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

A rocket engine and high-thrust technology, applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of difficult cooling of the center body and low efficiency of the nozzle

Active Publication Date: 2019-09-20
李鹏
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The air plug rocket engine with nozzle height compensation capability has low nozzle efficiency when the rocket does not reach supersonic speed, and it is difficult to cool the center body

Method used

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

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Embodiment Construction

[0015] Figure 4 is along image 3 The cross-sectional view of the A-A line in the center reflects the positional relationship between the outer contour of the cross-section of the central fungus part and the surrounding injector and the side wall of the combustion chamber. implementation plan. Figure 4 Among them, 1 is the inner wall of the columnar combustion chamber, 2 is the cross-section of the fungus part of the central body with convex rounded square pillow shape, and 3 represents the installation position of the pintle injector numbered 1 on the top cover of the combustion chamber. image 3 It is a cross-sectional view showing the cooling passage and the position of the twin-shaft turbine embedded in the center body. The entire flow path of the cooling medium is: from bottom to top through the combustion chamber throat 10, upward through the combustion chamber side wall 1, from the edge of the combustion chamber top cover 4 radially inward through the combustion cha...

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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 ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/80F02K9/97
Inventor 李鹏
Owner 李鹏
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