CN204250376U - A kind of Submerged Inlet structure of aircraft - Google Patents
A kind of Submerged Inlet structure of aircraft Download PDFInfo
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- CN204250376U CN204250376U CN201420707442.5U CN201420707442U CN204250376U CN 204250376 U CN204250376 U CN 204250376U CN 201420707442 U CN201420707442 U CN 201420707442U CN 204250376 U CN204250376 U CN 204250376U
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Abstract
本实用新型涉及飞行器进气道领域，涉及一种飞行器的埋入式进气道结构。包括埋入式进气道和飞行器，埋入式进气道分进气口、出气口以及进气道，进气口安装在飞行器的表面，出气口与飞行器的发动机的进气口连通，在进气道内开有若干喷气孔，从发动机的风扇或压气机后引出一根引气导管与各个喷气孔连通。喷气孔布置在进气道内的边界层气流潜在分离区的上游即前唇口导流面附近。喷气孔轴线与前唇口导流面呈倾斜角度。本实用新型的有益效果在于：结构简单，便于实施，显著提高埋入式进气道的总压恢复系数，有效降低畸变指数。
The utility model relates to the field of air intake ducts of aircraft, in particular to an embedded air intake duct structure of an aircraft. Including the embedded air inlet and the aircraft, the embedded air inlet is divided into air inlet, air outlet and air inlet, the air inlet is installed on the surface of the aircraft, and the air outlet communicates with the air inlet of the engine of the aircraft. There are some jet holes in the air inlet, and an air-inducing conduit is drawn from behind the fan or compressor of the engine to communicate with each jet hole. The air injection holes are arranged upstream of the potential separation zone of the boundary layer airflow in the intake duct, that is, near the guide surface of the front lip. The axis of the jet hole is at an oblique angle to the guide surface of the front lip. The beneficial effect of the utility model lies in that the structure is simple and easy to implement, the total pressure recovery coefficient of the buried air inlet can be significantly improved, and the distortion index can be effectively reduced.
Description
技术领域 technical field
本实用新型涉及飞行器进气道领域，具体的说是涉及一种飞行器的埋入式进气道结构。 The utility model relates to the field of air intake ducts of aircraft, in particular to an embedded air intake duct structure of an aircraft.
背景技术 Background technique
埋入式进气道是将进口和飞行器融合为一体，没有任何突起部分的特殊进气道。埋入式进气道不仅由于迎风面积小能够有效降低飞行器的迎风阻力和雷达散射面积，而且其与弹体的融合使得弹体的尺寸减小，有利于安装、运输和多平台发射。因此，埋入式进气道正在受到越来越广泛的关注和应用。但是，埋入式进气道的进口完全置于弹体附面层的低能流中，不能像S形进气道那样利用来流冲压，仅依靠前唇口处的压力梯度和侧棱处的卷吸涡进气。当卷吸涡强度太小时，埋入式进气道的进气效果差；而当卷吸涡过强时进气道出口的畸变又会很大。 The buried air inlet is a special air inlet that integrates the inlet and the aircraft without any protruding parts. The buried air intake can not only effectively reduce the wind resistance and radar scattering area of the aircraft due to the small windward area, but also reduce the size of the missile body by integrating it with the missile body, which is conducive to installation, transportation and multi-platform launch. Therefore, the buried air intake is receiving more and more attention and application. However, the inlet of the buried air intake is completely placed in the low-energy flow of the projectile boundary layer, and cannot be stamped by the incoming flow like the S-shaped air intake, and only relies on the pressure gradient at the front lip and the pressure gradient at the side edges. Suction vortex air intake. When the entrainment vortex strength is too small, the intake effect of the buried air inlet is poor; and when the entrainment vortex is too strong, the distortion of the inlet outlet will be great.
发明内容 Contents of the invention
本实用新型的目的在于解决上述问题，提供一种飞行器的埋入式进气道结构。 The purpose of the utility model is to solve the above problems, and provide a buried air intake structure of an aircraft.
为了实现本实用新型的目的，本实用新型采用的技术方案为： In order to realize the purpose of the utility model, the technical scheme that the utility model adopts is:
一种飞行器的埋入式进气道结构，包括埋入式进气道和飞行器，埋入式进气道分进气口、出气口以及进气道，进气口安装在飞行器的表面，出气口与飞行器的发动机的进气口连通，在进气道内开有若干喷气孔，从发动机的风扇或压气机后引出一根引气导管与各个喷气孔连通。 A buried air intake structure for an aircraft, comprising a buried air intake and an aircraft, the buried air intake is divided into an air inlet, an air outlet and an air inlet, the air inlet is installed on the surface of the aircraft, and the outlet The air port is communicated with the air intake of the engine of the aircraft, has some jet holes in the air inlet, and draws an air-inducing conduit from behind the fan or compressor of the engine to communicate with each jet hole.
喷气孔布置在进气道内的边界层气流潜在分离区的上游即前唇口导流面附近。 The air injection holes are arranged upstream of the potential separation zone of the boundary layer airflow in the intake duct, that is, near the guide surface of the front lip.
喷气孔轴线与前唇口导流面呈倾斜角度。 The axis of the jet hole is at an oblique angle to the guide surface of the front lip.
