Rapid design method for hypersonic variable cross-section revolving inlet with full flow capture

An internally rotating air inlet, hypersonic technology, applied in computing, mechanical equipment, jet propulsion, etc., can solve the problems of complex implementation process and long design cycle, and achieve a simplified design process, shortened design cycle, and easy software. The effect of automated design

Active Publication Date: 2019-09-06
广东空天科技研究院
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0007] These design methods can realize the controllable shape of the inlet and outlet of the inlet at the same time, and can also ensure that the leading edge of the inlet is completely wave-ridden to achieve full flow capture, but there are also problems such as very complicated implementation process and long design cycle.

Method used

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  • Rapid design method for hypersonic variable cross-section revolving inlet with full flow capture
  • Rapid design method for hypersonic variable cross-section revolving inlet with full flow capture
  • Rapid design method for hypersonic variable cross-section revolving inlet with full flow capture

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Embodiment 1

[0053] refer to Figure 1 to Figure 6 , the inlet of the inner-turning inlet is selected as a rectangle, and the outlet is a circle. The detailed steps are described:

[0054] Such as figure 1 As shown in , it is a schematic diagram of the processing method of a given reference flow field, which is divided into a dependent region and a weighted transition region by characteristic lines.

[0055] For the reference flow field and incoming flow parameters of the known compression profile and center body radius, the characteristic line method is used to calculate the flow conditions of the reference flow field, and the leading edge shock wave, tail shock wave, also called reflected shock wave, and forward shock wave are obtained. The characteristic line of the intersection point of the marginal shock and the central body. The characteristic line OC divides the reference flow field into two regions, the dependent region and the weighted transition region.

[0056] Such as figu...

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PUM

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Abstract

The invention provides a hypersonic-speed inward rotation type air feeding channel quick design method which can achieve full flow capture, meanwhile can meet the free design requirements for the shapes of an inlet and an outlet and moreover can keep certain datum flow field performance, the shapes of the inlet and the outlet of an air feeding channel can be freely manufactured, the problem that amathematical function weighting transition method is used, so that a leading edge shock wave shape is changed, and the air feeding channel cannot completely ride a wave is solved, and full flow capture is achieved. According to the design method, the design process is easy and quick, software automatic design is easy to achieve, the design period is greatly shortened, and a foundation is providedfor carrying out further research work based on a lot of air feeding channel embodiments.

Description

technical field [0001] The invention relates to the design field of aircraft engine inlets, in particular to a rapid design method for a hypersonic variable cross-section inwardly rotating inlet used for scramjet full-flow capture. Background technique [0002] The hypersonic inlet is an important part of the scramjet engine, which undertakes the task of capturing the incoming flow for the engine, decelerating and supercharging the engine, and its design performance directly affects the working efficiency of the engine. Parameters such as incoming flow capture rate, boost ratio, and total pressure recovery coefficient are important indicators for evaluating the performance of a hypersonic inlet. [0003] Since the 1950s, with the research on scramjet and supersonic combustion, countries have made significant progress in hypersonic inlet design and performance analysis, and a series of hypersonic inlets have been born. Such as binary inlets, side pressure inlets, axisymmetri...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/042G06F17/50
CPCF02C7/042G06F30/17
Inventor 肖鸿文岳连捷肖雅彬张启帆张新宇
Owner 广东空天科技研究院
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