NOFBX thrust chamber based on micro-channel regenerative cooling technology

A regenerative cooling, micro-channel technology, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve problems such as the inability to meet the cooling requirements of NOFBX combustion chambers

Inactive Publication Date: 2021-07-06
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the problem that the existing liquid film cooling and regenerative cooling of liquid rocket engines cannot meet the cooling requirements...

Method used

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  • NOFBX thrust chamber based on micro-channel regenerative cooling technology
  • NOFBX thrust chamber based on micro-channel regenerative cooling technology
  • NOFBX thrust chamber based on micro-channel regenerative cooling technology

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Embodiment Construction

[0032] In order to make the purpose, advantages and features of the present invention clearer, a NOFBX thrust chamber based on microchannel regenerative cooling technology proposed by the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0033] The NOFBX thrust chamber based on the microchannel regenerative cooling technology provided by this embodiment is as follows: figure 1 As shown, the combustion chamber, injector, spark plug 31 and propellant inlet conduit 41 are included.

[0034] The combustion chamber includes an inner casing 11 , an outer casing 12 , a cover plate 13 and an annular blocking cover 14 . The inner shell 11 and the outer shell 12 are set coaxially, and their rear ends are flush with each other. A first channel is formed between the inner shell 11 and the outer shell 12 . The cover plate 13 is fixedly installed at the opening of the front end of the outer shell 12 , and t...

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Abstract

The invention relates to an NOFBX thrust chamber based on a micro-channel regenerative cooling technology. The NOFBX thrust chamber aims to solve the problem that liquid film cooling and regenerative cooling of an existing liquid rocket engine cannot meet the cooling requirement of an NOFBX combustion chamber. The thrust chamber includes a combustion chamber, an injector, an electric spark plug, and a propellant inlet conduit. The combustion chamber comprises an inner shell, an outer shell, a cover plate and an annular blanking cap, the inner shell and the outer shell are coaxially arranged, a first channel is formed between the inner shell and the outer shell, the cover plate is arranged at the front end of the outer shell, and the annular blanking cap is arranged at the rear end of the first channel. The injector comprises an injector main body and an injector core body, an annular groove is formed in the front end face of an annular injection plate of the injector main body, a plurality of direct-current injection holes are formed in the bottom of the groove, and the injector core body is made of a first porous medium material and is arranged in the annular groove. The injector is arranged on the inner side of the front end of the inner shell, a second channel is formed between the injector and the cover plate, and regeneration cooling channel cores made of a second porous medium material are arranged in the first channel and the second channel.

Description

technical field [0001] The invention relates to the technical field of liquid rocket engines, in particular to a NOFBX thrust chamber based on microchannel regenerative cooling technology. Background technique [0002] NOFBX propellant is a new type of oxygen-burning premixed propellant composed of nitrous oxide and hydrocarbon fuel (ethylene, acetylene or ethane), where "NOFB" stands for the combination of nitrous oxide and hydrocarbon, and "X" Represents two numbers, the first number indicates the C2 family, where 1 indicates ethane, 2 indicates ethylene, and 3 indicates acetylene; the second number indicates the mixing ratio of oxidizer and fuel. For example, NOFB29 represents N with a mixing ratio of 9 2 O and C 2 h 4 premixed propellants. As a green and non-toxic propellant, NOFBX propellant has the advantages of high specific impulse performance of bicomponent propellant and simple monopropellant engine system. It can realize self-pressurization and deep throttling...

Claims

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Application Information

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IPC IPC(8): F02K9/64F02K9/52F02K9/95
CPCF02K9/64F02K9/52F02K9/95
Inventor 张锋尚冬琴冯建畅胡洪波刘计武
Owner XIAN AEROSPACE PROPULSION INST
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