CN113847147B - Air-entraining and dust-removing structure for internal cooling air of aircraft engine - Google Patents
Air-entraining and dust-removing structure for internal cooling air of aircraft engine Download PDFInfo
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- CN113847147B CN113847147B CN202111120731.6A CN202111120731A CN113847147B CN 113847147 B CN113847147 B CN 113847147B CN 202111120731 A CN202111120731 A CN 202111120731A CN 113847147 B CN113847147 B CN 113847147B
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- air
- combustion chamber
- cooling air
- entraining
- dust
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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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
Abstract
The utility model relates to an aeroengine's dust removal technical field for an aeroengine inside cooling air's bleed dust removal structure, including locating the cooling gas circuit between high-pressure drum barrel connecting axle and the combustion chamber internal casing, the bleed circumferential weld that communicates with the high-pressure compressor export is seted up to the one end that cooling gas circuit is close to the high-pressure compressor export, set up the air inlet hole with the cooling gas circuit intercommunication on the combustion chamber internal casing, air inlet hole locates one side that the combustion chamber internal casing is close to combustion chamber import diffuser, be equipped with the first current-limiting piece that reduces bleed circumferential weld air input between cooling gas circuit and the bleed circumferential weld. The dust filter has the technical effects of effectively filtering the dust of the cooling gas entering the cooling gas circuit and improving the operation efficiency and quality of the aero-engine.
Description
Technical Field
The application belongs to the technical field of dust removal of aircraft engines, in particular to an air-entraining dust removal structure for cooling air in an aircraft engine.
Background
When a modern civil aircraft executes tasks, the modern civil aircraft is required to have all-weather and all-AREA flight capability, and often works in complex regions or severe weather environments, such as desert regions of middle east, northwest africa, xinjiang China and the like, sand weather, haze weather and the like, and when the engine is lifted, landed and flies in the severe air environments, a large amount of sand dust is sucked.
The cooling air introduced from the main flow passage of the engine into the engine may be adhered and gathered in a high temperature environment, deteriorating the working environment of the parts. When cooling air containing a large amount of sand dust flows into the turbine blade, the bonded sand dust particles block the air film holes or the internal cooling channels of the turbine air-cooled blade, so that the flow is blocked, the cooling effect of the turbine blade is influenced, and the blade is prematurely over-temperature ablated. Between the blade flanges, sand dust will cause the sealed vibration damping sheets to be adhered, so as to change the damping effect of the vibration damping sheets and cause fatigue fracture of the turbine blades.
The research results of the published documents show that the engine failure is obviously increased in the dusty environment, the maintenance interval is shortened, and the service life is far lower than that of other areas. Therefore, the degree of cleanliness of the cooling air is related to the life, economy, and safety of the engine.
In the design of the existing engine air system, most of air for cooling the turbine is guided from the outlet of the high-pressure compressor, and no special dust removal structure design measure is adopted for the guided cooling air.
Therefore, how to effectively reduce the sand dust entering in the cooling gas circuit of the engine is a problem to be solved.
Disclosure of Invention
The application aims at providing an aeroengine inside cooling air's bleed dust removal structure to solve among the prior art problem that sand and dust enters into engine cooling gas circuit easily and leads to the engine performance to descend.
The technical scheme of the application is as follows: the utility model provides an aeroengine inside cooling air's bleed dust removal structure, is including locating the cooling gas circuit between high-pressure drum barrel connecting axle and the combustion chamber internal casing, and the bleed circumferential weld that communicates with the high-pressure compressor export is seted up to the one end that the cooling gas circuit is close to the high-pressure compressor export, set up the inlet opening with the cooling gas circuit intercommunication on the combustion chamber internal casing, inlet opening locates one side that the combustion chamber internal casing is close to the combustion chamber import, be equipped with the first current-limiting piece that reduces bleed circumferential weld air input between cooling gas circuit and the diffuser bleed circumferential weld.
Preferably, the one end that combustion chamber import diffuser is close to the combustion chamber is equipped with first guide plate and second guide plate, be the combustion chamber import between first guide plate and the second guide plate, one side that is close to the quick-witted casket in the combustion chamber is located to first guide plate, it separates the chamber for triangular annular to form the cross section between quick-witted casket in the combustion chamber and the first guide plate, the air inlet through hole is seted up on the inner wall that the annular separates the chamber.
