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Single-tube rotary valve type double-bypass pulse detonation engine

A technology of pulse detonation and rotary valve, which is applied in the direction of machines/engines, mechanical equipment, jet propulsion devices, etc. It can solve the problems of high valve driving power, large volume and weight, and complex structure, and achieve light weight, small volume, The effect of simple structure

Inactive Publication Date: 2011-02-09
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Purpose of the invention: In order to solve the shortcomings of the existing rotary valve multi-tube pulse detonation engine, such as complex structure, large volume and weight, high valve driving power, difficulty in multi-tube coordinated control, and coupling interference, the present invention provides a simple structure , light weight, small size, and avoid the coordination, control and coupling interference between multiple detonation tubes. Single-tube rotary valve double-duct pulse detonation engine

Method used

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  • Single-tube rotary valve type double-bypass pulse detonation engine
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  • Single-tube rotary valve type double-bypass pulse detonation engine

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Embodiment Construction

[0011] see figure 1 and figure 2 As shown, the present invention discloses a single-pipe rotary valve type double-duct pulse detonation engine, a central cone 1, a lip cover 2 surrounding the central cone 1, and an outer shell 3 extending from the lip cover 2 along the longitudinal direction , the thrust wall barrel 4 extending from the central cone 1, the barrel valve 5, the drive motor 6 connected to the barrel valve 5 and used to drive the barrel valve 5 to rotate, and the barrel valve 5 to penetrate and be located in the outer shell 3 Detonation tube 7, igniter 8, fuel nozzle 9, front bearing 10, rear bearing 11, front support 12 and rear support 13. The cylindrical valve 5 and the driving motor 6 are located inside the thrust wall cylinder 4; the cylindrical valve 5 is provided with a plurality of inner air intake holes 20 and an auxiliary air intake baffle 21 located at the rear end of the inner air intake holes 20, so that The thrust wall cylinder 4 is provided with ...

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Abstract

The invention provides a single-tube rotary valve type double-bypass pulse detonation engine. In the detonation engine, air inlets are repeatedly opened and closed through circumferential rotation of a barrel type valve, and then the rotary valve type single-tube detonation engine is realized. The invention not only has the advantages of simple structure, light weight and small volume, but also avoids the technical problems of coordination, control, coupling interference, and the like among a plurality of detonation tubes. The double-bypass design is also adopted by the detonation engine, captured air flow is switched between the inner bypass and the outer bypass, therefore, the periodic blockage of the air flow in the air inlet is avoided, a low flow resistance is kept, and the ejection effect of inner bypass high-speed air flow to outer bypass air flow is utilized for realizing additional push effect.

Description

technical field [0001] The invention relates to a pulse detonation engine, in particular to a single-pipe rotary valve type double-duct pulse detonation engine adopting a barrel-type rotary valve and internal and external double ducts. Background technique [0002] The pulse detonation engine is a new concept engine that uses pulse detonation combustion waves to generate thrust. Because the propagation speed of the detonation wave is extremely fast (up to several kilometers per second), so that the combustion products have no time to expand during the combustion process, the detonation process is very close to the constant volume combustion process, so theoretically its cycle thermal efficiency is significantly higher than that of the previous ones. Conventional aero-engine based on isobaric combustion. In addition, because the detonation process also has a strong supercharging capacity, the detonation engine can eliminate rotating components such as compressors and turbine...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K7/02F02K3/00
Inventor 陈伟韩启祥谭慧俊温玉芬
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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