Divergent dual-throat nozzle with gas-injection divergent section
An expansion section and expansion type technology, applied in the directions of jet propulsion, aircraft parts, aircraft control, etc., to achieve the effect of reducing cost, improving nozzle performance and simple structure
Inactive Publication Date: 2012-05-30
BEIHANG UNIV
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Problems solved by technology
[0008] The purpose of the present invention is to solve the start-up problem of the expansion-type double-throat nozzle, improve the performance of the nozzle, and propose an expansion-section air-injection type expansion-type double-throat nozzle
Method used
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Embodiment Construction
[0025] The present invention will be further described in detail below with reference to the accompanying drawings.
[0026] The present invention is an expansion section gas injection type expansion double-throat nozzle, such as figure 1 As shown, the inner cavity of the nozzle housing 1 is sequentially composed of a straight section 101, a first constricted section 102, an expanded section 103, and a second constricted section 104 from the air inlet end to the air outlet end, wherein the throat of the second constricted section 104 is The size is greater than the throat size of the first constricted section 102 . A first gas injection slit 3 is opened at the throat of the first contraction section 102 , and a second gas injection slit 4 is opened on the expansion section, so that the expansion section 103 can be injected with gas. Gas injection in the expansion section 103 can generate an oblique shock wave system, and a large separation area is formed before and after the ...
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The invention discloses a divergent dual-throat nozzle with a gas-injection divergent section. The cavity in the nozzle casing is successively composed of a flat section, a first convergent section, a divergent section and a second convergent section from the gas inlet end to the gas outlet end, wherein the size of the throat at the second convergent section is greater than that at the first convergent section. The throat at the first convergent section is provided with a first gas injection seam, and the divergent section is provided with a second gas injection seam, thereby realizing gas injection at the divergent section. The gas injection at the divergent section can generate an oblique shock-wave system, and a large separation zone is respectively formed before and behind the gas injection port, thereby changing the shape of the primary flow channel of the divergent dual-throat nozzle, reducing the shock wave loss and solving the problems in starting the nozzle. In addition, the invention obviously enhances the nozzle performance, simplifies the structure, reduces the weight and lowers the cost.
Description
technical field [0001] The invention relates to an aero-engine tail nozzle fluid control thrust vectoring technology, and specifically designs an expansion section gas injection type expansion double-throat nozzle. Background technique [0002] Thrust vectoring technology can bring fighters such as improved maneuverability and agility, reduced tail area, reduced aircraft drag and weight, improved aircraft stealth performance, safety and survivability, shortened aircraft takeoff and landing distances, and significantly improved air combat. It has many benefits such as efficiency, adapting to people's requirements for fighter jets in the future air combat environment, and has become one of the necessary technologies for fourth-generation fighter jets. [0003] For thrust vectoring technology, thrust vectoring nozzle technology is its foundation, and developing advanced and applicable thrust vectoring nozzle technology has become a necessary condition for the development of air...
Claims
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IPC IPC(8): F02K1/06F02K1/38B64C15/00
Inventor 额日其太王强苏沛然蒋登宇
Owner BEIHANG UNIV