A New Type of Precooling Air Combined Engine

A cold air and engine technology, applied in the direction of machine/engine, rocket engine device, mechanical equipment, etc., can solve the problems of difficult to achieve high system performance, low system specific impulse performance, high fuel consumption rate, and achieve improved specific impulse performance, The effect of avoiding fuel waste and reducing fuel consumption

Active Publication Date: 2021-09-07
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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  • A New Type of Precooling Air Combined Engine
  • A New Type of Precooling Air Combined Engine
  • A New Type of Precooling 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

A new type of pre-cooled air combined engine, including air combustion path (1), helium cooling path (2), hydrogen energy supply path (3), by using the ultra-low temperature characteristics of liquid hydrogen fuel to cool the stagnant air through the intake port The final high-temperature incoming air is introduced into the helium cooling circuit (2) as an intermediate cycle to carry out energy transfer and conversion between the hydrogen energy supply circuit (3) and the air combustion circuit (1), reducing the fuel and cooling requirements Fuel combustion rate, while reducing the heating power of the heater, has the characteristics of large flight envelope, simple mode conversion, high air pre-cooling efficiency and high system specific impulse, and can be used as a repeatable two-stage orbiting aircraft for horizontal take-off and landing The power system of the first stage and adjacent air hypersonic launch 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 Patents(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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