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Runner structure of ramjet engine, ramjet engine and aircraft

A ramjet and flow channel technology, applied in the field of ramjet, can solve the problems of high complexity of geometric structure and difficult sealing technology, etc.

Active Publication Date: 2022-04-05
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The usual mechanical adjustment structure consists of hydraulic connecting rods, adjustable panels, control systems, etc. The overall variable geometric structure is highly complex and the sealing technology is difficult

Method used

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  • Runner structure of ramjet engine, ramjet engine and aircraft
  • Runner structure of ramjet engine, ramjet engine and aircraft
  • Runner structure of ramjet engine, ramjet engine and aircraft

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Embodiment Construction

[0020] In order to make the above objects, features and advantages of the present invention more comprehensible, specific implementations of the present invention will be described in detail below in conjunction with the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. However, the present invention can be implemented in many other ways different from those described here, and those skilled in the art can make similar improvements without departing from the connotation of the present invention, so the present invention is not limited by the specific embodiments disclosed below.

[0021] The terms "first" and "second" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of indicated technical features. Thus, the features defined as "first" and "second" may explicitly or ...

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PUM

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Abstract

The invention relates to a flow passage structure of a ramjet engine, a ramjet engine and an aircraft. The flow channel structure includes the air inlet, the combustion chamber and the nozzle section. The two ends of the combustion chamber are respectively connected with the air inlet and the nozzle section; the combustion chamber includes a deformable section with a control section, and the deformable section is made of shape memory alloy material. As a result, the deformable section can deform according to the temperature change, thereby changing the area of ​​the control section; wherein, the control section is the section with the smallest flow area of ​​the combustion chamber. In the above-mentioned channel structure, ramjet engine and aircraft, as the working Mach number of the ramjet engine increases, the deformable section can reach the training temperature through active or passive temperature control, and the geometric structure is gradually deformed, so that the area of ​​the control section is variable, reaching The purpose of adjusting the channel configuration of the ramjet combustion chamber with the flight state. The above-mentioned flow channel structure has no complicated mechanical adjustment structure, and has the characteristics of simple adjustment method and can reduce the difficulty of sealing technology.

Description

technical field [0001] The invention relates to the technical field of ramjet engines, in particular to a flow path structure of ramjet engines, ramjet engines and aircrafts. Background technique [0002] When an air-breathing hypersonic vehicle using a ramjet engine climbs along the flight trajectory in the range of Mach number Ma3-Ma8, the flow of the initial relay operating point (Mach number is Ma3) and the final cruise state operating point (Mach number is Ma8) The air flow and the fuel flow for combustion work vary greatly. For the initial relay operating point, it is expected that the flow area of ​​the internal runner of the ramjet engine should be relatively large, so as to prevent the pressure gradient generated in the engine combustion chamber from propagating upstream and affecting the normal operation of the intake port; however, for the cruising state In terms of ramjet, it has been proved that the smaller flow area of ​​the inner runner of the ramjet is condu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K7/10F02K7/08F02C7/04F23R3/42
CPCF02K7/10F02K7/08F02C7/04F23R3/42
Inventor 杨雷超潘余王宁安彬邢航李庆王良叶童
Owner NAT UNIV OF DEFENSE TECH