CN113882906B - Self-adaptive turbine outer ring block of aircraft engine - Google Patents
Self-adaptive turbine outer ring block of aircraft engine Download PDFInfo
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- CN113882906B CN113882906B CN202111213542.3A CN202111213542A CN113882906B CN 113882906 B CN113882906 B CN 113882906B CN 202111213542 A CN202111213542 A CN 202111213542A CN 113882906 B CN113882906 B CN 113882906B
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- outer ring
- block
- sliding block
- self
- ring block
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Classifications
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
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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
- F01D25/04—Antivibration arrangements
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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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a self-adaptive turbine outer ring block of an aircraft engine, wherein a high-pressure bleed air inlet is formed in the upper end of a shell of the self-adaptive turbine outer ring block; the sliding block a and the sliding block b are both provided with hook-shaped bulges and hinge mounting holes; the sliding block a is provided with a limiting column and a vent hole; the sliding block a and the sliding block b are arranged in a shell cavity of the outer ring block of the self-adaptive turbine, and two ends of the hinge are arranged in hinge mounting holes of two hook-shaped protrusions of the sliding block a and the sliding block b; the bottom end of the shell of the self-adaptive turbine outer ring block is provided with a boss, the wear-resistant coating block is arranged at the boss, and the wear-resistant coating block can move up and down at the boss; and the repulsion permanent magnets are embedded into two sides of the sliding block a and the sliding block b, and a gap is formed between the repulsion permanent magnets and the outer ring block shell of the self-adaptive turbine. The outer ring block of the turbine is self-adaptively controlled, and no matter the thrust is increased or reduced, the outer ring block of the turbine and the blade tip of the turbine blade can both ensure relatively small gaps, so that the engine keeps high efficiency, and simultaneously, the problem of collision and abrasion vibration caused by gap mismatching is avoided.
Description
Technical Field
The invention relates to the technical field of an outer ring block of a turbine of an aero-engine, in particular to an adaptive outer ring block of a turbine of an aero-engine.
Background
The outer ring block of the turbine of the aircraft engine is mainly matched with a turbine rotor blade, and the air quantity leaked from the gap between the tip of the turbine and the outer ring block is controlled in a semi-contact mode, so that the energy of gas is converted into mechanical work to the maximum extent. The conventional turbine outer ring block is generally fixed, and is affected by a high temperature difference when an engine works, so that the turbine outer ring block of the turbine blade has the problems of collision and abrasion caused by the fact that a gap is small or gas leakage quantity caused by the fact that the gap is large and the like. In the center of the prior art, as shown in fig. 1-3, when the engine increases thrust, the ambient temperature is increased, the turbine outer ring block with the wear-resistant coating is subjected to high thermal expansion deformation speed, the turbine rotor blades and the turbine disc are subjected to low thermal expansion deformation, gaps between the turbine rotor blades and the wear-resistant coating are enlarged, a large amount of gas leaks from the gaps, the efficiency of the engine is greatly reduced, and the thrust loss is large. When the engine reduces thrust, the ambient temperature is reduced, the turbine outer ring block with the wear-resistant coating is cooled, contracted and deformed at a high speed, the turbine rotor blade and the turbine disc are cooled, contracted and deformed slowly, gaps between the turbine rotor blade and the wear-resistant coating are reduced and then scraped, the efficiency of the engine is greatly reduced, and meanwhile, the problem of large vibration is caused.
Disclosure of Invention
The invention aims to provide an adaptive turbine outer ring block of an aircraft engine, which has the following specific scheme:
an adaptive turbine outer ring block of an aircraft engine comprises an adaptive turbine outer ring block shell, a sliding block a, a sliding block b, a repulsion permanent magnet and a wear-resistant coating block;
the shell of the self-adaptive turbine outer ring block is a sector section, and the upper end of the shell is provided with a high-pressure bleed air inlet;
hook-shaped bulges are arranged on the sliding block a and the sliding block b, and hinge mounting holes are formed in the hook-shaped bulges;
the sliding block a is provided with a limiting column and a vent hole;
the sliding block a and the sliding block b are arranged in a self-adaptive turbine outer ring block shell cavity, the sliding block a is arranged at the upper end, the sliding block b is arranged at the lower end, the hook-shaped bulges on the sliding block a and the sliding block b are vertically opposite on a straight line, and two ends of the hinge are arranged in hinge mounting holes of the hook-shaped bulges on the sliding block a and the sliding block b;
the bottom end of the shell of the self-adaptive turbine outer ring block is provided with a boss, the wear-resistant coating block is arranged at the boss, and the wear-resistant coating block can move up and down at the boss;
the repulsion permanent magnets are embedded into two sides of the sliding block a and the sliding block b, and a gap is formed between the repulsion permanent magnets and the shell of the self-adaptive turbine outer ring block;
a plurality of adaptive turbine outer ring blocks are arranged along the circumference of the turbine to form an adaptive turbine outer ring block assembly.
