CN104295405A - Method of lowering gas flow resistance to outer duct of aviation turbofan engine with small bypass ratio - Google Patents
Method of lowering gas flow resistance to outer duct of aviation turbofan engine with small bypass ratio Download PDFInfo
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- CN104295405A CN104295405A CN201410409516.1A CN201410409516A CN104295405A CN 104295405 A CN104295405 A CN 104295405A CN 201410409516 A CN201410409516 A CN 201410409516A CN 104295405 A CN104295405 A CN 104295405A
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- air duct
- pass
- outer duct
- gas flow
- pass air
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Abstract
The invention discloses a method of lowering gas flow resistance to an outer duct of an aviation turbofan engine with a small bypass ratio. A rectification structure is used for lowering the flow resistance. The aviation turbofan engine with the small bypass ratio comprises an intermediate case shunt ring (1), an annular channel (2), an outer duct inner wall face (3) and an outer duct outer wall face (4). The aviation turbofan engine with the small bypass ratio is characterized in that the annular channel (2) is arranged between the outer duct inner wall face (3) and the outer duct outer wall face (4), one end of the annular channel (2) is fixed to the rear end face of the intermediate case shunt ring (1), and the other end of the annular channel (2) extends into the outer duct. By means of the method, a sudden expansion channel for gas flow of the outer duct on the outlet section of the intermediate case shunt ring (1) is omitted, and therefore sudden expansion loss of the gas flow of the outer duct is reduced. Meanwhile, the cross section of the annular channel wraps a high-pressure compressor regulating mechanism and a part of core engine external pipes, so that streaming loss of the gas flow of the outer duct is reduced.
Description
Technical field
The present invention relates to little bypass ratio aviation turbofan engine by-pass air duct field of structural design, specifically provide a kind of method reducing by-pass air duct gas flow resistance.
Background technique
Little bypass ratio aviation turbofan engine by-pass air duct aeroperformance has important impact to overall performance, especially the total pressure recovery coefficient of by-pass air duct gas flow resistance is characterized, directly affect fan outlet condition, the distribution of tail pipe burner inlet pressure and temperature distribution, and then affect the overall performance parameters such as fan surge margin, the component capabilities parameter such as augmented thrust ratio, combustion efficiency, afterburning oil consumption rate of tail pipe burner and motor power, oil consumption rate, delivery temperature.Reduce by-pass air duct gas flow resistance, improve total pressure recovery coefficient, be conducive to improving motor overall performance.The mode of current reduction by-pass air duct gas flow resistance is mainly optimized design to the mechanism in by-pass air duct, pipeline profile, but is limited to by-pass air duct space size, and the resistance reducing effect that profile optimization design is brought is limited.
Summary of the invention
The object of the invention is: for little bypass ratio aviation turbofan engine by-pass air duct structural feature, invent a kind of method utilizing rectifier structure to reduce flow resistance.The method arranges annular pass on the inside and outside duct shunting ring of tradition little bypass ratio aviation turbofan engine, and the shape face of annular pass is determined according to mechanism, line arrangement in the inside and outside wall configuration of by-pass air duct and by-pass air duct.Annular pass is set, by-pass air duct air-flow sudden expansion loss can be reduced and stream loss, and then improving total pressure recovery coefficient.
Technological scheme of the present invention is: a kind of method reducing little bypass ratio aviation turbofan engine by-pass air duct gas flow resistance, comprise: Middle casing shunting ring 1, annular pass 2, by-pass air duct internal face 3, by-pass air duct outer wall 4, it is characterized in that: between little bypass ratio aviation turbofan engine by-pass air duct internal face 3 and by-pass air duct outer wall 4, annular pass 2 is set, Middle casing shunting ring 1 ear end face is fixed in one end, annular pass 2, and the other end stretches in by-pass air duct.
Shape face and Middle casing shunting ring 1 that Middle casing shunting ring 1 ear end face one end is being fixed in described annular pass 2 export tangent.
Described annular pass 2 stretch into that one end length in by-pass air duct is no more than by-pass air duct internal face 3 length 1/3.
The invention has the beneficial effects as follows: Middle casing shunting ring 1 ear end face extends by the present invention in by-pass air duct, the shape face of Middle casing shunting ring 1 ear end face one end is fixed in annular pass 2 and Middle casing shunting ring 1 exports tangent, stretch into that one end length in by-pass air duct is no more than by-pass air duct internal face 3 length 1/3, to reduce the channels expending of Middle casing shunting ring 1 outlet by-pass air duct air-flow, and then reduce by-pass air duct air-flow sudden expansion loss.Meanwhile, the shape bread of annular pass wraps up in high-pressure compressor controlling mechanism and part core engine exterior line, and then reduction by-pass air duct air-flow streams loss.
