

Intermediate fulcrum bearing cavity structure of counter-rotating turbine
Technical Field
The application belongs to the field of design of aero-engines and gas turbines, and particularly relates to a middle fulcrum bearing cavity structure of a counter-rotating turbine.
Background
The aircraft engine with the contra-rotating structure adopts an intermediate fulcrum supporting structure, so that the connection of the high-pressure rotor and the low-pressure rotor is more compact, the length and the weight of the engine are reduced, and the thrust-weight ratio of the engine is improved. The design of the intermediate fulcrum bearing cavity of the high-low pressure turbine comprises a bearing inner ring and bearing outer ring connecting structure, the lubricating and cooling of the bearing, the sealing of the bearing cavity and the like.
Because the high-low pressure turbine is in a contra-rotating state, the relative rotating speed of the inner ring and the outer ring of the bearing is high, the heat generation is high, and the cooling and the temperature reduction of the bearing cavity need to be mainly solved. The scheme of the existing bearing cavity adopts the scheme of a double-wall sealing ring to reduce the heat conduction to the bearing cavity so as to reduce the temperature of the bearing cavity.
Adopt the cooling that the sealing ring of double-walled structure can realize contrarotating turbine bearing chamber, nevertheless have following problem:
(1) Because the ambient temperature of the bearing cavity is unchanged due to the gas and the sealing gas, the cooling effect of the bearing cavity brought by the double-wall structure is limited;
(2) The double-walled structure increases the number of parts, increases the structural complexity, and increases the weight of the engine.
Therefore, how to improve the cooling quality in the contra-rotating turbine bearing cavity and reduce the structural complexity is a problem to be solved.
Disclosure of Invention
The utility model provides a to supporting point bearing cavity structure in middle of revolving turbine to cooling effect is limited, the high problem of structure complexity when adopting double-walled structure sealing ring to cool down turbine bearing cavity among the solution prior art.
The technical scheme of the application is as follows: a structure of an intermediate fulcrum bearing cavity of a contra-rotating turbine is arranged between a high-pressure turbine disc and a low-pressure turbine disc, and a first labyrinth is arranged between the high-pressure turbine disc and the low-pressure turbine disc and comprises a high-vortex rear shaft neck, a low-pressure turbine shaft, a disc center sealing ring, a bearing sealing ring, a rear shaft sealing ring and a bearing assembly; a bearing cavity is formed among the bearing sealing ring, the rear shaft sealing ring and the low-pressure turbine shaft, the bearing assembly is arranged in the bearing cavity, and a sealing exhaust cavity is formed among the disc center sealing ring, the low-pressure turbine disc and the high-vortex rear shaft neck; a second labyrinth is arranged between the disc core sealing ring and the high-vortex rear shaft neck, and a third labyrinth is arranged between the bearing sealing ring and the high-vortex rear shaft neck; and a cooling cavity is formed among the disc center sealing ring, the bearing sealing ring and the high vortex rear shaft neck, a plurality of groups of vent holes communicated with the cooling cavity are arranged at intervals along the circumferential direction of the low-pressure turbine shaft, and the vent holes are communicated with outside air.
Preferably, a first flat ring is arranged on the disc center sealing ring, a second flat ring is arranged on the bearing sealing ring, the second flat ring is correspondingly arranged on the inner side of the first flat ring, and the radial width of the first flat ring and the radial width of the second flat ring are smaller than the radial width between the first labyrinth and the second labyrinth.
Preferably, an inner collar is arranged at a position, corresponding to the outer side of the disc core sealing ring, of the low-pressure turbine disc, and the radial width from the first straight ring to the inner collar is smaller than the radial width from the first straight ring to the outer surface of the first labyrinth.
Preferably, the bearing assembly comprises a bearing outer ring, a bearing inner ring, bearing balls and a compression nut; the bearing balls are connected between the bearing outer ring and the bearing inner ring, the bearing inner ring and the compression nut are both connected to the rear shaft sealing ring, and the bearing outer ring is connected to the low-pressure turbine shaft; a first oil return channel is formed between the bearing outer ring and the bearing sealing ring, and an oil return hole is formed in the position of the low-pressure turbine shaft, which corresponds to the first oil return channel; and a second oil return channel is arranged on the low-pressure turbine shaft and corresponds to the bearing roller.
Preferably, bolt holes which are arranged correspondingly to each other are formed among the bearing sealing ring, the bearing outer ring and the low-pressure turbine shaft, the bolt holes of the bearing outer ring are located between the bearing sealing ring and the bolt holes of the low-pressure turbine shaft, and long bolts are connected in the bolt holes.