Preferably, the air inlet through holes are arranged in a plurality of groups and uniformly spaced along the circumferential direction of the casing in the combustion chamber.
Preferably, the casing in the combustion chamber comprises a flow guiding section and a sand accumulating section, the flow guiding section is obliquely arranged, the annular separation cavity is formed between the flow guiding section and the first flow guiding plate, and the sand accumulating section is connected with the flow guiding section and can accumulate sand and dust.
Preferably, the first flow limiting piece comprises a first labyrinth arranged on a connecting shaft of the high-pressure drum and a first sealing plate arranged on a casing in the combustion chamber, and a gap between the end part of the first labyrinth and the first sealing plate is used for cooling air at the air-entraining circular seam to enter.
Preferably, at least two groups of teeth of the first grate teeth are arranged and are arranged at intervals along the air inlet direction of the cooling air.
Preferably, the first labyrinth is a step tooth, the length of the tooth of the first labyrinth close to the air-entraining circular seam is greater than that of the tooth of the other side, and the first sealing plate is provided with a step corresponding to the first labyrinth.
Preferably, an arc-shaped transition is formed between one side of the first grid tooth, which is close to the air-entraining circular seam, and the high-pressure drum connecting shaft, and an included angle formed between the high-pressure drum connecting shaft and the first grid tooth is an acute angle, so that an annular sand accumulation cavity is formed.
Preferably, one end of the cooling air path, which is far away from the air-entraining circular seam, is provided with a second labyrinth and a second sealing plate which are correspondingly arranged.
Preferably, at least two groups of second grid teeth are arranged and are arranged at intervals along the air inlet direction of cooling air, and the second grid teeth are flat teeth.
The utility model provides an aeroengine inside cooling air's bleed dust removal structure, set up the air inlet hole with the cooling gas circuit intercommunication on the casing in the combustion chamber, locate one side that the casing is close to combustion chamber inlet diffuser with the air inlet hole in the combustion chamber, through the reverse flow of air current and the weak flow swirl of formation in order to get rid of the dust and sand in the cooling air is effectual, will get into the dust and sand of cooling gas circuit by the bleed circumferential weld and get rid of through setting up first current-limiting piece, guarantee to enter into the quality of the air in the cooling gas circuit, the quality of cooling is carried out to the engine to the assurance, the operating efficiency of engine obtains guaranteeing.
Preferably, the combustor casing forms an annular partition chamber with a triangular cross section by matching with the first guide plate so as to ensure that the cooling gas entering the annular partition chamber can effectively form weak vortex to effectively filter the dust and sand.
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.
1. A last stage disc of the high-pressure compressor; 2. a high-pressure drum connecting shaft; 3. a combustor inlet diffuser; 4. a combustion chamber inner casing; 5. a first comb tooth; 6. a second comb tooth; 7. a first sealing plate; 8. a second sealing plate; 9. air-entraining circular seams; 10. an air inlet through hole; 11. a first baffle; 12. a second baffle; 13. a drainage section; 14. a sand accumulation section; 15. a sand accumulation cavity; 16. and cooling the gas circuit.
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.
A bleed air dust removal structure for cooling air in an aircraft engine is shown in figure 1, wherein the cooling air is blown out from an outlet of a high-pressure air compressor to form two cooling air flows. The first cooling air flow is a main flow passage and enters from a diffuser 3 at the inlet of the combustion chamber, and then a part of the first cooling air flow is blown into the combustion chamber; the other part of the air flow is blown into the inner ring of the combustion chamber, the air flow blown into the inner ring of the combustion chamber cools the combustion chamber through the outer surface of the combustion chamber, and then the air flow continues backwards and is used for cooling the flame tube and the like.
A cooling air path 16 is arranged between the high-pressure drum connecting shaft 2 and the casing 4 in the combustion chamber, the high-pressure drum connecting shaft 2 is connected with the high-pressure compressor final disc 1, the cooling air path 16 is an annular air path, an air-entraining annular seam 9 is arranged at one end of the cooling air path close to the outlet of the high-pressure compressor, and a second cooling air flow enters the cooling air path 16 from the air-entraining annular seam 9 and is used for cooling the high-pressure turbine working blade. The flow requirement of the second cooling air flow is much smaller than that of the first cooling air flow.
