Integrated propellant supply system of rocket based combined circulating engine

Abstract

The invention discloses an integrated propellant supply system of a rocket based combined circulating engine. The integrated propellant supply system consists of a liquid oxygen path supply system, a kerosene path supply system and a fuel gas system; the liquid oxygen path supply system provides an oxidant for the engine; the kerosene path supply system provides fuels for the engine; the fuel gas system provides turbine driving fuel gas for a turbine; and the liquid oxygen path supply system and the kerosene path supply system are symmetrically arranged with respect to a fuel gas generator 14. The supply system takes a fuel gas generator circulating system with a simple structure as a basic structural form for discharging the turbine driving fuel gas into a low-pressure ramjet flow path to carry out complementary combustion, so that an engine complementary combustion circulating system with a relatively simple structure and excellent performance is formed; moreover, the system has a large range of regulating capacity, and also meets supply needs of a main rocket propellant and engine secondary fuels of the rocket based combined circulating engine. The propellant supply system increases an energy utilization rate and improves engine performance, and can be used for wide-envelop multi-mode RBCC engine system integrating.

Description

technical field [0001] The invention relates to the field of rocket-based combined cycle engines, in particular to an integrated propellant supply system for rocket-based combined cycle engines. Background technique [0002] A reasonable and reliable propellant supply system is not only the fundamental guarantee for the normal operation of the engine, but also an effective means to reduce the negative mass of the engine and increase the specific impulse of the engine. The rocket-based combined cycle engine integrates the rocket engine and the ramjet engine in the same flow channel, which effectively improves the specific impulse and thrust-to-weight ratio of the engine, and is the most promising power device for aerospace vehicles in the future. The working process of the rocket-based combined cycle engine experiences ejection, sub-combustion, super-combustion, and pure rocket modes. The working parameters of the propellant supply system vary greatly under different working ...

AI Technical Summary

Problems solved by technology

Usually, it is very difficult to develop a high-thrust afterburning cycle system based on a rocket engine, and the structure of a hybrid cycle system with a rocket engine afterburning cycle is more complicated.

Moreover, the expansion cycle in the Strutjet scheme is only suitable for liquid oxygen and liquid hydrogen engines, not for liquid oxygen and kerosene engines.

The series-parallel pump solution in the prior art has high technical risk, great difficulty in development, and high development cost

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