CN113550828B - Split type centrifugal ventilator structure of aeroengine - Google Patents
Split type centrifugal ventilator structure of aeroengine Download PDFInfo
- Publication number
- CN113550828B CN113550828B CN202110771928.XA CN202110771928A CN113550828B CN 113550828 B CN113550828 B CN 113550828B CN 202110771928 A CN202110771928 A CN 202110771928A CN 113550828 B CN113550828 B CN 113550828B
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- gas
- inner ring
- oil
- outer ring
- supporting parts
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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
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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
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a split type centrifugal ventilator structure of an aircraft engine, which relates to the technical field of aircraft engines and comprises a gear shaft, wherein one end of the gear shaft is provided with a gas channel, and separated gas obtained after oil-gas separation is discharged out of a gear box; the oil-gas separator consists of an inner ring, an outer ring and a plurality of supporting walls between the inner ring and the outer ring, wherein the inner ring is provided with a plurality of first supporting parts and a plurality of second supporting parts, one end of the inner ring is provided with a plurality of inner ring claw grooves, and one end of the outer ring is provided with a plurality of outer ring claw grooves; the wheel disk-shaped gear is matched with the oil-gas separator for use to prevent the oil-gas mixture from leaking from the oil-gas separator. According to the invention, through the combined design of the gear and the oil-gas separator, the oil-gas separator can effectively and stably separate the oil gas of the gear box while transmitting power, does not occupy a large installation space, reduces the weight and the cost, and effectively improves the integrated design level of the gear box component.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to a split type centrifugal ventilator structure of an aero-engine.
Background
The accessory transmission gear box is a key part of an aeroengine, a transmission gear of the accessory transmission gear box can generate a large amount of heat during operation, lubricating oil is required to be continuously utilized for circulating heat dissipation and lubrication, a large amount of gas-liquid mixtures such as oil mist, oil gas and the like can be generated in the transmission gear box in the lubricating oil circulating lubrication process, and certain influence can be caused on the lubricating oil heat dissipation and the internal pressure of the gear box, so that corresponding devices are required to be adopted for gas-liquid separation of oil gas in the gear box; the traditional solution is to design an independent mounting interface platform on an accessory transmission gear box, mount an oil-gas separator, provide power for the gear box to drive the gear box to work, and carry out gas-liquid separation on oil gas in the gear box through pipeline connection.
Meanwhile, the oil-gas separator in the prior art is complex in structure, large in weight and size and poor in maintainability, and causes certain technical difficulty for the layout of the accessory transmission gear box.
Therefore, the technical personnel in the field provide a split type centrifugal ventilator structure of an aircraft engine to solve the problems in the background art.
Disclosure of Invention
The invention aims to provide a split type centrifugal ventilator structure of an aircraft engine, and solves the problems that in the prior art, an accessory transmission gear box needs to design an independent accessory installation space and a power output port for an oil-gas separator, so that the number of engine parts is large and the maintenance complexity is high.
According to one aspect of the invention, a split type centrifugal ventilator structure of an aircraft engine is provided, which comprises a gear shaft, wherein one end of the gear shaft is provided with a gas channel, the gas channel is a circular counter bore, one end of the gas channel, which is far away from the end face of the gear shaft, is provided with a channel inlet for introducing separated gas after oil-gas separation, the gear shaft is provided with a meshing gear outside the gas channel, which is close to the channel inlet, and the gear shaft is provided with a plurality of shaft shoulders and bosses for axially limiting parts of a gear box; the oil-gas separator consists of an inner ring, an outer ring and a plurality of supporting walls between the inner ring and the outer ring, the sections of the inner ring and the outer ring are both in a circular ring shape, one end of the inner ring is provided with a plurality of first supporting parts, a plurality of second supporting parts are arranged inside the inner ring, one end of the inner ring, which is far away from the first supporting parts, is provided with a plurality of inner ring claw grooves, and one end of the outer ring, which is at the same side as the inner ring claw grooves, is provided with a plurality of outer ring claw grooves; the oil-gas separator is characterized in that the wheel disk gear is provided with a wheel disk, the wall surface of the wheel disk gear is divided into a plane and a wheel disk surface, and the plane is attached to the end surfaces of the inner ring and the outer ring of the oil-gas separator, which are provided with claw grooves, so that the oil-gas mixture cannot leak from the oil-gas separator.
