CN110374747A - A kind of aircraft engine bleed air line with self-compensating function - Google Patents
A kind of aircraft engine bleed air line with self-compensating function Download PDFInfo
- Publication number
- CN110374747A CN110374747A CN201910677497.3A CN201910677497A CN110374747A CN 110374747 A CN110374747 A CN 110374747A CN 201910677497 A CN201910677497 A CN 201910677497A CN 110374747 A CN110374747 A CN 110374747A
- Authority
- CN
- China
- Prior art keywords
- air line
- casing
- engine bleed
- bleed air
- engine
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Joints Allowing Movement (AREA)
Abstract
The application belongs to aero-engine piping system design field, in particular to a kind of aircraft engine bleed air line with self-compensating function.It include: engine bleed pipeline (3) and blade profile radome fairing (6).Bleed air line (1) connects on the outside of one end of engine bleed pipeline (3) and engine, the other end is connect with intension casing (8), outer culvert interconnecting piece is provided on the engine bleed pipeline (3), outer culvert interconnecting piece cooperation sealing ring (4) connect with outer culvert casing (5)；Blade profile radome fairing (6) is set on the engine bleed pipeline (3), and described blade profile radome fairing (6) one end is connect with the outer culvert casing (5), and the other end is connect with the intension casing (8).The application is capable of providing preferable deformation-compensated ability and sealability using structure compensation design is slidingly sealed, and can substantially lower the outer pressure loss for containing air-flow by blade profile radome fairing, improve the efficiency and thrust of medium Bypass Ratio Turbofan Engine.
Description
Technical field
The application belongs to aero-engine piping system design field, in particular to a kind of aircraft with self-compensating function
Engine bleed pipeline.
Background technique
Exterior line is the important component of aero-engine.Exterior line is used for fuel oil, lubricating oil, air, oil gas
Deng each host part and system for being transported to host from each engine accessory power rating, guarantee the normal operation of engine.
In the prior art, the bleed structure in small Bypass Ratio Turbofan Engine can be realized from aero-engine intension to hair
The purpose of the outer bleed of motivation, and the design by obturaging connector spherical, while solving the problems, such as sealing and structure compensation.But
The structure is not suitable for medium bypass ratio engine, and main problem is as follows: for small bypass ratio engine, inside and outside culvert flow channel space
Apart from small, when a small amount of deformation occurs in inside and outside culvert casing, the deformation-compensated ability that spherical structure provides is to meet to want
It asks；But for medium bypass ratio engine, inside and outside culvert flow channel space is apart from larger, when moderate finite deformation occurs in inside and outside culvert casing
When amount, the structure compensation amount is insufficient, and in addition when deforming larger, the function of obturaging of globe joint also will failure.For small duct
For engine, the outer air mass flow contained in circulation passage is less with respect to for total flow, while pipeline diameter is smaller, causes
Outer culvert flow losses it is limited；But for medium bypass ratio engine, flow is very big in outer culvert circulation passage, flies simultaneously
Power traction air pipe is relatively large in diameter, and causes biggish outer culvert flow losses, and then have larger impact to complete machine.Small bypass ratio is sent out
For motivation, the pipeline diameter between aircraft engine is smaller, and since pipeline diameter is small, the rigidity of pipeline is weaker, can rely on
The deformation-compensated intension casing of itself and the outer deformation for containing casing；But for medium bypass ratio engine, aircraft engine
Pipeline diameter between machine is larger, and the pipeline rigidity of major diameter is stronger, and the simple deformation for relying on pipeline itself, is to be unable to satisfy change
The requirement of shape compensation.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
The purpose of the application there is provided a kind of aircraft engine bleed air line with self-compensating function, it is existing to solve
At least one problem existing for technology.
The technical solution of the application is:
A kind of aircraft engine bleed air line with self-compensating function, comprising:
Engine bleed pipeline, bleed air line connection, another on the outside of one end of the engine bleed pipeline and engine
End is connect with intension casing, and outer culvert interconnecting piece, the outer culvert interconnecting piece cooperation sealing are provided on the engine bleed pipeline
Circle is connect with outer culvert casing；
Blade profile radome fairing, the blade profile radome fairing are set on the engine bleed pipeline, the blade profile radome fairing one
End is connect with the outer culvert casing, and the other end is connect with the intension casing.
