Rocket ejector and thermal protection structure and method thereof

A technology for thermal protection structure and ejection of rockets, which is applied in the direction of rocket engine devices, jet propulsion devices, ramjet engines, etc., can solve the problems of insufficient cooling of the throat, and achieve good cooling effect, less coolant, and high reliability. Effect

Pending Publication Date: 2019-05-28
CENT SOUTH UNIV
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Problems solved by technology

The nose cone at the leading edge of the ejection rocket is cooled by lamination to solve the local overheating problem caused by the particles in the gas blocking the cooling channel; the thrust chamber adopts exhaust cooling to make full use of the coolant, and the nozzle part is added with porous sweat cooling to solve the throat Insufficient cooling problem

Method used

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  • Rocket ejector and thermal protection structure and method thereof
  • Rocket ejector and thermal protection structure and method thereof
  • Rocket ejector and thermal protection structure and method thereof

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Embodiment Construction

[0034] In order to enable those skilled in the art to better understand this technology, we will further describe the present invention in detail in conjunction with the accompanying drawings and specific implementation examples.

[0035] The embodiment of the present invention provides a heat protection structure for a TRRE ejection rocket using exhaust and sweat compound cooling. The TRRE ejection rocket includes a leading edge nose cone 1 and a thrust chamber 2, and the thrust chamber 2 includes a combustion chamber 20 and a thrust chamber 2. Nozzle 21, the nozzle 21 is divided into a nozzle inner layer 210 and a nozzle outer layer 211; the thermal protection structure includes a sweat cooling structure and a discharge cooling structure, and the sweat cooling structure includes a laminate sweat cooling structure and a porous sweat cooling structure Cooling structure: the front nose cone 1 adopts a laminar sweating cooling structure, the combustion chamber 20 and the nozzle o...

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Abstract

The invention discloses a thermal protection structure and method of utilizing emission and transpiration combined cooling for a TRRE (turbo-aided rocket-augmented ramjet combined cycle engine) rocketejector. The rocket ejector is divided into a front edge head cone and a thrust chamber, and the front edge head cone and the thrust chamber are cooled respectively. Laminate transpiration cooling isadopted by the front edge head cone portion to conduct thermal protection. The mode of combined cooling of emission cooling and transpiration cooling is adopted by the thrust chamber portion, and a spiral cooling channel structure is adopted by the emission cooling. The outer surface and the inner surface of a combustion chamber are cooled through emission cooling at the same time, the cooling effect of a spray pipe portion is poor, and then porous transpiration cooling is conducted on the spray pipe portion. The thermal protection structure and method are good in cooling effect, small in quantity of cooling agents and high in reliability, and can achieve the purpose of being reusable.

Description

technical field [0001] The invention relates to a thermal protection structure and method for ejecting a rocket in a TRRE engine, in particular to performing heat protection on an ejecting rocket in a TRRE engine by using combined cooling of discharge and sweating. Background technique [0002] For a long time, countries all over the world have been increasing the use and development of space resources, but most of them are active in the atmosphere and earth orbit within 20km, and pay attention to the adjacent space (about 20-100km) between the two less. With the development of the level of science and technology and the concept of air-space integrated operations, countries have begun to pay attention to the adjacent space between air and space. As an important tool for fast travel between the sky and the earth, near space vehicles, one of its core technologies is the power system, and put forward higher requirements for it, which need to have high performance, low cost, wi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K7/18F02K7/16F02K9/64F02K9/97
Inventor 罗世彬席文雄袁运飞戴健许德泉
Owner CENT SOUTH UNIV
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