According to an exemplary embodiment of the invention, any two adjacent supporting walls of the oil-gas separator, the inner ring, the outer ring and the wheel with spoke plate form an oil-gas separation chamber, the claw grooves of the inner ring and the wheel with spoke plate form a gas outlet of the separation chamber, and the claw grooves of the outer ring and the wheel with spoke plate form a liquid-oil outlet of the separation chamber.
According to another exemplary embodiment of the present invention, the inner ring detent groove has a groove depth greater than that of the outer ring detent groove, and the inner ring detent groove width is smaller than that of the outer ring detent groove.
According to another exemplary embodiment of the present invention, a plurality of left end surfaces of the first supporting portions are attached to a right end surface of the meshing gear, and a plurality of right end surfaces of the first supporting portions are in the same plane with the left end surface of the channel inlet.
According to another exemplary embodiment of the invention, a number of said second support parts left end faces are in the same plane as the channel inlet right end face.
According to another exemplary embodiment of the present invention, the second supporting portion is provided at a central position of any two inner ring claw groove intervals, the width of the second supporting portion is smaller than the distance of any two inner ring claw groove intervals, the number of the first supporting portion and the second supporting portion is the same and is at least three, and the first supporting portion and the second supporting portion are on the same axis.
According to another exemplary embodiment of the present invention, the pressure in the oil-gas separation chamber is 0.01-0.05MPa greater than the pressure in the gas channel.
According to another exemplary embodiment of the invention, an outlet end of the gas channel is provided with a gas path adapter, one end of the gas path adapter is suitable for being assembled on a gear shaft, the other end of the gas path adapter is connected with the tail part of the aircraft engine, and the joint of the gas path adapter and the tail part of the aircraft engine is in a negative pressure state.
According to another exemplary embodiment of the present invention, the rotational speed of the gear shaft is at least 20000 r/min.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, through the combined design of the gear and the oil-gas separator, the oil-gas separator can effectively and stably separate the oil gas of the gearbox while transmitting power, does not need to occupy larger installation space, reduces the weight and the cost, effectively improves the integrated design level of the gearbox component, and has the advantages of compact structure, good economy and low maintenance cost.
2. The oil-gas separator adopts the structural design of the inner ring and the outer ring double-claw grooves, and the oil-gas separation is realized by skillfully matching the self structure of the duplicate gear.
3. The centrifugal ventilator is split, and different separation efficiencies can be obtained by adjusting the structure of the oil-gas separator (parameters such as the number of the claw grooves, the groove width, the outline size and the like) to replace oil-gas separators with different specifications without changing the structure of the transmission chain.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is a sectional view of a split type centrifugal ventilator structure of an aircraft engine;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
FIG. 3 is a cross-sectional view of the gear shaft;
FIG. 4 is an overall structure schematic diagram of an oil-gas separator;
FIG. 5 is a front view of an oil-gas separator;
fig. 6 is a sectional view B-B of fig. 5.
In the figure: 1. pressing a plate; 2. locking the nut; 3. a first bearing; 4. a first support case; 5. a toothed wheel with a web; 6. an oil-gas separator; 601. a support wall; 602. an inner ring claw groove; 603. an outer ring claw groove; 604. an oil-gas separation chamber; 605. a separation chamber gas outlet; 606. a separation chamber liquid oil outlet; 607. a first support section; 608. a second support portion; 7. a gear shaft; 701. a gas channel; 702. a channel inlet; 703. a meshing gear; 8. a second bearing; 9. a second support case; 10. dynamic sealing; 11. a gas circuit adapter; 12. a cover plate; 13. sealing the rubber ring; 14. oil-gas mixture; 15. a liquid oil; 16. the gas is separated.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention are further described in detail below by way of examples with reference to the accompanying drawings. In the specification, the same or similar reference numerals denote the same or similar components. The following description of the embodiments of the present invention with reference to the accompanying drawings is intended to explain the general inventive concept of the present invention and should not be construed as limiting the invention.