According to the preferred scheme, four repulsion permanent magnets are arranged in the adaptive turbine outer ring block.
The preferable scheme of the aeroengine self-adaptive turbine outer ring block is that the wear-resistant coating block is formed by coating, processing, shaping and heating in advance.
The aircraft engine self-adaptive turbine outer ring block is preferably characterized in that the hinge can be replaced by selecting different linear tensioning mechanisms.
The aircraft engine self-adaptive turbine outer ring block has the advantages that the bottom surface of the wear-resistant coating block is flush with or recessed from the lower surface of the outer ring block shell.
The working principle of the aeroengine self-adaptive turbine outer ring block is as follows: the position of the wear-resistant coating block is automatically adjusted through the pressure difference between high-pressure air and the pressure of gas reserved in the high-pressure air compressor, when the thrust of the engine is increased, the temperature is increased, the high-pressure air pressure led from the high-pressure air compressor is higher than the pressure of the gas in the flow channel, so that the wear-resistant coating block is tightly propped towards the direction of the high-pressure turbine blade, and the trend of gap enlargement caused by the temperature is eliminated; when the thrust of the engine is reduced, the high-pressure air is introduced from the high-pressure air compressor and becomes low, the pressure of the inner cavity of the outer ring block is smaller than the pressure of the gas in the flow channel through throttling and pressure reduction of the high-pressure air introducing inlet, the outer ring block moves towards the centrifugal direction, and the problems of gap reduction and collision and abrasion vibration caused by the gap reduction are solved. Through the self-adaptive control of the outer ring block of the turbine, no matter the thrust is increased or reduced, the outer ring block of the turbine and the blade tip of the turbine blade can both ensure relatively small gaps, so that the engine keeps high efficiency, and simultaneously, the problem of collision and abrasion vibration caused by gap mismatching is avoided.
Compared with the prior art, the invention has the beneficial effects that:
according to the mechanism such as the hook-shaped protrusion, the hinge and the repulsion permanent magnet, the wear-resistant coating is placed on the surface of the adjusted outer ring block, the turbine outer ring block is pushed to the minimum diameter state through the repulsion permanent magnet when an engine works, and the repulsion permanent magnet and the hinge on the hook-shaped protrusion delay the thermal deformation of the case along with the rise of the temperature of the engine, so that the case and the disc shaft blade deform coordinately and synchronously; meanwhile, the clearance control mode is mechanical, auxiliary control such as a control system and a hydraulic system is not needed, and the pressure of an engine control system and the weight of the whole engine are reduced. Through verification, the optimal clearance control between the turbine rotor blades and the turbine outer ring block can be realized; the energy conversion of the gas can be improved by about 3%, the oil consumption rate can be reduced by 2.5% by colleagues, and the fuel gas is suitable for various military and civil aviation engines.
Drawings
FIG. 1 is a schematic diagram of an outer ring block structure in a transmission structure;
FIG. 2 is a state diagram of an outer race block of the transmission of FIG. 1 during increased engine thrust;
FIG. 3 is a state diagram of an outer race block of the transmission of FIG. 1 during engine thrust reduction;
FIG. 4 is a schematic view of the structure of the present invention;
FIG. 5 is a state diagram of the outer ring block of the present invention during thrust augmentation of the engine;
FIG. 6 is a state diagram of the outer ring block of the present invention with the engine thrust reduced;
FIG. 7 is a state diagram of the adaptive turbine outer ring block assembly as the engine increases and decreases thrust.
In the figure, 1-self-adaptive turbine outer ring block shell, 2-slide block a, 3-slide block b, 4-repulsion permanent magnet, 5-wear-resistant coating block, 6-high-pressure bleed air inlet, 7-hook-shaped bulge, 8-limiting column, 9-vent hole, 10-hinge, 11-boss, 12-high-pressure air pressure, 13-air pressure in runner, 14-pressure difference and 15-repulsion force.