An air inlet through hole 10 communicated with a cooling air path 16 is formed in the combustion chamber casing, the air inlet through hole 10 is formed in one side, close to the combustion chamber inlet diffuser 3, of the combustion chamber casing 4, and a first flow limiting piece for reducing air inflow of the air introducing annular gap 9 is arranged between the cooling air path 16 and the air introducing annular gap 9.
After the engine sucks sand and dust, the main flow passage is sand and dust-containing airflow, the inner ring air of the combustion chamber is sourced from the main flow passage, the sand and dust content is high, the sand and dust is carried under the flowing inertia effect of the inner ring airflow in the combustion chamber, the momentum in the flowing direction is high, the air inlet through hole 10 is arranged on one side of the casing 4 in the combustion chamber close to the inlet diffuser 3 of the combustion chamber, the flowing direction of cooling airflow passing through the air inlet through hole 10 is opposite to that of most of the airflow, the flow speed is reduced, the sand and dust are easy to separate from the cooling airflow, and the airflow is difficult to completely enter because the cross section of the air inlet through hole 10 is far smaller than other flow paths, so that a clockwise weak flowing vortex is formed at the air inlet end of the air inlet through hole 10, and the sand and dust is thrown out through centrifugal force. When the cooling air containing sand dust enters from the air-entraining circular seam 9 and passes through the first flow-limiting piece, the sand dust and most of the cooling air are blocked, so that only a small amount of filtered cooling air enters the cooling air path 16. Therefore, the sand content of the cooling air entering the cooling air path 16 from the air inlet through hole 10 is effectively reduced, and the adverse effect of the sand dust contained in the cooling air on the working blade of the high-pressure turbine is effectively avoided.
Meanwhile, the initial cost is not increased due to the optimized design of the structure of the bleed air flow path, and meanwhile, the purified cooling flow path avoids the adverse effects of abrasion, blockage, heat exchange deterioration and the like of parts caused by sand and dust, so that the engine faults are greatly reduced, the maintenance period of the engine is shortened, and the comprehensive use cost of the generator is remarkably reduced.
Compared with the sand-containing air, the purified cooling air improves the use efficiency of parts, thereby improving the use efficiency of the whole engine.
Preferably, a first guide plate 11 and a second guide plate 12 are arranged at one end, close to the combustion chamber, of the outlet diffuser of the combustion chamber, an inlet of the combustion chamber is formed between the first guide plate 11 and the second guide plate 12, the first guide plate 11 is arranged on one side of a casing 4 in the combustion chamber, an annular partition chamber with a triangular cross section is formed between the casing 4 and the first guide plate 11 in the combustion chamber, and the air inlet through hole 10 is formed in the inner wall of the annular partition chamber.
After the cooling gas containing sand enters the annular separation cavity, because the size of the air inlet through holes 10 is small, the air which cannot enter the air inlet through holes 10 circularly flows at the annular separation cavity, so that weak flow vortexes can be effectively formed to filter sand dust, and the quality of the cooling gas entering the cooling gas circuit 16 is ensured.
Preferably, the intake through holes 10 are provided in plural sets and spaced apart along the circumferential direction of the combustion chamber casing 4. The plurality of air inlet through holes 10 respectively enter the cooling air path 16 from different positions, so that the amount of cooling air is enough to effectively cool the high-pressure turbine blade.
Preferably, the combustion chamber casing 4 comprises a flow guiding section 13 and a sand accumulation section 14, the flow guiding section 13 is arranged obliquely and forms an annular compartment with the first flow guiding plate 11, and the sand accumulation section 14 is connected with the flow guiding section 13 and can accumulate sand and dust. Because the height of the flow guiding section 13 is greater than that of the sand deposition section 14, filtered sand and dust can be accumulated at the sand deposition section 14 without influencing air inlet of the air inlet through hole 10, and the sand and dust can be regularly cleaned.
Preferably, the first flow limiting piece comprises a first labyrinth 5 arranged on the high-pressure drum connecting shaft 2 and a first sealing plate 7 arranged on the combustion chamber casing 4, and a gap between the end part of the first labyrinth 5 and the first sealing plate 7 is used for introducing cooling air at the air-introducing annular seam 9. Through mutual cooperation of first labyrinth 5 and first board 7 of obturating, can carry out effectual blockking to the cooling gas that gets into from bleed circumferential weld 9, block the admitting air of most cooling gas and sand and dust, realize the filtration to the cooling gas, guarantee the quality of the air in the cooling gas circuit 16.
