CN115123558B - Guiding device for inhibiting secondary flow in S-shaped air inlet channel - Google Patents
Guiding device for inhibiting secondary flow in S-shaped air inlet channelInfo
- Publication number
- CN115123558B CN115123558B CN202210921876.4A CN202210921876A CN115123558B CN 115123558 B CN115123558 B CN 115123558B CN 202210921876 A CN202210921876 A CN 202210921876A CN 115123558 B CN115123558 B CN 115123558B
- Authority
- CN
- China
- Prior art keywords
- air inlet
- shaped air
- flow
- inlet channel
- secondary flow
- Prior art date
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Exhaust Gas After Treatment (AREA)
Abstract
本发明公开一种抑制S形进气道内部二次流的导流装置，涉及飞行器进气道相关技术领域，包括位于S形进气道过渡段主流区域的导流片，所述导流片的布置方向与S形进气道中心线平行。本发明提供的抑制S形进气道内部二次流的导流装置，使S形进气道内部的二次流得到抑制，从而可以改善S形进气道内部的流场品质，提高发动机的性能。
The present invention discloses a flow guide device for suppressing secondary flow inside an S-shaped air inlet, which relates to the technical field related to aircraft air inlets, and comprises a flow guide vane located in the mainstream area of the transition section of the S-shaped air inlet, wherein the arrangement direction of the flow guide vane is parallel to the center line of the S-shaped air inlet. The flow guide device for suppressing secondary flow inside an S-shaped air inlet provided by the present invention suppresses the secondary flow inside the S-shaped air inlet, thereby improving the flow field quality inside the S-shaped air inlet and improving the performance of the engine.
Description
Technical Field
The invention relates to the technical field related to air inlets of aircrafts, in particular to a flow guiding device for restraining secondary flow in an S-shaped air inlet.
Background
The S-shaped air inlet is compact in structure and good in stealth performance, and fighters widely adopt the S-shaped air inlet to provide continuous air flow for the engine. The main function of the air inlet is to reduce the speed and boost the air flow, so the cross section area of the S-shaped air inlet is gradually increased along the flowing direction, and meanwhile, the center line of the S-shaped air inlet is a curve in an S shape due to the compact structure of the S-shaped air inlet. The increasing cross-sectional area in the S-shaped inlet causes the longitudinal air flow to flow split against the counter-pressure gradient, while the curved centerline causes secondary flow to exist inside the S-shaped inlet, so the S-shaped inlet internal flow is typical of flow in a curved expanding duct. The longitudinal flow separation and the transverse secondary flow inside the S-shaped air inlet channel can cause the total pressure loss and the uneven total pressure distribution of the air flow. The total pressure loss of the air inlet channel can cause the loss of the engine thrust, and researches show that about two percent of the engine thrust loss is caused by one percent of the total pressure loss, and the service life of the engine can be influenced by uneven air flow total pressure distribution on the cross section of the air inlet channel. For the above reasons, it is necessary to improve the quality of the air flow in the S-shaped inlet by effective flow control means for improving the performance of the engine.
In the past, it has been essential to improve the flow field quality inside the S-shaped inlet from the standpoint of suppressing flow separation, such as vortex generators and blow-in gas control measures. Flow control measures for improving the quality of the flow field in the S-shaped air inlet channel from the viewpoint of inhibiting the secondary flow in the air inlet channel are not presented.
Disclosure of Invention
The invention aims to provide a flow guiding device for restraining secondary flow in an S-shaped air inlet channel, so as to solve the problems in the prior art, and restrain the secondary flow in the S-shaped air inlet channel, thereby improving the quality of a flow field in the S-shaped air inlet channel and improving the performance of an engine.
In order to achieve the above object, the present invention provides the following solutions:
The invention provides a flow guiding device for inhibiting secondary flow in an S-shaped air inlet channel, which comprises flow guiding sheets positioned in a main flow area of a transition section of the S-shaped air inlet channel, wherein the arrangement direction of the flow guiding sheets is parallel to the central line of the S-shaped air inlet channel. The guide vane is designed from the aspect of restraining secondary flow, and the main flow direction of the transition section of the S-shaped air inlet channel is adjusted to meet the turning requirement of the curved wall surface, so that the quality of the flow field in the S-shaped air inlet channel is improved, and the performance of an engine is improved.
Optionally, connecting portions are symmetrically arranged at two ends of the guide vane, and the connecting portions are fixedly connected with the inner wall of the S-shaped air inlet channel.
Optionally, rectangular grooves are symmetrically formed on two sides of the guide vane, and the connecting portion is a side edge of each rectangular groove.
Optionally, the number of the guide vanes can be increased or decreased according to the curvature of the central line of the S-shaped air inlet.
Optionally, the connecting portion is welded with an inner wall of the S-shaped air inlet channel.