Preferably, the long bolt is provided with an inward concave ring, and the non-inward concave ring on the long bolt is in threaded connection with the bearing sealing ring, the bearing outer ring and the bolt holes on the low-pressure turbine shaft.
Preferably, the end of the bolt hole of the bearing sealing ring is provided with a local bevel angle.
The utility model provides a middle fulcrum bearing chamber structure of contra-rotating turbine, including high whirlpool back journal, low-pressure turbine shaft, disk heart seal ring, bearing seal ring, back shaft seal ring and bearing assembly; a cooling cavity is formed among the disc center sealing ring, the bearing sealing ring and the high-vortex rear shaft neck, and a plurality of groups of vent holes communicated with the cooling cavity are arranged at intervals along the circumferential direction of the low-pressure turbine shaft; when the cooling device works, the vent hole in the cone arm of the low-pressure turbine shaft introduces external air from a rear casing of the aircraft engine, and the air enters the cooling cavity to cool the bearing cavity by reducing the ambient temperature outside the bearing sealing ring; the introduced foreign air enters the sealed exhaust cavity through the second labyrinth after cooling the bearing cavity, the high-temperature low-pressure plate front air is sealed at the first labyrinth, and the rest foreign air is discharged through a ventilation and discharge hole in the low-pressure turbine plate; on the one hand, the temperature of the bearing cavity is reduced, and meanwhile, the influence of the high-temperature low-pressure disk front gas on the bearing cavity is isolated, so that the working reliability and safety of the contra-rotating turbine bearing cavity are comprehensively improved.
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 schematic view of the overall structure of the present application;
FIG. 2 is a schematic view of an oil return structure of the present application;
FIG. 3 is a schematic view of the connection structure of the long bolt of the present application;
FIG. 4 is a schematic view of the construction of the long bolt of the present application;
FIG. 5 is a schematic view of the separation structure of the long bolt and the bearing sealing ring.
1. A high pressure turbine disk; 2. a high vortex aft journal; 3. a rear shaft seal Yan Huan; 4. a bearing inner ring; 5. a bearing ball; 6. a bearing outer ring; 7. a low pressure turbine disk; 8. a disc center sealing ring; 9. a bearing sealing ring; 10. a low-pressure turbine shaft; 11. a compression nut; 12. a cooling chamber; 13. a first flat ring; 14. a second straight loop; 15. an inner collar; 16. a first oil return passage; 17. a second oil return passage; 18. a long bolt; 19. an inner concave ring; 20. local bevel angle.
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.
The utility model provides a to changeing middle fulcrum bearing chamber structure of turbine, locates between high-pressure turbine dish and the low pressure turbine dish, is equipped with first labyrinth between high-pressure turbine dish and the low pressure turbine dish. And sealing gas in the high-pressure turbine disc is discharged through the first labyrinth.
As shown in fig. 1, the turbine comprises a high-turbine rear journal 2, a low-pressure turbine shaft 10, a disc center sealing ring 8, a bearing sealing ring 9, a rear shaft sealing ring 3 and a bearing assembly; a bearing cavity is formed among the bearing sealing ring 9, the rear shaft sealing ring 3 and the low-pressure turbine shaft 10, the bearing assembly is arranged in the bearing cavity, and a sealing exhaust cavity is formed among the disc center sealing ring 8, the low-pressure turbine disc 7 and the high-vortex rear shaft neck 2; a second labyrinth is arranged between the disc core sealing ring 8 and the high vortex rear shaft neck 2, and a third labyrinth is arranged between the bearing sealing ring 9 and the high vortex rear shaft neck 2.
And a cooling cavity 12 is formed among the disc center sealing ring 8, the bearing sealing ring 9 and the high-vortex rear shaft neck 2, and a plurality of groups of vent holes communicated with the cooling cavity 12 are arranged on the conical arm of the low-pressure turbine shaft 10 at intervals along the circumferential direction and are communicated with outside air.
When the cooling device works, the vent hole on the cone arm of the low-pressure turbine shaft introduces external air from a rear casing of the aero-engine and enters the cooling cavity 12, the cooling of the bearing cavity is realized by reducing the ambient temperature outside the bearing sealing ring 9, and meanwhile, the sealing of lubricating oil in the bearing cavity is realized at the third labyrinth; the outer culvert gas cooling bearing cavity enters the sealed exhaust cavity through the second labyrinth, the high-temperature sealed gas in front of the low-pressure disc is sealed at the first labyrinth, and the rest outer culvert gas is exhausted through the vent hole in the low-pressure turbine disc 7; on the one hand, the temperature of the bearing cavity is reduced, and meanwhile, the influence of the high-temperature low-pressure disk front gas on the bearing cavity is isolated, so that the working reliability and safety of the contra-rotating turbine bearing cavity are comprehensively improved.
