Novel pre-cooling air combined engine

A cold air and engine technology, which is applied to machines/engines, rocket engine devices, mechanical equipment, etc., can solve the problems of low specific impulse performance of the system, difficult to achieve high system performance, and high fuel consumption rate, so as to improve the specific impulse performance, The effect of avoiding fuel waste and reducing fuel consumption

Active Publication Date: 2019-02-22
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology

[0003] The technical problem solved by the invention is: aiming at the problems in the current prior art that the fuel consumption rate of the engine pre-cooling technology is too high, the specific impulse performance of the system is low, and it is difficult to realize the high performance of the system, a new type of pre-cooling air combined engine is proposed

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  • Novel pre-cooling air combined engine

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Embodiment Construction

[0025] A new type of pre-cooled air combination engine, such as figure 1 As shown, it includes air combustion path 1, helium cooling path 2, and hydrogen energy supply path 3. Using the ultra-low temperature characteristics of liquid hydrogen fuel to absorb the heat in the high-temperature incoming air after stagnation in the intake port, it is introduced into the helium cooling path 2 As an intermediate cycle, the energy transfer and conversion between the air combustion path 1 and the hydrogen energy supply path 3 are carried out. Its characteristics are: the helium cooling circuit 2 adopts the circulation scheme of split flow and heat recovery, and uses the thrust chamber to replenish part of the heat for the helium cooling circuit 2; the hydrogen energy supply circuit 3 adopts the circulation scheme of staged cooling, and the hydrogen is absorbed in the heat exchanger After the waste heat from the helium enters the hydrogen turbine to expand and do work, the temperature dr...

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Abstract

The invention provides a novel pre-cooling air combined engine. The engine comprises an air combustion path (1), a helium cooling path (2), and a hydrogen energy supply path (3); and the ultralow temperature characteristic of the liquid hydrogen fuel is utilized to cool the high-temperature incoming flow air after being stagnated through an air inlet channel, the helium cooling path (2) is introduced to be used as an intermediate circulation to carry out energy transfer and conversion between the hydrogen energy supply path (3) and the air combustion path (1), and thus the fuel required by cooling and the fuel combustion rate are reduced; and meanwhile, the concurrent heating power of a heater is reduced. The engine has the characteristics that the flight envelope is large, the mode conversion is simple and convenient, the air pre-cooling efficiency is high, and the system specific impulse is high; and the engine can be used as one stage of a horizontal take-off and landing repeatabletwo-stage to-orbit vehicle and as a power system of near-air hypersonic velocity launching platform.

Description

technical field [0001] The invention relates to a novel precooling air combined engine, which belongs to the design field of precooling air combined engines. Background technique [0002] With the increasing frequency of space launch activities, the requirements for repeatable and low-cost space vehicles are becoming more and more urgent. At the same time, the strategic position of hypersonic vehicles in near space has gradually been paid attention to. In this context, the pre-cooled air-type combined power system that introduces a closed helium cycle as an intermediate medium has become one of the research hotspots in the field of hypersonics at home and abroad because of its advantages such as large working envelope, simple mode conversion, and high degree of component sharing. one. At present, the hot topic of this type of engine in the world is the SABER scheme proposed by the British REL company. This scheme includes two working modes: air-breathing mode and pure rocke...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/60F02K9/64
CPCF02K9/60F02K9/64
Inventor 张蒙正马海波李光熙刘典多南向谊马元逯婉若
Owner XIAN AEROSPACE PROPULSION INST
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