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Rocket engine, rocket, and method for starting rocket engine

A rocket engine and turbine technology, which is applied to rocket engine devices, engine functions, machines/engines, etc., can solve the problems of high cost, exhaust of combustion gas, and large energy loss, so as to reduce energy loss, improve combustion efficiency, The effect of improving robustness

Inactive Publication Date: 2015-09-16
MITSUBISHI HEAVY IND LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Potentially lower reliability and higher cost due to the need for an additional burner
The second problem is that the combustion gas that drives the turbine is directly exhausted
The energy of the combustion gas driven by the turbine is not effectively utilized and becomes a loss, so the energy loss is large
The third problem is that the gas generator requires extremely high reliability
This rocket engine is difficult to apply to rocket engines that use hydrocarbons as fuel

Method used

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  • Rocket engine, rocket, and method for starting rocket engine
  • Rocket engine, rocket, and method for starting rocket engine
  • Rocket engine, rocket, and method for starting rocket engine

Examples

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no. 1 Embodiment approach

[0030] The structure of the rocket engine of the first embodiment and a rocket to which it is applied will be described. figure 2 It is a schematic diagram showing the structure of the rocket engine of this embodiment and the rocket to which it is applied. Rocket 1 flies by burning hydrocarbon fuel and oxidizer, and ejecting combustion gas backward. The rocket 1 has a rocket body 2 and a rocket engine 3 .

[0031] The rocket body 2 includes a fuel tank 4 , an oxidizing agent tank 5 , and a control unit 6 . The fuel tank 4 stores liquid hydrocarbon fuel. The fuel tank 4 delivers fuel to the rocket engine 3 by means of gas pressurization or the like based on the control of the control unit 6 . The oxidizing agent tank 5 stores a liquid oxidizing agent (for example: LOX). The oxidant tank 5 sends oxidant to the rocket engine 3 by means of gas pressurization or the like based on the control of the control unit 6 . The control unit 6 is an information processing device such a...

no. 2 Embodiment approach

[0059] The structure of the rocket engine of the second embodiment and the rocket to which it is applied will be described. This embodiment differs from the first embodiment in that the catalyst portion is provided separately instead of the piping of the fuel flow path. Hereinafter, differences will be mainly described.

[0060] Figure 5 It is a schematic diagram showing the structure of the rocket engine of this embodiment and the rocket to which it is applied. In the rocket engine 3 a of the present embodiment, the catalyst unit 52 is provided separately as a catalytic reactor in the middle of the fuel flow path 37 , not in at least part of the piping of the fuel flow path 34 to the fuel flow path 36 . In other words, in the first embodiment, the catalyst part 51 is the fuel flow path 34 to the fuel flow path 36, which are also the catalyst part 51, but in this embodiment, the catalyst part 52 is an independent catalytic reactor, and is provided in the fuel flow path. on...

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Abstract

A rocket engine is provided with a fuel flow path (31-39), a catalyst part (51), a turbine (12), a first pump (11), a combustion chamber (21), and a nozzle (22). Hydrocarbon-based fuel flows through the fuel flow path (31-39). The catalyst part (51) is provided in the middle of the fuel flow path (31-39), and gasifies the fuel. The turbine (12) is driven by the gasified fuel. The first pump (11) supplies the fuel to the fuel flow path (31-39) by the driving of the turbine (12). The combustion chamber (21) burns the gasified fuel supplied from the fuel flow path (31-39), and an oxidizing agent. The nozzle (22) delivers combustion gas in the combustion chamber (21) and is cooled by heat exchange with part of the fuel flow path (31-39).

Description

technical field [0001] The present invention relates to rocket motors, in particular to liquid rocket motors using hydrocarbons as fuel. Background technique [0002] Liquid rocket engines using hydrocarbons as propellants are known. The liquid rocket motor has a turbopump for supplying propellant (oxidant and hydrocarbon). The turbopump is driven by the rotation of the turbine. This turbine uses hydrocarbon as fuel and rotates by combustion gas generated in an auxiliary combustor called a gas generator (sub combustor) that uses LOX (Liquid Oxygen) as an oxidant, for example. For example, Non-Patent Document 1 discloses a liquid rocket engine to which such a gas generator cycle is applied. [0003] figure 1 It is a schematic diagram showing the structure of the liquid rocket motor described in this non-patent document 1. In this figure, the upper left image is a liquid rocket motor with a gas generator cycle applied. In this rocket engine, a fuel pump and an oxidizer p...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/64B64G1/00F02K9/46F02K9/68
CPCB64G1/401F02K9/64F02K9/68F02K9/48F02K9/972F05D2260/85F02K9/62B64G1/00
Inventor 川又善博尾场瀬公人
Owner MITSUBISHI HEAVY IND LTD
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