The pressure in the exhaust cavity is tightly sealed to be higher than that of the front cavity of the low-pressure turbine disc, so that the high-temperature gas in the front cavity of the low-pressure turbine disc can not affect the bearing cavity completely; meanwhile, lubricating oil in the bearing cavity can be stably discharged without being affected, the structure is simple, the cost is low, the use is convenient, the sealing reliability of the bearing cavity is effectively improved, the service life of the bearing is prolonged, and the safety of the turbine engine is improved.
The design of the cooling cavity 12 will increase the space occupation of the intermediate fulcrum structure to some extent, and in order to compensate for the space structure of the part, space optimization design is performed in other parts.
Preferably, the disc center sealing ring 8 is provided with a first straight ring 13, the bearing sealing ring 9 is provided with a second straight ring 14, the second straight ring 14 is correspondingly arranged on the inner side of the first straight ring 13, the radial widths of the first straight ring 13 and the second straight ring 14 are as small as possible under the condition of meeting the air flow circulation capacity, and the design effectively reduces the space occupation of the cooling cavity 12 between the disc center sealing ring 8 and the bearing sealing ring 9. Preferably, an inner convex ring 15 is arranged at a position, corresponding to the outer side of the disc center sealing ring 8, of the low-pressure turbine disc 7, and the radial distance from the first flat ring 13 to the inner convex ring 15 is as small as possible under the condition that the airflow circulation capacity is met/the design effectively reduces the space occupation of the sealing exhaust cavity while the stable work of the sealing exhaust cavity is ensured. Referring to fig. 2, preferably, the bearing assembly includes a bearing outer ring 6, a bearing inner ring 4, bearing balls 5, and a gland nut 11; the bearing balls 5 are connected between the bearing outer ring 6 and the bearing inner ring 4, the bearing inner ring 4 and the compression nut 11 are both connected on the rear shaft sealing ring 3, and the bearing outer ring 6 is connected on the low-pressure turbine shaft 10; a first oil return passage 16 is formed between the bearing outer ring 6 and the bearing sealing ring 9, and an oil return hole is formed in the position of the low-pressure turbine shaft 10 corresponding to the first oil return passage 16; a second oil return passage 17 is arranged on the low-pressure turbine shaft 10, and the second oil return passage 17 is arranged corresponding to the bearing roller. Through the design of the double oil return flow paths, the inner side and the outer side of the bearing outer ring 6 are fully lubricated and cooled simultaneously, and the working reliability of the bearing is improved.
Referring to fig. 3, preferably, seam allowance connecting structures are arranged between any two adjacent structures of the bearing sealing ring 9, the bearing outer ring 6 and the low-pressure turbine shaft 10, bolt holes which are arranged correspondingly to each other are formed among the bearing sealing ring 9, the bearing outer ring 6 and the low-pressure turbine shaft 10, the bolt holes of the bearing outer ring 6 are located between the bolt holes of the bearing sealing ring 9 and the low-pressure turbine shaft 10, and long bolts 18 are connected in the bolt holes. Through the design of the connecting structure of the long bolt 18, the reliable centering connection of the bearing assembly, the bearing sealing ring 9 and the low-pressure turbine shaft 10 can be realized, the number of parts is reduced, the occupied space is reduced, and the structural reliability is improved.
In conclusion, through the reduction design of multiple space occupation, the bearing cavity can be cooled efficiently, the sealing gas is sealed efficiently, and meanwhile, the difference of the whole intermediary fulcrum structure is small compared with the original structure, and even the space occupation is smaller than that of the original intermediary fulcrum structure.
With reference to fig. 4, preferably, the long bolt 18 is provided with an inward concave ring 19, and the non-inward concave ring position on the long bolt 18 is connected with the bearing sealing ring 9, the bearing outer ring 6 and the bolt holes on the low-pressure turbine shaft 10, specifically, a small clearance fit is adopted to improve the connection stability of the rotor; the design of the inner grooves reduces the local rigidity of the long bolts 18 and improves the deformation coordination in the working process while ensuring the stable connection of all parts.
With reference to fig. 5, the cooling cavity 12 is preferably designed to compress the installation space of the long bolt 18, and for this reason, the end of the bolt hole of the bearing sealing ring 9 is provided with a local bevel 20, which solves the problem of small axial assembly space.
