Actively Cooled Pintle Injectors for Inline Ignition

A technology of active cooling and ignition device, used in rocket engine devices, jet propulsion devices, machines/engines, etc., which can solve the problems of large propellant flow resistance, ablation, and difficulty in applying engineering products.

Active Publication Date: 2020-05-15
重庆零壹空间航天科技有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, due to the structural characteristics of the pintle injector itself, its head is often eroded and ablated by the gas vortex.
[0003] In order to solve the above problems, there is also a pintle injector designed in the prior art, in which an internal cooling channel is added, but because the structure of this pintle injector is too complicated and there is propellant flow resistance It is difficult to be applied to real engineering products, so it is urgent to improve the existing pintle injectors in the prior art

Method used

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  • Actively Cooled Pintle Injectors for Inline Ignition
  • Actively Cooled Pintle Injectors for Inline Ignition
  • Actively Cooled Pintle Injectors for Inline Ignition

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Embodiment Construction

[0021] The application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain related inventions, rather than to limit the invention. It should also be noted that, for ease of description, only parts related to the invention are shown in the drawings.

[0022] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.

[0023] Please refer to figure 1 with figure 2 Disclosed is an actively cooled pintle injector suitable for an embedded ignition device.

[0024] An actively cooled pintle injector suitable for an embedded ignition device, comprising: a hollow cylindrical injector body 1 with one end closed and ...

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Abstract

This application provides a specific structure of an active cooling pintle injector suitable for an embedded ignition device. According to the technical scheme, a main injection hole and an auxiliaryinjection channel arranged in a first bench are designed, two levels of injection forms are formed on an injector body, in view of the different structural forms of the main injection hole and the auxiliary injection channel, the propellant flow distributed in the main injection hole and the auxiliary injection channel is different, while the propellants in the main injection hole and the auxiliary injection channel are sprayed in the radial direction of the injector body and can be matched with a flame injection channel to form the first combustion and the second combustion respectively, theoverall combustion is made to be more adequate advantageously, and the occurrence of the combustion instability is inhibited to a certain extent.

Description

technical field [0001] The present disclosure generally relates to the field of space propulsion technology, and in particular to an actively cooled pintle injector suitable for an embedded ignition device. Background technique [0002] The pintle injector has been widely used in space liquid rocket engines due to its advantages of high mixing efficiency, good atomization effect, high combustion stability and easy realization of variable thrust adjustment. However, due to the structural characteristics of the pintle injector itself, its head is often eroded and ablated by the gas vortex. [0003] In order to solve the above problems, there is also a pintle injector designed in the prior art, in which an internal cooling channel is added. It is difficult to be applied to real engineering products, so it is urgent to improve the existing pintle injector in the prior art. Contents of the invention [0004] In view of the above-mentioned defects or deficiencies in the prior ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/52F02K9/95
CPCF02K9/52F02K9/95
Inventor 沈函默舒畅马超
Owner 重庆零壹空间航天科技有限公司
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