It optionally, further include bellows, the bellows is arranged between the outer culvert casing and the intension casing
On the engine bleed pipeline.
Optionally, engine bleed pipeline passes through flanged joint with bleed air line on the outside of engine.
Optionally, engine bleed pipeline is connect with bleed air line on the outside of engine by snap ring.
Optionally, the engine bleed pipeline is provided with flange installation side, and the intension casing is provided with intension installation
Seat, the engine bleed pipeline are connect by bolt with the intension casing.
Optionally, the outer culvert interconnecting piece and the engine bleed pipeline are integrally formed.
Optionally, the outer culvert interconnecting piece and the engine bleed pipeline pass through welded connecting.
Optionally, the outer interconnecting piece of containing has the groove circumferentially opened up, and the sealing ring is arranged in the groove,
The outer culvert casing is provided with sealing surface, by the way that the sealing ring to be pressed on the outer sealing surface for containing casing, realizes institute
Engine bleed pipeline is stated to connect with the outer culvert casing.
Optionally, the blade profile radome fairing is bolted with the outer culvert casing.
Optionally, the blade profile radome fairing and the intension casing pass through welded connecting.
At least there are following advantageous effects in invention:
The aircraft engine bleed air line with self-compensating function of the application is designed using structure compensation is slidingly sealed,
It is capable of providing preferable deformation-compensated ability and sealability, outer culvert air-flow can substantially be lowered by blade profile dome structure
The pressure loss improves the efficiency and thrust of medium Bypass Ratio Turbofan Engine.
Detailed description of the invention
Fig. 1 is the aircraft engine bleed air line schematic diagram with self-compensating function of one embodiment of the application；
Fig. 2 is the A-A view of Fig. 1；
Fig. 3 is the outer culvert connection of the aircraft engine bleed air line with self-compensating function of one embodiment of the application
Portion's schematic diagram.
Wherein:
Bleed air line on the outside of 1- engine；2- snap ring；3- engine bleed pipeline；4- sealing ring；Contain casing outside 5-；6- leaf
Type radome fairing；7- bellows；8- intension casing.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 to Fig. 3 the application is described in further details with reference to the accompanying drawing.
The aircraft engine bleed air line with self-compensating function that this application provides a kind of, comprising: engine bleed pipe
Road 3 and blade profile radome fairing 6.
Specifically, bleed air line 1 connects on the outside of one end of engine bleed pipeline 3 and engine, the other end and intension machine
Casket 8 connects, and outer culvert interconnecting piece is provided on engine bleed pipeline 3, and outer culvert interconnecting piece cooperation sealing ring 4 and outer culvert casing 5 connect
It connects；Blade profile radome fairing 6 is set on engine bleed pipeline 3, and 6 one end of blade profile radome fairing is connect with outer culvert casing 5, the other end with
Intension casing 8 connects.
The aircraft engine bleed air line with self-compensating function of the application, further includes bellows 7, and bellows 7 is arranged
On the engine bleed pipeline 3 for the outer culvert runner being located between outer culvert casing 5 and intension casing 8.Pass through the ripple of bellows 7
Pipe structure can compensate for intension casing 8 and the outer deformation problem contained between casing 5, and bellows structure has bigger knot
Structure compensation ability, so that the adaptability and reliability of structure greatly improve.
In the embodiment of the application, engine bleed pipeline 3 can pass through with bleed air line 1 on the outside of engine
Flanged joint.In the another embodiment of the application, bleed air line 1 may be used also on the outside of engine bleed pipeline 3 and engine
To be connected by quick-release snap ring 2.
The aircraft engine bleed air line with self-compensating function of the application is provided with method on engine bleed pipeline 3
Orchid installation side, intension casing 8 are provided with intension mounting base, and engine bleed pipeline 3 is connect by bolt with intension casing 8.