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 (5)

1. The utility model provides a to changeing middle fulcrum bearing chamber structure of turbine, locates between high-pressure turbine dish (1) and low pressure turbine dish (7), be equipped with first labyrinth between high-pressure turbine dish (1) and low pressure turbine dish (7), its characterized in that: the turbine comprises a high-vortex rear journal (2), a low-pressure turbine shaft (10), a disc center sealing ring (8), a bearing sealing ring (9), a rear shaft seal Yan Huan (3) and a bearing assembly; a bearing cavity is formed among the bearing sealing ring (9), the rear shaft seal Yan Huan (3) and the low-pressure turbine shaft (10), the bearing assembly is arranged in the bearing cavity, and a sealing exhaust cavity is formed among the disc center sealing ring (8), the low-pressure turbine disc (7) and the high-vortex rear journal (2); a second labyrinth is arranged between the disc core sealing ring (8) and the high vortex rear journal (2), and a third labyrinth is arranged between the bearing sealing ring (9) and the high vortex rear journal (2);
a cooling cavity (12) is formed among the disc center sealing ring (8), the bearing sealing ring (9) and the high-vortex rear journal (2), a plurality of groups of vent holes communicated with the cooling cavity (12) are formed in the conical arm of the low-pressure turbine shaft (10) along the circumferential direction, and the vent holes are communicated with outside air;
a first straight ring (13) is arranged on the disc center sealing ring (8), a second straight ring (14) is arranged on the bearing sealing ring (9), the second straight ring (14) is correspondingly arranged on the inner side of the first straight ring (13), and the radial width of the first straight ring (13) and the second straight ring (14) is smaller than the radial width between the first labyrinth and the second labyrinth;
an inner convex ring (15) is arranged at the position, corresponding to the outer side of the disk center sealing ring (8), of the low-pressure turbine disk (7), and the radial width from the first flat ring (13) to the inner convex ring (15) is smaller than the radial width from the first flat ring (13) to the outer surface of the first labyrinth.
2. The medium fulcrum bearing cavity structure of a counter-rotating turbine according to claim 1, wherein: the bearing assembly comprises a bearing outer ring (6), a bearing inner ring (4), bearing balls (5) and a compression nut (11); the bearing balls (5) are connected between the bearing outer ring (6) and the bearing inner ring (4), the bearing inner ring (4) and the gland nut (11) are connected to the rear shaft seal Yan Huan (3), and the bearing outer ring (6) is connected to the low-pressure turbine shaft (10); a first oil return passage (16) is formed between the bearing outer ring (6) and the bearing sealing ring (9), and an oil return hole is formed in the position, corresponding to the first oil return passage (16), of the low-pressure turbine shaft (10); and a second oil return passage (17) is arranged on the low-pressure turbine shaft (10), and the second oil return passage (17) is arranged corresponding to the bearing roller.
3. The medium fulcrum bearing cavity structure of a counter-rotating turbine according to claim 2, wherein: bolt holes which are arranged correspondingly to each other are formed among the bearing sealing ring (9), the bearing outer ring (6) and the low-pressure turbine shaft (10), the bolt holes of the bearing outer ring (6) are located between the bolt holes of the bearing sealing ring (9) and the low-pressure turbine shaft (10), and long bolts (18) are connected in the bolt holes.
4. The medium fulcrum bearing cavity structure of a counter-rotating turbine according to claim 3, wherein: an inward concave ring (19) is arranged on the long bolt (18), and the non-inward concave ring position on the long bolt (18) is connected with the bearing sealing ring (9), the bearing outer ring (6) and the bolt holes on the low-pressure turbine shaft (10).
5. The medium fulcrum bearing cavity structure of a counter-rotating turbine according to claim 4, wherein: the end part of the bolt hole of the bearing sealing ring (9) is provided with a local bevel angle (20).
CN202211113661.6A 2022-09-14 2022-09-14 Intermediate fulcrum bearing cavity structure of counter-rotating turbine Active CN115217536B (en)

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CN117345433B (en) * 2023-12-06 2024-02-06 成都中科翼能科技有限公司 Sealing assembly component of gas turbine exhaust casing

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RU2455511C1 (en) * 2011-03-11 2012-07-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Gas turbine engine
FR3018547B1 (en) * 2014-03-13 2019-07-12 Safran Aircraft Engines HIGH PRESSURE TURBINE DISCHARGE SEALING SYSTEM WITH CURVIC LINK
CN110005545B (en) * 2019-02-21 2020-08-18 西安航天动力研究所 Squirrel-cage elastic supporting bearing cavity structure
CN115030821A (en) * 2021-03-03 2022-09-09 中国航发商用航空发动机有限责任公司 Aeroengine bearing cavity labyrinth sealing structure
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CN114542205B (en) * 2022-02-11 2022-11-22 中国航发沈阳发动机研究所 High-temperature-resistant and high-pressure-resistant bearing cavity structure of high-mach aircraft engine

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