Compared with the prior art, the invention has the following technical effects:
The flow in the S-shaped air inlet channel is the problem that the main flow changes direction in a bend pipe which is diffused and has a longitudinal reverse pressure gradient. The main flow is subjected to the effects of counter-pressure gradients, centrifugal forces and viscous forces. According to the invention, the flow field quality in the S-shaped air inlet is improved by introducing the guide vane to adjust the main flow direction at the air inlet transition section, the secondary flow in the S-shaped air inlet is restrained, the flow separation area is reduced, and the guide vane is incompletely connected to the air inlet wall surface, so that the corner vortex at the joint of the guide vane and the S-shaped air inlet wall surface is avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a front view of a baffle of the present invention suppressing secondary flow within an S-shaped inlet;
FIG. 2 is an isometric view of a baffle of the present invention suppressing secondary flow within an S-shaped inlet;
In the figure, an S-shaped air inlet channel is 1, and a flow deflector is 2.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a flow guiding device for restraining secondary flow in an S-shaped air inlet channel, so as to solve the problems in the prior art, and restrain the secondary flow in the S-shaped air inlet channel, thereby improving the quality of a flow field in the S-shaped air inlet channel and improving the performance of an engine.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
The invention provides a flow guiding device for inhibiting secondary flow in an S-shaped air inlet channel, which comprises two flow guiding sheets 2 positioned in the S-shaped air inlet channel 1, wherein the arrangement direction of the flow guiding sheets 2 is parallel to the central line of the S-shaped air inlet channel 1 in order to determine the arrangement mode and the geometric dimension of the flow guiding sheets 2 and reduce the total pressure distortion under the condition of not increasing the total pressure loss, as shown in fig. 1 and 2. According to the invention, the guide vanes 2 are designed from the aspect of restraining secondary flow, and because the guide vanes 2 are used for adjusting the direction of main flow, the two guide vanes 2 are arranged in the main flow area of the transition section of the S-shaped air inlet channel 1, and the main flow direction of the transition section of the S-shaped air inlet channel 1 is adjusted to meet the turning requirement of the curved wall surface, so that the quality of the flow field in the S-shaped air inlet channel 1 is improved, and the performance of an engine is improved.
The two sides of the guide vane 2 are respectively cut off to form two rectangular grooves, four bulges positioned on the two sides are formed at the two ends of the guide vane 2 after the two rectangular grooves are cut off and serve as connecting parts, the connecting parts are welded on the wall surface of the S-shaped air inlet channel 1 through contact points at the tail ends of the connecting parts, the guide vane 2 is incompletely connected to the wall surface of the S-shaped air inlet channel 1, corner vortex at the joint of the guide vane 2 and the wall surface of the S-shaped air inlet channel 1 is avoided, a certain distance is reserved between the guide vane 2 and the upper wall surface and the lower wall surface of the S-shaped air inlet channel 1 for adjusting the main flow direction to a large extent, and the distance between the two guide vanes 2 is 0.4 times of the cross section diameter of the S-shaped air inlet channel 1. The number of guide vanes 2 can be increased according to the curvature of the central line of the S-shaped air inlet channel 1.
When the invention works, uniform air flow enters the S-shaped air inlet channel 1, and the guide vane 2 positioned at the transition section of the S-shaped air inlet channel 1 enables the air flow to meet the turning requirement of the curved wall surface by adjusting the main flow direction, so that secondary flow in the S-shaped air inlet channel 1 can be restrained, and meanwhile, the flow separation area in the S-shaped air inlet channel 1 can be reduced. The guide vane 2 introduced in the main flow area of the transition section of the S-shaped air inlet channel 1 has obvious effect on adjusting the main flow direction in the S-shaped air inlet channel 1, the guide vane 2 can not only effectively inhibit the non-uniformity generated by the secondary flow in the S-shaped air inlet channel 1, but also has a control effect on the flow separation of the wall surface of the S-shaped air inlet channel 1, thereby obviously improving the air flow quality on the AIP section and the performance of the engine.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "top", "bottom", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided herein to facilitate understanding of the principles and embodiments of the present invention and to provide further advantages and practical applications for those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (3)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210921876.4A CN115123558B (en) | 2022-08-02 | 2022-08-02 | Guiding device for inhibiting secondary flow in S-shaped air inlet channel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210921876.4A CN115123558B (en) | 2022-08-02 | 2022-08-02 | Guiding device for inhibiting secondary flow in S-shaped air inlet channel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115123558A CN115123558A (en) | 2022-09-30 |
| CN115123558B true CN115123558B (en) | 2025-07-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210921876.4A Active CN115123558B (en) | 2022-08-02 | 2022-08-02 | Guiding device for inhibiting secondary flow in S-shaped air inlet channel |
Country Status (1)
| Country | Link |
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| CN (1) | CN115123558B (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109026349A (en) * | 2018-09-18 | 2018-12-18 | 江苏心源航空科技有限公司 | A kind of two stroke engine scavenging air belt |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2465061Y (en) * | 2001-02-21 | 2001-12-12 | 聂法玉 | Coupling flow guiding device for residence shared exhausting duct |
| US8177498B2 (en) * | 2009-04-21 | 2012-05-15 | Ford Global Technologies, Llc | Inlet swirl control for turbochargers |
| DE102011078004A1 (en) * | 2011-06-22 | 2012-12-27 | Robert Bosch Gmbh | Sensor arrangement for determining at least one flow characteristic of a fluid medium flowing with a main flow direction |
| CN213870042U (en) * | 2020-12-17 | 2021-08-03 | 中国航发商用航空发动机有限责任公司 | Pipeline structure for reducing pressure loss of air supply pipeline of aircraft engine |
| CN117272544A (en) * | 2023-10-08 | 2023-12-22 | 北京航空航天大学 | Design method of S-shaped air inlet channel shape surface |
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2022
- 2022-08-02 CN CN202210921876.4A patent/CN115123558B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109026349A (en) * | 2018-09-18 | 2018-12-18 | 江苏心源航空科技有限公司 | A kind of two stroke engine scavenging air belt |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115123558A (en) | 2022-09-30 |
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