High Thrust Closed Expansion Cycle Rocket Engine Based on Improved Expansion Deflection Nozzle

Abstract

The invention discloses a closed expansion circulation rocket engine with an expansion / deflection nozzle, and particularly relates to a closed expansion circulation rocket engine. In the closed expansion circulation rocket engine, the mushroom-shaped center body of the expansion / deflection nozzle has the high diameter, and the surface is the heat exchanger surface for driving working media to flow. Since more heat absorption surfaces are arranged, the working media absorbing more heat can drive turbines trough higher power, and the original industry-recognized limitation that thrust of closedexpansion circulation rocket engines is not larger than 30 tons is broken through. The section of the mushroom rod portion of the mushroom-shaped center body deviates from a circle, by means of differential control on flow of pintle injectors evenly or unevenly distributed on the periphery, three-axis vector propulsion in the nozzle fixed condition is achieved. A pipeline leading to the turbine can be omitted for the turbines which are embedded into the thickened mushroom rod portion of the center body. By means of the structure that the coaxial contra-rotating turbines drive a fuel pump and an oxidizing agent pump, the size is reduced.

Description

technical field

[0001] The invention relates to a closed expansion cycle rocket engine using an expansion / deflection nozzle, in particular to a mushroom-shaped central body of the expansion / deflection nozzle which has a relatively thick diameter, and its surface is also formed by the working fluid of the driving turbine. A closed expansion cycle rocket engine with flow over the heat exchanger surface. Background technique

[0002] The heat energy possessed by the working medium that drives the turbine of the existing closed expansion cycle rocket engine comes from the inner wall of the combustion chamber and the nozzle. Since the heat energy that the working medium can absorb is limited by the heat exchange surface area, it is an industry consensus that the thrust of the existing closed expansion cycle rocket engine is not greater than 30 tons. In order to realize the thrust vector control of the existing rocket engine, the pump back swing technology must be adopted or the ...

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