Furthermore, in the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. In other instances, well-known structures and devices are shown in schematic form in order to simplify the drawing.
According to a general technical concept of the invention, a split type centrifugal ventilator structure of an aircraft engine is provided, which comprises a gear shaft 7, wherein one end of the gear shaft 7 is provided with a gas channel 701, the gas channel 701 is a circular counter bore, one end of the gas channel 701, which is far away from the end face of the gear shaft 7, is provided with a channel inlet 702 for introducing separated gas 16 after oil-gas separation, a meshing gear 703 is arranged at the position, which is close to the channel inlet 702, outside the gas channel 701 of the gear shaft 7, and the gear shaft 7 is provided with a plurality of shaft shoulders and bosses for axially limiting various parts of a gear box; the oil-gas separator 6 comprises an inner ring, an outer ring and a plurality of supporting walls 601 between the inner ring and the outer ring, the sections of the inner ring and the outer ring are both annular, one end of the inner ring is provided with a plurality of first supporting parts 607, a plurality of second supporting parts 608 are arranged inside the inner ring, one end of the inner ring, far away from the first supporting parts 607, is provided with a plurality of inner ring claw grooves 602, and one end of the outer ring, at the same side as the inner ring claw grooves 602, is provided with a plurality of outer ring claw grooves 603; the oil-gas separator is characterized by comprising a wheel disk gear 5, wherein the wall surface of the wheel disk gear 5 is divided into a plane and a wheel disk surface, and the plane is attached to the end surfaces of the inner ring and the outer ring of the oil-gas separator 6, which are provided with claw grooves, so that the oil-gas mixture 14 cannot leak from the oil-gas separator 6.
As shown in fig. 1-2, in the illustrated embodiment, any two adjacent support walls 601 of the oil-gas separator 6, the inner ring, the outer ring and the wheel with spoke 5 form an oil-gas separation chamber 604 for separating the oil-gas mixture 14 in the gear box, the inner ring claw grooves 602 and the wheel with spoke 5 form a separation chamber gas outlet 605 for facilitating the separated gas 16 to pass into the gas channel 701 in the gear shaft 7, and the outer ring claw grooves 603 and the wheel with spoke 5 form a separation chamber liquid-oil outlet 606 for facilitating the separated liquid oil 15 to enter the gear box for recycling.
As shown in fig. 1-3, in the illustrated embodiment, the rotation speed of the gear shaft 7 is at least 20000r/min, and it is proved by experiments that when the rotation speed of the gear shaft 7 is too low, the separated gas 16 in the gas channel 701 contains the liquid oil 15, and the content of the liquid oil 15 in the separated gas 16 decreases with the increase of the rotation speed of the gear shaft 7, and when the rotation speed of the gear shaft 7 reaches above 20000r/min, the liquid oil 15 in the separated gas 16 reaches the discharge standard.
Preferably, when in actual use, the end of the wheel disk gear 5 far away from the oil-gas separator 6 is abutted with the pressing plate 1, the end of the pressing plate 1 far away from the wheel disk gear 5 is abutted with the first bearing 3, the first bearing 3 is used in cooperation with the first support casing 4, the end of the first bearing 3 far away from the pressing plate 1 is abutted with the locking nut 2, and after the locking nut 2 is locked, the abutting of each part plays a role in axial limiting of the oil-gas separator 6.
Preferably, in actual use, the left end surface of the first supporting portion 607 is attached to the right end surface of the meshing gear 703 to limit the leftward axial displacement of the oil-gas separator 6 on the gear shaft 7, and the right end surfaces of the plurality of first supporting portions 607 and the left end surface of the channel inlet 702 are in the same plane, so that the separated gas 16 can enter the gas channel 701 conveniently.
