A two-component air turbine rocket propulsion system

An air turbine, rocket propulsion technology

Active Publication Date: 2020-06-30
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the technical problem that the existing aircraft power system cannot meet the needs of hypersonic aircraft for the power system, the present invention provides a two-component air turbine rocket propulsion system

Method used

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  • A two-component air turbine rocket propulsion system
  • A two-component air turbine rocket propulsion system
  • A two-component air turbine rocket propulsion system

Examples

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Embodiment Construction

[0042] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0043] refer to figure 1 , a two-component air turbine rocket propulsion system, including an engine casing 3, a secondary combustion chamber 8 and an exhaust nozzle 9 connected in sequence along the direction of gas injection.

[0044] The inner cavity of the engine casing 3 and the secondary combustion chamber 8 is provided with a rectifying cone 1, an axial fan 2, a connecting shaft 4, a primary combustion chamber 5, a gas turbine 6 and a mixing device 7 in sequence along the gas injection direction. In order to reduce heat loss, the inner walls of the secondary combustion chamber 8 and the tail nozzle 9 are provided with heat insulating linings.

[0045] The outlet end of the rectifying cone 1 is connected to the inlet of the axial flow fan 2 . One end of the connecting shaft 4 is sleeved in the inner hole of the axial fan 2 and fixedly c...

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Abstract

The invention relates to an aircraft power system, in particular to a dual-component air turbine rocket propulsion system. The technical problem that existing aircraft power systems cannot meet the requirements of hypersonic aerocrafts for power systems is solved. According to the technical solution, the dual-component air turbine rocket propulsion system comprises an engine shell, a secondary combustion chamber and an exhaust nozzle, all of which are sequentially connected in the gas injection direction; a fairing cone, an axial fan, a connecting shaft, a primary combustion chamber, a gas turbine and a mixing device are arranged in an inner cavity of the engine shell and an inner cavity of the secondary combustion chamber; the outlet end of the fairing cone is connected to an inlet of theaxial fan; the primary combustion chamber is arranged between the axial fan and the gas turbine; an inlet of the primary combustion chamber is connected with a propellant supply pipeline, and an outlet of the primary combustion chamber is connected with an inlet of the gas turbine; an outlet of the gas turbine communicates with an inner runner in the mixing device; and an outer runner formed between the mixing device and the secondary combustion chamber communicates with an outlet of the axial fan.

Description

technical field [0001] The invention relates to an aircraft power system, in particular to a two-component air turbine rocket propulsion system. Background technique [0002] Aircraft is the core of aerospace technology and a highly comprehensive product of modern science and technology. Hypersonic aircraft refers to aircraft, missiles, artillery shells and other winged or wingless aircraft that fly faster than 5 times the speed of sound. They have the characteristics of high penetration success rate and have huge military value and potential economic value. It is an important research and development direction in the field of aerospace. [0003] A hypersonic vehicle not only needs to cruise at a hypersonic speed (more than 5 times the speed of sound), but also needs to be able to take off and land horizontally, and must also be reusable, so its power system must have the ability to work at a wide Mach number. The Mach number is the ratio of the speed of an aircraft in air...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/78F02K9/60
CPCF02K9/60F02K9/78
Inventor 南向谊马元朱岩李哲李光熙逯婉若黄乐萍刘典多
Owner XIAN AEROSPACE PROPULSION INST
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