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Lightweight composite cooling thrust chamber body device

A composite cooling and thrust chamber technology, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve problems such as limited weight reduction and thermal structure damage, and achieve improved performance, high connection strength, and reliable thermal protection Effect

Pending Publication Date: 2022-07-08
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology

[0004] The purpose of the present invention is to solve the technical problems of thermal structure damage and limited weight loss caused by the local optimization of the current lightweight thrust chamber body, and propose a lightweight composite cooling thrust chamber body device; aiming at the current space engine For lightweight requirements, a thrust chamber body structure using titanium alloy lightweight materials is provided. quality, high performance and reliable thermal protection

Method used

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  • Lightweight composite cooling thrust chamber body device
  • Lightweight composite cooling thrust chamber body device
  • Lightweight composite cooling thrust chamber body device

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Embodiment Construction

[0038] In this embodiment, "front" and "rear" are along the gas flow direction, the gas coming from is front, and the gas going back.

[0039] see figure 1 and figure 2 , this embodiment provides a lightweight composite cooling thrust chamber body device, including a high temperature anti-oxidation thermal barrier coating 2, an inner wall 3, a cooling jacket 4 and an outer wall 5 sequentially arranged from inside to outside; the thickness of the inner wall 3 It is 0.8mm~1.5mm; among them, the inner wall 3, the cooling jacket 4 and the outer wall 5 are integrally formed by 3D printing technology, so that the number of welds for preparing the thrust chamber body is reduced from 150 to 0, and the number of parts is reduced to 1 , the connection strength of the inner wall 3 and the outer wall 5 is higher, which is more conducive to realizing reliable thermal protection of the body.

[0040] The high-temperature anti-oxidation thermal barrier coating 2 includes an MCrAlY anti-ox...

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Abstract

The invention relates to a lightweight composite cooling thrust chamber body device to solve the technical problems that a thermal structure is damaged and the weight reduction degree is limited due to the fact that local optimization is adopted for lightweight of a thrust chamber body at present. The device comprises a high-temperature anti-oxidation thermal barrier coating, an inner wall, a cooling jacket and an outer wall which are sequentially arranged from inside to outside. The thrust chamber body part is sequentially provided with a cylinder section, a convergence section and an expansion section from front to back; a coolant inlet and an inlet liquid collecting cavity formed in the inlet liquid collecting ring are formed in the outer side surface of the rear end of the expansion section; a coolant outlet and an outlet liquid collecting cavity formed in the outlet liquid collecting ring are formed in the outer side surface of the front end of the cylindrical section; the cooling jacket comprises a plurality of cooling channels arranged in the extending direction of the thrust chamber body and connecting ribs arranged between the adjacent cooling channels. The multiple cooling channels are evenly distributed in the circumferential direction. The cooling channel is communicated with the inlet liquid collecting cavity and the outlet liquid collecting cavity; the inner wall, the cooling jacket and the outer wall are all made of titanium alloy materials.

Description

technical field [0001] The invention relates to a thrust chamber body device, in particular to a lightweight composite cooling thrust chamber body device. Background technique [0002] The thrust-to-mass ratio (thrust produced per kilogram of structural mass) of space engines has also become more and more demanding as the payloads transported to space become larger and larger. Therefore, the structural mass of the engine should be minimized to effectively improve the thrust-to-mass ratio. Lightweight is one of the important directions for the development of liquid rocket engines in the future. As the core component of the liquid rocket engine, the thrust chamber accounts for more than half of the total weight of the entire engine. Therefore, the weight of the thrust chamber is the key to the lightweight of the engine. . [0003] The weight reduction scheme of the traditional thrust chamber is mainly based on local structural topology optimization and weight reduction, but ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/64
CPCF02K9/64
Inventor 谭永华卞香港高坤宋大亮李龙飞王春民王化余章荣军凌前程
Owner XIAN AEROSPACE PROPULSION INST
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