Two-dimensional nozzle cooling air flow control method

A binary nozzle and control method technology, applied in jet propulsion devices, machines/engines, etc., to achieve high thrust and good machine performance

Active Publication Date: 2021-06-04
AECC SHENYANG ENGINE RES INST
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Problems solved by technology

[0006] The present invention aims at the problem that the optimal matching of the whole machine performance is not realized in the design process of the cooling gas of the existing binary nozzle, and proposes a method for back-calculating the gas temperature at the outlet of the afterburner for a given flow of the cooling gas of the binary nozzle, through The cooling air of the binary nozzle with different flow rates is back-calculated for different afterburner outlet parameters, so as to calculate different thrusts, select the optimal performance solution, and realize the optimal matching of the performance of the binary nozzle and the main engine

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[0031] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below by referring to the figures are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...

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Abstract

The invention belongs to the field of aircraft engine control, and relates to a two-dimensional nozzle cooling air flow control method. The method comprises the steps that a set of cooling air flow used for cooling a two-dimensional nozzle is temporarily determined according to the air flow W<16> of an outer duct of a turbofan engine; for each cooling gas flow, according to the cooling gas temperature, the highest fuel gas temperature which can be borne by the two-dimensional nozzle is calculated; according to the highest fuel gas temperature, the afterburner outlet temperature is inversely calculated, and therefore the afterburner total pressure recovery coefficient and the afterburner fuel oil mass flow rate are determined; mixing loss and thrust coefficient of the two-dimensional nozzle are determined according to the cooling gas flow and the main runner flow, and the thrust of the whole machine is further determined; and the cooling air flow corresponding to the maximum thrust value of the whole machine is selected as a cooling air flow control strategy, and the opening degree of a cooling air flow opening is controlled. The invention provides a performance optimization method in matching design process of the whole machine and two-dimensional nozzle, and therefore the cooling gas control strategy when the thrust of the engine is maximum can be obtained.

Description

technical field [0001] The application belongs to the field of aircraft engine control, and in particular relates to a method for controlling the cooling air flow of a binary nozzle. Background technique [0002] Stealth performance is a must-have typical feature and technical index for a new generation of combat aircraft. As the main component that is visible from the rear of the engine, the stealth performance of the exhaust system is crucial to the stealth of the engine and even the rear fuselage of the aircraft. The structure of the binary nozzle Features can better realize radar stealth and infrared stealth. The binary nozzle is easy to carry out stealth design, and it is easy to integrate with the rear fuselage of the aircraft. It has been successfully applied to a foreign fighter jet. Considering the difference from the axisymmetric nozzle, the binary nozzle needs a large amount of engine air for cooling. When the engine is installed in series, the matching design of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K1/82F02K1/78
CPCF02K1/822F02K1/78
Inventor 程荣辉陈伟博薛海波张志舒张志成袁继来阮文博
Owner AECC SHENYANG ENGINE RES INST
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