In the embodiment of the application, outer culvert interconnecting piece, outer culvert are provided on the tube wall of engine bleed pipeline 3
One end of interconnecting piece and engine bleed pipeline 3 can be integrated molding, can also pass through welded connecting.In the present embodiment, outside
The other end for containing interconnecting piece has the groove circumferentially opened up, and sealing ring 4 is arranged in a groove, and outer culvert casing 5 is provided with sealing
Realize that engine bleed pipeline 3 is connect with outer culvert casing 5 by the way that sealing ring 4 to be pressed on the outer sealing surface for containing casing 5 in face.
It is this to be slidingly sealed structure, it can be realized the sealing for externally containing air-flow, also can compensate between outer culvert casing 5 and intension casing 8
Radial deformation the problem of.
In the embodiment of the application, 6 one end of blade profile radome fairing is bolted with outer culvert casing 5, another
End passes through welded connecting with intension casing 8.Major diameter pipeline can be significantly reduced by 6 structure of blade profile radome fairing externally to contain
The disturbance of air-flow reduces the outer performance loss for containing air-flow, while also reducing direct impact of the outer culvert air-flow to pipeline, improves
Reliability of structure and safety.
The aircraft engine bleed air line with self-compensating function of the application, using being slidingly sealed structure and bellows two
Locate structure compensation design, is capable of providing preferable deformation-compensated ability and sealability, it can be big by blade profile dome structure
Width lowers the outer pressure loss for containing air-flow, improves the efficiency and thrust of medium Bypass Ratio Turbofan Engine, meets medium bypass ratio
The use demand of fanjet.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of aircraft engine bleed air line with self-compensating function characterized by comprising
Engine bleed pipeline (3), bleed air line (1) connection on the outside of one end of the engine bleed pipeline (3) and engine,
The other end is connect with intension casing (8), and outer culvert interconnecting piece, the outer culvert connection are provided on the engine bleed pipeline (3)
Portion's cooperation sealing ring (4) is connect with outer culvert casing (5)；
Blade profile radome fairing (6), the blade profile radome fairing (6) are set on the engine bleed pipeline (3), the blade profile rectification
Cover (6) one end is connect with the outer culvert casing (5), and the other end is connect with the intension casing (8).
2. the aircraft engine bleed air line according to claim 1 with self-compensating function, which is characterized in that further include
Bellows (7), bellows (7) setting is in the outer engine contained between casing (5) and the intension casing (8)
In bleed air line (3).
3. the aircraft engine bleed air line according to claim 1 with self-compensating function, which is characterized in that engine
Bleed air line (1) passes through flanged joint on the outside of bleed air line (3) and engine.
4. the aircraft engine bleed air line according to claim 1 with self-compensating function, which is characterized in that engine
Bleed air line (3) is connect with bleed air line on the outside of engine (1) by snap ring (2).
5. the aircraft engine bleed air line according to claim 1 with self-compensating function, which is characterized in that the hair
Motivation bleed air line (3) is provided with flange installation side, and the intension casing (8) is provided with intension mounting base, described to start power traction
Air pipe (3) is connect by bolt with the intension casing (8).
6. the aircraft engine bleed air line according to claim 1 with self-compensating function, which is characterized in that described outer
Contain interconnecting piece and the engine bleed pipeline (3) is integrally formed.
7. the aircraft engine bleed air line according to claim 1 with self-compensating function, which is characterized in that described outer
Contain interconnecting piece and the engine bleed pipeline (3) passes through welded connecting.
8. the aircraft engine bleed air line according to claim 1 with self-compensating function, which is characterized in that described outer
Containing interconnecting piece has the groove circumferentially opened up, and the sealing ring (4) is arranged in the groove, and the outer culvert casing (5) sets
It is equipped with sealing surface, by the way that the sealing ring (4) to be pressed on the outer sealing surface for containing casing (5), realizes the engine
Bleed air line (3) is connect with the outer culvert casing (5).
