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Method for designing high-supersonic speed three-channel air inlet

A hypersonic, design method technology, applied in mechanical equipment, jet propulsion devices, gas turbine devices, etc., can solve the problems of limited available space and difficult control, and achieve the goal of reducing the windward area and external resistance and improving the performance of the combustion chamber. Effect

Active Publication Date: 2017-06-13
XIAMEN UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, since the TriJet inlet has one more rocket channel than the TBCC engine inlet, the available space is quite limited, and it is very difficult to control the structural layout and the transition between different modes. Therefore, the research on the three-channel inlet is very important The development of hypersonic vehicles has far-reaching and important significance

Method used

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  • Method for designing high-supersonic speed three-channel air inlet
  • Method for designing high-supersonic speed three-channel air inlet
  • Method for designing high-supersonic speed three-channel air inlet

Examples

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Embodiment

[0044] Embodiment: Considering the design method of the three-dimensional internal rotation hypersonic three-channel inlet, this example adopts the design Mach number Ma=4 as the incoming flow Mach number, and the design is as follows Figure 7 The working Mach number range shown is 0-4.5, and the transitional Mach number range is a turbo-based combined cycle power intake port with Ma=1.8-3. The turbine channel 38 is formed by the splitter plate 20 . It has been determined that the inlet can achieve three-dimensional shock wave contact and full flow capture under the design Mach number condition.

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Abstract

The invention discloses a method for designing a high-supersonic speed three-channel air inlet and relates to the high-supersonic speed air inlet of an aircraft. The method comprises the following steps of designing a punching channel, wherein the mach number Ma of work mach number range of the punching channel is between 3 and 4.5; designing a flow-distributing plate, wherein as air flow entering a turbine channel and the air flow entering an ejector rocket channel are allocated through the rotation of the flow-distributing plate, the flow-distributing plate should be designed by corresponding to the rocket channel, the turbine channel and the rocket channel; designing a turbine channel expanding section, wherein the mach number Ma of work mach number range of the turbine channel expanding section is between 0 and 1.8; and designing an ejector rocket channel expanding section, wherein the mach number Ma of work mach number range of the ejector rocket channel expanding section is between 1.8 and 3. The existing method for designing an inner parallel dual-channel turbine base combined circulating power air-inlet channel is improved, and the method for designing the three-dimensional inner rotation type high-supersonic speed three-channel turbine base combined circulating power air-inlet channel is provided.

Description

technical field [0001] The invention relates to a hypersonic air inlet of an aircraft, in particular to a design method of a hypersonic three-channel air inlet. Background technique [0002] In today's increasingly fierce international competition, aircraft will also usher in a technological revolution from subsonic, transonic, and supersonic to hypersonic. In view of the application value of hypersonic aircraft in national defense security and low-cost entry into space, the world's major Aerospace powers are vigorously promoting the development of hypersonic vehicles. For my country, which is currently the world's second largest economy, progress in the research of hypersonic vehicles will also become an advantage for my country in the game of great powers. an important step. Under the condition that the current single-mode engine cannot meet the large-span flight Mach number range of hypersonic vehicles, two combined-cycle power plants based on turbines and rockets have eme...

Claims

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Application Information

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IPC IPC(8): F02C7/042F02K7/16F02K7/18
CPCF02C7/042F02K7/16F02K7/18
Inventor 张旭尤延铖朱呈祥
Owner XIAMEN UNIV
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