Supersonic speed combustion chamber burner scheme with novel injection structure

A technology of supersonic combustion chamber and combustion chamber, which is applied in the direction of combustion chamber, combustion method, continuous combustion chamber, etc., can solve the problems that have not been proposed, and achieve the effect of improving effective mixing and small total pressure loss

Inactive Publication Date: 2009-04-29
周建兴
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  • Abstract
  • Description
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Problems solved by technology

However, there is no new proposal on how to make full use of the flame stabilization effect of the groove structure, and how to combine the f

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  • Supersonic speed combustion chamber burner scheme with novel injection structure
  • Supersonic speed combustion chamber burner scheme with novel injection structure
  • Supersonic speed combustion chamber burner scheme with novel injection structure

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Embodiment Construction

[0026] The specific implementation of the supersonic combustion chamber nozzle design scheme of the new injection structure proposed by the present invention can be carried out in the following design manner. When designing the actual combustion chamber structure, according to the specific design requirements, the layout positions of the groove, the groove front nozzle and the groove front wall nozzle can be appropriately modified, and after the simulation analysis is carried out with a certain numerical value, the fuel nozzle The design ideas and schemes are applied to the structural design of the supersonic combustion chamber. In this way, on the one hand, it can reduce the research and development expenses in the initial stage of the design work in the past; on the other hand, to a large extent, the weight of the supersonic ramjet engine can be reduced, the size of the final product can be reduced, and the maneuverability of the final power system product can be increased. ...

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Abstract

The innovation of the invention is to provide a proposal for a superacoustic combustion chamber nozzle with a novel structure. The proposal has the characteristic that fuel nozzles are arranged in front of a combustion chamber groove and at the front wall surface of the groove. The design proposal applies the structural design of the groove and the fuel nozzles at the groove in a superacoustic combustion chamber and an improved type superacoustic combustion chamber, and can ensure that fuels are evenly injected in the superacoustic combustion chamber for achieving sufficient mixing, thereby ensuring the ignition and stable combustion of fuels in superacoustic air flow. Compared with the prior nozzle proposal of the superacoustic combustion chamber, the design proposal has the following advantages: the fuels are evenly injected, fully blended, ignited stably and combusted stably, thereby shortening the structural size of the superacoustic combustion chamber, improving the size of the whole superacoustic power system, and having considerable potential economic benefit. The superacoustic combustion chamber nozzle with the novel structure mainly comprises struts in the combustion chamber, the groove and the fuel nozzles in front of the groove and in the groove.

Description

1. Technical field [0001] Fuel ignition and stable combustion are the key issues to achieve stable combustion in a hypersonic combustor. In the ramjet power system with supersonic combustion chamber and subsonic combustion chamber as the main components, its main performance indicators are severely restricted by the structural size of the combustion chamber. On a deeper level, these performance indicators are all subject to processes such as fuel blending, ignition and stable combustion in the combustion chamber. 2. Background technology [0002] The scramjet combustor is an energy conversion device. The chemical energy released by the fuel through combustion is converted into heat energy of the airflow. In the supersonic combustion chamber, in order to better organize the combustion, fuel nozzles with different structures and methods are arranged in different ways on the support plate and wall (or cavity wall) in the supersonic combustion chamber, and the fuel is placed in...

Claims

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Application Information

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IPC IPC(8): F23R3/28
Inventor 周建兴
Owner 周建兴
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