Preferably, in actual use, the left end face of the second support portion 608 is flush with the right end face of the channel inlet 702, so as to facilitate the entry of the separation gas 16 into the gas channel 701 while ensuring sufficient strength.
Preferably, in actual use, the pressure in the oil-gas separation chamber 604 is 0.01-0.05MPa greater than the pressure in the gas passage 701.
Preferably, when the aircraft engine is in actual use, the outlet end of the gas channel 701 is provided with the gas path adapter 11, one end of the gas path adapter 11 is suitable for being assembled on the gear shaft 7, the other end of the gas path adapter 11 is connected with the tail of the aircraft engine, and the joint of the gas path adapter 11 and the tail of the aircraft engine is in a negative pressure state, so that the arrangement of the gas pressure in the oil-gas separator 6, the gas channel 701 and the gas path adapter 11 from high to low is realized, and the separated gas 16 can be smoothly discharged out of the aircraft engine.
Preferably, in practical use, a dynamic seal 10 is arranged at the joint of the gas circuit adapter 11 and the gear shaft 7 to prevent the separated gas 16 from leaking into the gear box, a second bearing 8 is arranged between the gas circuit adapter 11 and the meshing gear 703, the gas circuit adapter 11 and the second bearing 8 are suitable for being assembled with a second support casing 9, a plurality of sealing rubber rings 13 are arranged between the gas circuit adapter 11 and the second support casing 9 to prevent the separated gas 16 from leaking into the gear box, a cover plate 12 is arranged at one end, far away from the gear shaft 7, of the gas circuit adapter 11, the cover plate 12 is integrally nested in the gas circuit adapter 11, and the sealing rubber rings 13 are arranged between the cover plate and the gas circuit adapter 11.
As shown in fig. 4 to 6, in the illustrated embodiment, the second supporting portion 608 is provided at a central position where any two adjacent inner ring claw grooves 602 are spaced apart, the width of the second supporting portion 608 is smaller than the distance where any two adjacent inner ring claw grooves 602 are spaced apart, the number of the first supporting portions 607 and the second supporting portions 608 is the same and is at least three, and the first supporting portions 607 and the second supporting portions 608 are on the same axis.
Preferably, in practical use, the groove depth of the inner ring claw groove 602 is greater than the groove depth of the outer ring claw groove 603, and the groove width of the inner ring claw groove 602 is smaller than the groove width of the outer ring claw groove 603.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. The split type centrifugal ventilator structure of the aircraft engine is characterized by comprising a gear shaft (7), wherein one end of the gear shaft (7) is provided with a gas channel (701), the gas channel (701) is a circular counter bore, one end, far away from the end face of the gear shaft (7), of the gas channel (701) is provided with a channel inlet (702) for introducing separated gas (16) after oil-gas separation, a meshing gear (703) is arranged at the position, close to the channel inlet (702), outside the gas channel (701) of the gear shaft (7), and the gear shaft (7) is provided with a plurality of shaft shoulders and bosses for axially limiting parts in a gear box; the oil-gas separator (6) comprises an inner ring, an outer ring and a plurality of supporting walls (601) between the inner ring and the outer ring, the sections of the inner ring and the outer ring are circular, a plurality of first supporting parts (607) are arranged at one end of the inner ring, a plurality of second supporting parts (608) are arranged in the inner ring, a plurality of inner ring claw grooves (602) are arranged at one end of the inner ring, which is far away from the first supporting parts (607), and a plurality of outer ring claw grooves (603) are arranged at one end of the outer ring, which is at the same side with the inner ring claw grooves (602); the wall surface of the wheel with the wheel disc (5) is divided into a plane and a wheel disc surface, and the plane is attached to the end surfaces of one ends, provided with claw grooves, of the inner ring and the outer ring of the oil-gas separator (6);
any two adjacent supporting walls (601) of the oil-gas separator (6), the inner ring, the outer ring and the wheel with spoke plate (5) form an oil-gas separation chamber (604), the inner ring claw groove (602) and the wheel with spoke plate (5) form a separation chamber gas outlet (605), and the outer ring claw groove (603) and the wheel with spoke plate (5) form a separation chamber liquid-oil outlet (606);
the groove depth of the inner ring claw groove (602) is greater than that of the outer ring claw groove (603), and the groove width of the inner ring claw groove (602) is less than that of the outer ring claw groove (603);
the left end surfaces of the first supporting parts (607) are attached to the right end surface of the meshing gear (703), and the right end surfaces of the first supporting parts (607) and the left end surface of the channel inlet (702) are positioned on the same plane;
the left end faces of the second supporting parts (608) and the right end face of the channel inlet (702) are in the same plane;
the second supporting part (608) is arranged at the center position of the interval between any two adjacent inner ring claw grooves (602), the width of the second supporting part (608) is smaller than the interval distance between any two adjacent inner ring claw grooves (602), the number of the first supporting parts (607) and the number of the second supporting parts (608) are the same and are at least three, and the first supporting parts (607) and the second supporting parts (608) are on the same axis.