Accompanying drawing explanation
Fig. 1 is the annular channel structure schematic diagram reducing flow resistance.
Embodiment
Mode of execution 1:
In Middle casing structural design, shunting ring 1 ear end face is extended smoothly in by-pass air duct, form annular pass 2, stretch into that one end length in by-pass air duct is no more than by-pass air duct internal face 3 length 1/3, to reduce the channels expending of Middle casing shunting ring 1 outlet by-pass air duct air-flow, and then reduce by-pass air duct air-flow sudden expansion loss.Meanwhile, the shape bread of annular pass wraps up in high-pressure compressor controlling mechanism and part core engine exterior line, and then reduction by-pass air duct air-flow streams loss.
Mode of execution 2:
In the welding of Middle casing shunting ring 1 ear end face or the annular pass 2 that is spirally connected, the shape face and the Middle casing shunting ring 1 that are fixed on Middle casing shunting ring 1 ear end face one end export tangent, stretch into that one end length in by-pass air duct is no more than by-pass air duct internal face 3 length 1/3, to reduce the channels expending of Middle casing shunting ring 1 outlet by-pass air duct air-flow, and then reduce by-pass air duct air-flow sudden expansion loss.Meanwhile, the shape bread of annular pass wraps up in high-pressure compressor controlling mechanism and part core engine exterior line, and then reduction by-pass air duct air-flow streams loss.
Claims (3)
1. one kind is reduced the method for little bypass ratio aviation turbofan engine by-pass air duct gas flow resistance, comprise Middle casing shunting ring (1), annular pass (2), by-pass air duct internal face (3) and by-pass air duct outer wall (4), it is characterized in that: between little bypass ratio aviation turbofan engine by-pass air duct internal face (3) and by-pass air duct outer wall (4), annular pass (2) is set, Middle casing shunting ring (1) ear end face is fixed in annular pass (2) one end, and the other end stretches in by-pass air duct.
2. according to the method reducing little bypass ratio aviation turbofan engine by-pass air duct gas flow resistance described in claim 1, it is characterized in that: shape face and Middle casing shunting ring (1) that annular pass (2) are being fixed on Middle casing shunting ring (1) ear end face one end export tangent.
3., according to the method reducing little bypass ratio aviation turbofan engine by-pass air duct gas flow resistance described in claim 1, it is characterized in that: annular pass (2) stretch into that one end length in by-pass air duct is no more than by-pass air duct internal face (3) length 1/3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410409516.1A CN104295405A (en) | 2014-08-15 | 2014-08-15 | Method of lowering gas flow resistance to outer duct of aviation turbofan engine with small bypass ratio |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410409516.1A CN104295405A (en) | 2014-08-15 | 2014-08-15 | Method of lowering gas flow resistance to outer duct of aviation turbofan engine with small bypass ratio |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104295405A true CN104295405A (en) | 2015-01-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410409516.1A Pending CN104295405A (en) | 2014-08-15 | 2014-08-15 | Method of lowering gas flow resistance to outer duct of aviation turbofan engine with small bypass ratio |
Country Status (1)
| Country | Link |
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| CN (1) | CN104295405A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107524522A (en) * | 2016-06-20 | 2017-12-29 | 中国航发商用航空发动机有限责任公司 | Receive expansion formula fanjet flow splitter |
| CN113738532A (en) * | 2021-11-04 | 2021-12-03 | 中国航发沈阳发动机研究所 | Aero-engine with overlapped ducts |
| CN114278617A (en) * | 2021-11-30 | 2022-04-05 | 清华大学 | Compression device and runner system thereof |
-
2014
- 2014-08-15 CN CN201410409516.1A patent/CN104295405A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107524522A (en) * | 2016-06-20 | 2017-12-29 | 中国航发商用航空发动机有限责任公司 | Receive expansion formula fanjet flow splitter |
| CN107524522B (en) * | 2016-06-20 | 2021-06-11 | 中国航发商用航空发动机有限责任公司 | Collecting and expanding type turbofan engine flow distribution ring |
| CN113738532A (en) * | 2021-11-04 | 2021-12-03 | 中国航发沈阳发动机研究所 | Aero-engine with overlapped ducts |
| CN113738532B (en) * | 2021-11-04 | 2022-02-18 | 中国航发沈阳发动机研究所 | Aero-engine with overlapped ducts |
| CN114278617A (en) * | 2021-11-30 | 2022-04-05 | 清华大学 | Compression device and runner system thereof |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150121 |
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| RJ01 | Rejection of invention patent application after publication |