Pulse detonation rocket engine oil supply scheme beneficial to cooling and detonation initiation of wall surface

Abstract

The invention provides a pulse detonation rocket engine oil supply scheme beneficial to cooling and detonation initiation of a wall surface. The pulse detonation rocket engine oil supply scheme structurally comprises a detonation combustion chamber, common rail oil supply pipes, an oil supply ring pipe, a rotating valve, a fuel oil preheating cavity, a sparking plug and a coaxial nozzle, wherein the detonation combustion chamber is sequentially divided into two parts of a DDT section and a detonation transmission section in the direction of an incoming flow. Fuel oil serves as fuel in the detonation combustion chamber, and is mixed with an oxidizing agent to form a detonable mixture, the fuel oil also serves as a cooling medium, carries out oil film cooling on the wall surface of the DDT section of the detonation combustion chamber and carries out sweat cooling on the wall surface of the detonation transmission section, and a part of fuel oil is preheated, so that the fuel injection uniformity in the detonation combustion chamber is improved, the discharge temperature after detonation is raised; and the oil supply scheme serves as a fluid DDT scheme, and an original solid DDT device is replaced, so that change from slow combustion to the detonation is accelerated, and the total pressure loss during the detonation initiation is reduced.

Description

technical field [0001] The invention relates to the technical field of pulse detonation engines, in particular to a fuel supply scheme for pulse detonation rocket engines that is beneficial to wall surface cooling and detonation. Background technique [0002] Detonation combustion is a constant-volume combustion method different from traditional isobaric combustion. It has the characteristics of high thermal cycle efficiency, fast heat release rate, and strong self-pressurization capability. The detonation engine is the application of detonation combustion in propulsion. The Pulse Detonation Rocket Engine (PDRE for short) is a new concept engine that uses high-frequency pulse detonation waves to generate thrust. Since PDRE has the advantages of high thermal cycle efficiency, simple structure, and light weight, and its technology is relatively mature, the aerospace industry has accelerated the research on PDRE in recent years, hoping to realize its engineering application as ...

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Problems solved by technology

[0004] In addition, the fuel atomization and mixing effect in PDRE will also affect the working performance of the engine. If the mixing in the DDT section is uneven, it will increase the difficulty of detonation; if the mixing in the detonation propagation section is uneven, the gas mixture in the pipe will Poor detonability may lead to decoupling of the detonation wave during propagation, weakening the detonation self-pressurization effect

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