本实用新型的有益效果在于：结构简单，便于实施，显著提高埋入式进气道的总压恢复系数，有效降低畸变指数。 The beneficial effect of the utility model lies in that the structure is simple and easy to implement, the total pressure recovery coefficient of the buried air inlet can be significantly improved, and the distortion index can be effectively reduced.
附图说明 Description of drawings
图1为本实用新型结构示意图， Fig. 1 is a structural representation of the utility model,
图2为本实用新型的埋入式进气道结构示意图。 Fig. 2 is a schematic diagram of the structure of the buried air inlet of the present invention.
具体实施方式 Detailed ways
下面结合附图和实施例对本实用新型进一步说明： Below in conjunction with accompanying drawing and embodiment the utility model is further described:
实施例： 参见图1，图2。 Embodiment: See Fig. 1, Fig. 2.
一种飞行器的埋入式进气道结构，包括埋入式进气道2和飞行器1，埋入式进气道分进气口201、出气口202以及进气道203，进气口201安装在飞行器1的表面，出气口201与飞行器1的发动机3的进气口连通，在进气道203内开有若干喷气孔204，从发动机3的风扇或压气机后引出一根引气导管4与各个喷气孔204连通。 An embedded air intake structure of an aircraft, comprising an embedded air intake 2 and an aircraft 1, the embedded air intake is divided into an air inlet 201, an air outlet 202 and an air inlet 203, and the air inlet 201 is installed On the surface of the aircraft 1, the air outlet 201 is communicated with the air intake of the engine 3 of the aircraft 1, and some air injection holes 204 are arranged in the air inlet 203, and an air-introduction duct 4 is drawn from the fan of the engine 3 or the compressor. Each gas injection hole 204 is connected.
喷气孔204布置在进气道203内的边界层气流潜在分离区的上游即前唇口导流面附近。 The air injection hole 204 is arranged upstream of the potential separation zone of the boundary layer air flow in the air intake duct 203 , that is, near the guide surface of the front lip.
喷气孔204轴线与前唇口导流面呈倾斜角度。 The axis of the jet hole 204 forms an oblique angle with the guide surface of the front lip.
本实用新型原理：引气导管4将从发动机3的风扇或压气机而来的高压气流导入埋入式进气道2。由于引气导管4内气流与进气道边界层气流之间的压差，气流将以特定的角度从进气道喷气孔204内喷出，产生的漩涡将加强边界层气流和主流的掺混，从而抑制边界层的分离，减小流动损失。形成的漩涡起到了相当于叶片式涡流发生器的作用，可以显著改善埋入式进气道2的性能。所以，通过引气导管4从发动机3风扇或压气机后引气是实现基于喷气式涡流发生器的埋入式进气道提高出口总压恢复系数和降低畸变指数的有力手段。 Principle of the utility model: the air-inducing conduit 4 guides the high-pressure airflow coming from the fan of the engine 3 or the air compressor into the embedded air intake 2 . Due to the pressure difference between the airflow in the bleed duct 4 and the boundary layer airflow of the intake port, the airflow will be ejected from the air inlet nozzle 204 at a specific angle, and the vortex generated will strengthen the mixing of the boundary layer airflow and the main flow , thereby inhibiting the separation of the boundary layer and reducing flow loss. The formed vortex acts as a vane-type vortex generator, which can significantly improve the performance of the buried air intake 2 . Therefore, bleed air from the fan or compressor of the engine 3 through the bleed air duct 4 is a powerful means to realize the embedded inlet port based on the jet vortex generator to improve the recovery coefficient of the total outlet pressure and reduce the distortion index.
本实用新型的实施例公布的是较佳的实施例之一也，但并不局限于此，本领域的普通技术人员，极易根据上述实施例，领会本实用新型的精神，并做出不同的引申和变化，但只要不脱离本实用新型的精神，都在本实用新型的保护范围内。 The disclosed embodiment of the utility model is one of the preferred embodiments, but it is not limited thereto. Those of ordinary skill in the art can easily understand the spirit of the utility model according to the above-mentioned embodiments, and make different Extensions and changes, but as long as they do not depart from the spirit of the utility model, they are all within the protection scope of the utility model.
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Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420707442.5U CN204250376U (en) | 2014-11-24 | 2014-11-24 | A kind of Submerged Inlet structure of aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420707442.5U CN204250376U (en) | 2014-11-24 | 2014-11-24 | A kind of Submerged Inlet structure of aircraft |
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| CN204250376U true CN204250376U (en) | 2015-04-08 |
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| CN201420707442.5U Expired - Lifetime CN204250376U (en) | 2014-11-24 | 2014-11-24 | A kind of Submerged Inlet structure of aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443402A (en) * | 2014-11-24 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Embedded type air inlet passage structure of aircraft |
| CN107719645A (en) * | 2016-08-11 | 2018-02-23 | 通用电气公司 | Intake assembly for aircraft aft-fan |
-
2014
- 2014-11-24 CN CN201420707442.5U patent/CN204250376U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443402A (en) * | 2014-11-24 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Embedded type air inlet passage structure of aircraft |
| CN107719645A (en) * | 2016-08-11 | 2018-02-23 | 通用电气公司 | Intake assembly for aircraft aft-fan |
| CN107719645B (en) * | 2016-08-11 | 2023-04-07 | 通用电气公司 | Inlet assembly for an aircraft rear fan |
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Granted publication date: 20150408 |