Preferably, the first grate 5 has at least two sets of teeth and is arranged at intervals along the air intake direction of the cooling air. As shown in fig. 1, the number of the racks of the first grid section 5 is 2, but is not limited to 2, and by arranging at least two sets of grid sections, the dust and sand at the bleed air circular seam 9 can be effectively blocked.
Preferably, the first labyrinth 5 is a step tooth, the length of the tooth of the first labyrinth 5 on one side close to the air-entraining annular seam 9 is greater than that of the tooth on the other side, and the first sealing plate 7 is provided with a step corresponding to the first labyrinth 5. Through the labyrinth structure of obturating that sets up the step, the air that contains sand makes the route that contains sand air admission increase on the one hand when entering into step department, and on the other hand makes the route that contains sand air admission more crooked for the filterable effect of dust and sand is better.
Preferably, the first grid section 5 is in arc transition with the high-pressure drum connecting shaft 2 at one side close to the air-entraining circular seam 9, an included angle between the high-pressure drum connecting shaft 2 and the first grid section 5 is an acute angle to form an annular sand accumulation cavity 15, the cross section of the annular sand accumulation cavity 15 is triangular, sand and dust left after being filtered at the first grid section 5 is accumulated in the sand accumulation cavity 15, the air inflow of the cooling air containing sand at the air-entraining circular seam 9 cannot be influenced, and the sand and dust in the sand accumulation cavity 15 can be regularly cleaned.
Preferably, one end of the cooling air flow, which is far away from the air-entraining circumferential weld 9, is provided with a second labyrinth 6 and a second sealing plate 8 which are correspondingly arranged, and the second labyrinth 6 and the second sealing plate 8 can simultaneously filter the sand-containing cooling air entering from the air inlet through hole 10 and the air-entraining circumferential weld 9, so that the air quality is further improved, and the operating efficiency and the quality of the engine are improved.
Preferably, at least two groups of second grid teeth 6 are arranged and are arranged at intervals along the air inlet direction of the cooling air, and the second grid teeth 6 are flat teeth. As shown in fig. 1, the number of teeth of the labyrinth is preferably three, so as to ensure the filtering quality, and the obturating labyrinth arranged by the flat teeth can ensure that the cooling air can enter the subsequent space more smoothly.
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 (7)
1. The utility model provides an aeroengine inside cooling air's bleed dust removal structure which characterized in that: the cooling air path (16) is arranged between a high-pressure drum connecting shaft (2) and a casing (4) in a combustion chamber, one end, close to an outlet of a high-pressure compressor, of the cooling air path (16) is provided with a gas-entraining circular seam (9) communicated with the outlet of the high-pressure compressor, the casing (4) in the combustion chamber is provided with a gas inlet through hole (10) communicated with the cooling air path (16), the gas inlet through hole (10) is arranged on one side, close to an inlet diffuser (3) of the combustion chamber, of the casing (4) in the combustion chamber, and a first flow limiting piece for reducing the air inflow of the gas-entraining circular seam (9) is arranged between the cooling air path (16) and the gas-entraining circular seam (9);
the first flow limiting piece comprises a first labyrinth tooth (5) arranged on the high-pressure drum connecting shaft (2) and a first sealing plate (7) arranged on the casing (4) in the combustion chamber, and a gap between the end part of the first labyrinth tooth (5) and the first sealing plate (7) is used for cooling air at the air-entraining circular seam (9) to enter;
the number of teeth of the first grate teeth (5) is at least two and the first grate teeth are arranged at intervals along the air inlet direction of cooling air;
the first labyrinth tooth (5) is a step tooth, the length of the tooth of one side, close to the air-entraining circular seam (9), of the first labyrinth tooth (5) is larger than that of the tooth of the other side, and the first sealing plate (7) is provided with a step corresponding to the first labyrinth tooth (5).
2. The bleed air dust removal structure for the interior cooling air of an aircraft engine according to claim 1, wherein: one end that combustion chamber import diffuser (3) is close to the combustion chamber is equipped with first guide plate (11) and second guide plate (12), be the combustion chamber import between first guide plate (11) and second guide plate (12), one side that is close to combustion chamber internal casing (4) is located in first guide plate (11), it is triangle-shaped annular partition chamber to form the cross section between internal casing (4) of combustion chamber and first guide plate (11), admit air through-hole (10) are seted up on the inner wall that the annular partition chamber was separated.
