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A method and system for optimal design of external and internal pressure ratio

An optimized design and connotation technology, applied in the field of optimal design method and system of external and internal pressure ratio, can solve the problems of reducing engine life and structural reliability

Active Publication Date: 2022-02-22
AECC SHENYANG ENGINE RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] c) After the engine performance declines, some performance indicators need to be achieved by increasing the engine speed, reducing engine life and structural reliability

Method used

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  • A method and system for optimal design of external and internal pressure ratio
  • A method and system for optimal design of external and internal pressure ratio

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Embodiment Construction

[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 shall fall within the scope of protection of this application. Embodiments of ...

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Abstract

The application belongs to the technical field of aero-engine control, and in particular relates to an optimization design method and system for an external and internal pressure ratio. The method includes: obtaining the total pressure recovery coefficient of the afterburner heat shield, the total pressure recovery coefficient of the afterburner in the intermediate state, and the total pressure recovery coefficient of the afterburner in the afterburner state; determining the total pressure recovery coefficient of the afterburner in the afterburner state A first ratio of the pressure recovery coefficient to the total pressure recovery coefficient of the augmented heat shield to determine a second ratio of the intermediate state afterburner total pressure recovery coefficient to the total pressure recovery coefficient of the augmented heat shield; Taking the design parameter of the external and internal pressure ratio between the first ratio and the second ratio as a constraint condition, the external and internal pressure ratio of the engine is optimally designed. The application can ensure that the mixing loss is greatly reduced when the engine is working in the intermediate state, and the performance of the engine is improved; when the engine is working in the afterburning state, a cooling air film is effectively formed to ensure the safety of the binary nozzle.

Description

technical field [0001] The application belongs to the field of aero-engine control, and in particular relates to a method and system for optimizing design of external and internal pressure ratios. 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. [0003] Considering the design difference from the axisymmetric nozzle, the binary nozzle needs a large amount of engine air to cool it. When matching the whole machine, ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/17G06F30/28G06F119/14G06F119/08G06F111/04G06F113/08
CPCG06F30/17G06F30/28G06F2119/14G06F2119/08G06F2111/04G06F2113/08
Inventor 程荣辉陈伟博张志舒薛海波阮文博张志成姜繁生
Owner AECC SHENYANG ENGINE RES INST
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