2. The split centrifugal ventilator structure of an aircraft engine according to claim 1, wherein the pressure in the oil-gas separation chamber (604) is 0.01-0.05MPa greater than the internal pressure in the gas channel (701).
3. The split type centrifugal ventilator structure of the aircraft engine according to claim 2, wherein an outlet end of the gas channel (701) is provided with a gas path adapter (11), one end of the gas path adapter (11) is suitable for being assembled on the gear shaft (7), the other end of the gas path adapter (11) is connected with the tail of the aircraft engine, and a joint of the gas path adapter (11) and the tail of the aircraft engine is in a negative pressure state.
4. The split centrifugal ventilator structure of an aircraft engine according to claim 1, characterized in that the rotational speed of the gear shaft (7) is at least 20000 r/min.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110771928.XA CN113550828B (en) | 2021-07-08 | 2021-07-08 | Split type centrifugal ventilator structure of aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110771928.XA CN113550828B (en) | 2021-07-08 | 2021-07-08 | Split type centrifugal ventilator structure of aeroengine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113550828A CN113550828A (en) | 2021-10-26 |
| CN113550828B true CN113550828B (en) | 2022-06-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110771928.XA Active CN113550828B (en) | 2021-07-08 | 2021-07-08 | Split type centrifugal ventilator structure of aeroengine |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205805734U (en) * | 2016-07-12 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of aerarium |
| CN110418879A (en) * | 2017-03-21 | 2019-11-05 | 赛峰直升机发动机公司 | Centrifugal deaerator for turbine |
| CN110917734A (en) * | 2019-12-05 | 2020-03-27 | 中国航发四川燃气涡轮研究院 | Centrifugal impeller type ventilator and gear box |
| CN111655991A (en) * | 2017-10-05 | 2020-09-11 | 联合发动机制造集团股份公司 | Accessory transmission case |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7377110B2 (en) * | 2004-03-31 | 2008-05-27 | United Technologies Corporation | Deoiler for a lubrication system |
| FR3071418B1 (en) * | 2017-09-26 | 2019-09-13 | Safran Helicopter Engines | PIECE FOR TURBOMACHINE CENTRIFUGAL DEGREYER AND PROCESS FOR MANUFACTURING THE SAME |
-
2021
- 2021-07-08 CN CN202110771928.XA patent/CN113550828B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205805734U (en) * | 2016-07-12 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of aerarium |
| CN110418879A (en) * | 2017-03-21 | 2019-11-05 | 赛峰直升机发动机公司 | Centrifugal deaerator for turbine |
| CN111655991A (en) * | 2017-10-05 | 2020-09-11 | 联合发动机制造集团股份公司 | Accessory transmission case |
| CN110917734A (en) * | 2019-12-05 | 2020-03-27 | 中国航发四川燃气涡轮研究院 | Centrifugal impeller type ventilator and gear box |
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| CN113550828A (en) | 2021-10-26 |
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