Detailed Description
The technical solutions in the present invention will be described clearly and completely with reference to the drawings in the present invention, and it should be apparent that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The specific implementation mode is as follows:
as shown in the attached figures 3-7, the self-adaptive turbine outer ring block of the aircraft engine comprises a self-adaptive turbine outer ring block shell 1, a sliding block a2, a sliding block b3, a repulsive force permanent magnet 4 and a wear-resistant coating block 5;
the self-adaptive turbine outer ring block shell 1 is a sector section, and the upper end of the self-adaptive turbine outer ring block shell is provided with a high-pressure bleed air inlet 6;
hook-shaped bulges 7 are arranged on the sliding block a2 and the sliding block b3, and hinge mounting holes are formed in the hook-shaped bulges 7;
the sliding block a2 is provided with a limiting column 8 and a vent hole 9;
the sliding block a2 and the sliding block b3 are arranged in a cavity of the self-adaptive turbine outer ring block shell 1, the sliding block a2 is arranged at the upper end, the sliding block b3 is arranged at the lower end, the sliding block a2 and the hook-shaped bulge 7 on the sliding block b3 are vertically opposite on a straight line, and two ends of the hinge 10 are arranged in hinge mounting holes of the hook-shaped bulges 7 on the sliding block a2 and the sliding block b 3;
the bottom end of the self-adaptive turbine outer ring block shell 1 is provided with a boss 11, the wear-resistant coating block 5 is arranged at the boss 11, and the wear-resistant coating block 5 can move up and down at the boss 11;
the repulsion permanent magnet 4 is embedded into the two sides of the sliding block a2 and the sliding block b3, and a gap is formed between the repulsion permanent magnet and the self-adaptive turbine outer ring block shell 1;
a plurality of adaptive turbine outer ring blocks are arranged along the circumference of the turbine to form an adaptive turbine outer ring block assembly.
Four repulsion permanent magnets 4 are arranged in the self-adaptive turbine outer ring block.
The wear-resistant coating block 2 is formed by coating processing in advance, shaping and heating.
The hinge 10 may be replaced by a different linear tensioning mechanism.
The bottom surface of the wear-resistant coating block 5 is flush with or recessed from the lower surface of the outer ring block shell.
The working principle of the aeroengine self-adaptive turbine outer ring block is as follows: the position of the wear-resistant coating block 5 is automatically adjusted through the pressure difference 14 between the high-pressure air pressure 12 and the gas pressure 13 in the flow channel, the repulsion permanent magnet can generate a stable repulsion force 15, when the thrust of the engine is increased, the temperature rises, the high-pressure air pressure led from the high-pressure compressor is higher than the gas pressure in the flow channel, so that the wear-resistant coating block is tightly propped towards the direction of a high-pressure turbine blade, and the trend of gap enlargement caused by the temperature is eliminated; when the thrust of the engine is reduced, the high-pressure air is introduced from the high-pressure air compressor, the pressure of the inner cavity of the outer ring block is reduced through throttling and pressure reduction of the high-pressure air introduction inlet, the pressure of the inner cavity of the outer ring block is smaller than the pressure of the gas in the flow channel, and the outer ring block moves towards the centrifugal direction, so that the problems of gap reduction and collision and grinding vibration caused by the gap reduction are solved. Through the self-adaptive control of the outer ring block of the turbine, no matter the thrust is increased or reduced, the outer ring block of the turbine and the blade tip of the turbine blade can both ensure relatively small gaps, so that the engine keeps high efficiency, and simultaneously, the problem of collision and abrasion vibration caused by gap mismatching is avoided.
Claims (5)
1. An aeroengine self-adaptation turbine outer ring piece which characterized in that: the self-adaptive turbine outer ring block comprises a self-adaptive turbine outer ring block shell, a sliding block a, a sliding block b, a repulsive force permanent magnet and a wear-resistant coating block;
the shell of the self-adaptive turbine outer ring block is a sector section, and the upper end of the shell is provided with a high-pressure bleed air inlet;
hook-shaped bulges are arranged on the sliding block a and the sliding block b, and hinge mounting holes are formed in the hook-shaped bulges;
the sliding block a is provided with a limiting column and a vent hole;
the sliding block a and the sliding block b are arranged in a self-adaptive turbine outer ring block shell cavity, the sliding block a is arranged at the upper end, the sliding block b is arranged at the lower end, the hook-shaped bulges on the sliding block a and the sliding block b are vertically opposite on a straight line, and two ends of the hinge are arranged in hinge mounting holes of the hook-shaped bulges on the sliding block a and the sliding block b;
the bottom end of the shell of the self-adaptive turbine outer ring block is provided with a boss, the wear-resistant coating block is arranged at the boss, and the wear-resistant coating block can move up and down at the boss;
the repulsion permanent magnets are embedded into two sides of the sliding block a and the sliding block b, and a gap is formed between the repulsion permanent magnets and the shell of the self-adaptive turbine outer ring block;
a plurality of adaptive turbine outer ring blocks are arranged along the circumference of the turbine to form an adaptive turbine outer ring block assembly.
