Rocket engine heat exchanger and aerospace craft

Abstract

The invention discloses a rocket engine heat exchanger and an aerospace craft. A rocket engine comprises a combustion chamber body with a combustion cavity. An outer-layer structure is arranged on theouter wall of the combustion chamber body, and a heat exchange space allowing a pressurizing working medium and the combustion cavity to be in heat exchange is formed between the outer-layer structure and the combustion chamber body. An inlet structure and an outlet structure communicating with the heat exchange space to enable the pressurizing working medium to come in and go out is further included. As the heat exchange space allowing the pressurizing working medium and the combustion cavity to be in heat exchange is formed between the outer-layer structure arranged on the outer wall of thecombustion chamber body and the combustion chamber body, a heat exchanger device specially designed for a rocket accumulator pressurizing system on the engine is omitted, the structural mass of the engine is reduced, and therefore the thrust-mass ratio performance of the engine is improved. The parts of the engine are simplified, and the structural reliability of the heat exchanger is improved.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a rocket engine heat exchanger and an aerospace vehicle. Background technique [0002] In the prior art, due to the high pressure in the combustion chamber of the high-thrust liquid rocket engine, it is necessary to pressurize the propellant components, so a pressurized working medium is required. The pressurized working medium can be the propellant used in rocket engines, or inert gases such as nitrogen and helium. The pressurized working medium often needs to exchange heat through a heat exchanger installed at the exhaust outlet of the turbine. During the heat exchange process, the high-temperature gas generated by the gas generator is discharged from the exhaust port of the turbine, thereby generating high-temperature turbine exhaust. The higher-temperature turbine exhaust is used to heat the increased working medium in the heat exchanger, so that the temperature of the pr...

AI Technical Summary

Problems solved by technology

[0005] Therefore, the technical problem to be solved by the present invention is to overcome that when the heat exchanger is placed on the turbine exhaust outlet of the rocket engine in the prior art, the overall structure of the rocket engine will be relatively complicated, and the weight will be heavier, which will make the thrust of the rocket engine The defect of poor mass ratio performance, so as to provide rocket engine heat exchanger and aerospace vehicle

Images