3. The bleed air dust removal structure for the interior cooling air of an aircraft engine according to claim 2, wherein: the air inlet through holes (10) are multiple groups and are uniformly arranged along the circumferential direction of the combustion chamber inner casing (4) at intervals.
4. An air entraining dust removing structure for cooling air inside an aircraft engine according to claim 2, wherein: the combustion chamber inner casing (4) comprises a flow guide section (13) and a sand accumulation section (14), the flow guide section (13) is obliquely arranged and forms an annular separation cavity with the first flow guide plate (11), and the sand accumulation section (14) is connected with the flow guide section (13) and can accumulate sand and dust.
5. An air entraining dust removing structure for cooling air inside an aircraft engine according to claim 1, wherein: one side of the first grid tooth (5) close to the air-entraining circular seam (9) is in arc transition with the high-pressure drum connecting shaft (2), and an included angle between the high-pressure drum connecting shaft (2) and the first grid tooth (5) is an acute angle so as to form an annular sand accumulation cavity (15).
6. The bleed air dust removal structure for the interior cooling air of an aircraft engine according to claim 1, wherein: and one end of the cooling gas path (16) far away from the air-entraining circular seam (9) is provided with a second labyrinth (6) and a second sealing plate (8) which are correspondingly arranged.
7. The bleed air dust removal structure for the interior cooling air of an aircraft engine according to claim 6, wherein: the number of teeth of the second grid teeth (6) is at least two, and the second grid teeth (6) are arranged at intervals along the air inlet direction of cooling air and are flat teeth.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111120731.6A CN113847147B (en) | 2021-09-24 | 2021-09-24 | Air-entraining and dust-removing structure for internal cooling air of aircraft engine |
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| CN202111120731.6A CN113847147B (en) | 2021-09-24 | 2021-09-24 | Air-entraining and dust-removing structure for internal cooling air of aircraft engine |
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| CN113847147A CN113847147A (en) | 2021-12-28 |
| CN113847147B true CN113847147B (en) | 2023-01-17 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114483310B (en) * | 2022-01-25 | 2023-07-04 | 中国联合重型燃气轮机技术有限公司 | Dustproof structure of heavy-duty gas turbine |
| CN115013837B (en) * | 2022-05-12 | 2023-08-18 | 中国航发四川燃气涡轮研究院 | Be used for aeroengine combustion chamber diffuser bleed air structure |
| CN115289499B (en) * | 2022-10-08 | 2023-01-10 | 成都中科翼能科技有限公司 | Hollow support plate of gas inlet of combustion chamber of gas turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104879324A (en) * | 2015-05-21 | 2015-09-02 | 中国南方航空工业(集团)有限公司 | Engine air cooling system |
| CN207962721U (en) * | 2017-12-28 | 2018-10-12 | 中国航发商用航空发动机有限责任公司 | A kind of combustion chamber and aero-engine |
| CN110318874A (en) * | 2019-06-24 | 2019-10-11 | 中国科学院工程热物理研究所 | The control whirlpool flow path system of centrifugal compressor back chamber in a kind of gas turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2904038A1 (en) * | 2006-07-19 | 2008-01-25 | Snecma Sa | Centrifugal compressor impeller downstream face cooling system for aircraft turbomachine e.g. turbojet and jet prop engines, has cylindrical passage and sheet guiding drawn ventilating air till neighborhood of downstream face of impeller |
| US8147178B2 (en) * | 2008-12-23 | 2012-04-03 | General Electric Company | Centrifugal compressor forward thrust and turbine cooling apparatus |
| FR2950656B1 (en) * | 2009-09-25 | 2011-09-23 | Snecma | VENTILATION OF A TURBINE WHEEL IN A TURBOMACHINE |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104879324A (en) * | 2015-05-21 | 2015-09-02 | 中国南方航空工业(集团)有限公司 | Engine air cooling system |
| CN207962721U (en) * | 2017-12-28 | 2018-10-12 | 中国航发商用航空发动机有限责任公司 | A kind of combustion chamber and aero-engine |
| CN110318874A (en) * | 2019-06-24 | 2019-10-11 | 中国科学院工程热物理研究所 | The control whirlpool flow path system of centrifugal compressor back chamber in a kind of gas turbine |
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