2. An aircraft engine adaptive turbine outer ring block according to claim 1, wherein: four repulsion permanent magnets are arranged in the self-adaptive turbine outer ring block.
3. An aircraft engine adaptive turbine outer ring block according to claim 1, characterized in that: the wear-resistant coating block is formed by coating processing, shaping and heating in advance.
4. An aircraft engine adaptive turbine outer ring block according to claim 1, wherein: the hinge can be replaced by a different linear tensioning mechanism.
5. An aircraft engine adaptive turbine outer ring block according to claim 1, wherein: the bottom surface of the wear-resistant coating block is flush with or recessed from the lower surface of the outer ring block shell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111213542.3A CN113882906B (en) | 2021-10-18 | 2021-10-18 | Self-adaptive turbine outer ring block of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111213542.3A CN113882906B (en) | 2021-10-18 | 2021-10-18 | Self-adaptive turbine outer ring block of aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113882906A CN113882906A (en) | 2022-01-04 |
| CN113882906B true CN113882906B (en) | 2023-04-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111213542.3A Active CN113882906B (en) | 2021-10-18 | 2021-10-18 | Self-adaptive turbine outer ring block of aircraft engine |
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Citations (6)
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|---|---|---|---|---|
| US5127793A (en) * | 1990-05-31 | 1992-07-07 | General Electric Company | Turbine shroud clearance control assembly |
| CN105545494A (en) * | 2009-01-15 | 2016-05-04 | 通用电气公司 | Compressor clearance control system using turbine exhaust |
| CN107605792A (en) * | 2016-07-11 | 2018-01-19 | 通用电气公司 | The passive clearance control of GTC |
| CN107882599A (en) * | 2017-11-01 | 2018-04-06 | 中国航发湖南动力机械研究所 | Monoblock type turbine outer ring attachment structure and turbogenerator |
| CN212535780U (en) * | 2020-07-03 | 2021-02-12 | 中国航发商用航空发动机有限责任公司 | Tip clearance control assembly, gas turbine engine, and aircraft |
| CN112554960A (en) * | 2020-12-02 | 2021-03-26 | 中国航发沈阳发动机研究所 | Turbine rotor blade apex structure and have its turbine rotor |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NZ551475A (en) * | 2004-05-17 | 2010-09-30 | Carlton Forge Works | Turbine case reinforcement in a gas turbine jet engine |
| US7740443B2 (en) * | 2006-11-15 | 2010-06-22 | General Electric Company | Transpiration clearance control turbine |
-
2021
- 2021-10-18 CN CN202111213542.3A patent/CN113882906B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5127793A (en) * | 1990-05-31 | 1992-07-07 | General Electric Company | Turbine shroud clearance control assembly |
| CN105545494A (en) * | 2009-01-15 | 2016-05-04 | 通用电气公司 | Compressor clearance control system using turbine exhaust |
| CN107605792A (en) * | 2016-07-11 | 2018-01-19 | 通用电气公司 | The passive clearance control of GTC |
| CN107882599A (en) * | 2017-11-01 | 2018-04-06 | 中国航发湖南动力机械研究所 | Monoblock type turbine outer ring attachment structure and turbogenerator |
| CN212535780U (en) * | 2020-07-03 | 2021-02-12 | 中国航发商用航空发动机有限责任公司 | Tip clearance control assembly, gas turbine engine, and aircraft |
| CN112554960A (en) * | 2020-12-02 | 2021-03-26 | 中国航发沈阳发动机研究所 | Turbine rotor blade apex structure and have its turbine rotor |
Non-Patent Citations (1)
| Title |
|---|
| 高杰等.燃气轮机涡轮叶顶间隙气热技术研究进展.航空学报.2017,第38卷(第9期),521019-1~31. * |
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| CN113882906A (en) | 2022-01-04 |
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