9. the aircraft engine bleed air line according to claim 1 with self-compensating function, which is characterized in that the leaf
Type radome fairing (6) is bolted with the outer culvert casing (5).
10. the aircraft engine bleed air line according to claim 1 with self-compensating function, which is characterized in that described
Blade profile radome fairing (6) and the intension casing (8) pass through welded connecting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910677497.3A CN110374747A (en) | 2019-07-25 | 2019-07-25 | A kind of aircraft engine bleed air line with self-compensating function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910677497.3A CN110374747A (en) | 2019-07-25 | 2019-07-25 | A kind of aircraft engine bleed air line with self-compensating function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110374747A true CN110374747A (en) | 2019-10-25 |
Family
ID=68256106
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910677497.3A Pending CN110374747A (en) | 2019-07-25 | 2019-07-25 | A kind of aircraft engine bleed air line with self-compensating function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110374747A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113123866A (en) * | 2020-01-15 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Culvert bleed air system and turbofan engine |
| CN113864057A (en) * | 2021-10-27 | 2021-12-31 | 中国航发沈阳发动机研究所 | Air-entraining structure in double-layer casing |
| CN114017387A (en) * | 2021-11-10 | 2022-02-08 | 中国航发沈阳发动机研究所 | Aeroengine compressor bleed structure |
| CN114215789A (en) * | 2021-12-06 | 2022-03-22 | 中国航发沈阳发动机研究所 | Air entraining structure of double-layer casing |
| CN114263636A (en) * | 2021-12-06 | 2022-04-01 | 中国航发沈阳发动机研究所 | Air-entraining structure in double-layer casing |
| CN114776925A (en) * | 2022-04-16 | 2022-07-22 | 中国航发沈阳发动机研究所 | Turbofan engine turbine cooling air-entraining pipeline with displacement compensation capability |
| CN118088792A (en) * | 2024-04-22 | 2024-05-28 | 成都中科翼能科技有限公司 | Bleed air assembly of double-layer runner casing of gas turbine |
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| US20150233298A1 (en) * | 2012-09-28 | 2015-08-20 | United Technologies Corporation | Reduction in jet flap interaction noise with geared turbine engine |
| CN109927916A (en) * | 2017-12-18 | 2019-06-25 | 郭俊鸽 | A kind of military aircraft composite material radome fairing |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113123866A (en) * | 2020-01-15 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Culvert bleed air system and turbofan engine |
| CN113123866B (en) * | 2020-01-15 | 2022-10-11 | 中国航发商用航空发动机有限责任公司 | Culvert bleed air system and turbofan engine |
| CN113864057A (en) * | 2021-10-27 | 2021-12-31 | 中国航发沈阳发动机研究所 | Air-entraining structure in double-layer casing |
| CN114017387A (en) * | 2021-11-10 | 2022-02-08 | 中国航发沈阳发动机研究所 | Aeroengine compressor bleed structure |
| CN114017387B (en) * | 2021-11-10 | 2023-07-07 | 中国航发沈阳发动机研究所 | Aeroengine compressor bleed air structure |
| CN114215789A (en) * | 2021-12-06 | 2022-03-22 | 中国航发沈阳发动机研究所 | Air entraining structure of double-layer casing |
| CN114263636A (en) * | 2021-12-06 | 2022-04-01 | 中国航发沈阳发动机研究所 | Air-entraining structure in double-layer casing |
| CN114263636B (en) * | 2021-12-06 | 2024-03-19 | 中国航发沈阳发动机研究所 | Double-deck quick-witted casket internal air entraining structure |
| CN114776925A (en) * | 2022-04-16 | 2022-07-22 | 中国航发沈阳发动机研究所 | Turbofan engine turbine cooling air-entraining pipeline with displacement compensation capability |
| CN118088792A (en) * | 2024-04-22 | 2024-05-28 | 成都中科翼能科技有限公司 | Bleed air assembly of double-layer runner casing of gas turbine |
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Application publication date: 20191025 |
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| RJ01 | Rejection of invention patent application after publication |