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A double swirl injector

An injector, double swirl technology, applied in jet propulsion devices, machines/engines, rocket engine devices, etc., can solve the problems of insufficient atomization performance of the injector, difficulty in ignition and flame stabilization of the gas generator, etc. Strong anti-ablation ability, low manufacturing cost and good atomization performance

Active Publication Date: 2017-07-25
NAT UNIV OF DEFENSE TECH
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to provide a double-swirl injector to solve the problem of injector atomization when a liquid rocket engine or a gas generator adopts a non-volatile fuel (such as kerosene) and an oxidant (such as air) with low oxygen content. Insufficient performance and difficulty in ignition and flame stabilization of this type of gas generator

Method used

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Embodiment Construction

[0056] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways defined and covered by the claims.

[0057] 1. Single nozzle double swirl injector

[0058] Preferred embodiment one of the present invention is a single-nozzle double-swirl injector, see for details Figure 12 . When the liquid fuel flow rate is small, that is, the liquid fuel flow rate is less than 400g / s, a single nozzle configuration is adopted; the single nozzle configuration is a gas-liquid coaxial type, which is beneficial to the injection and atomization performance of non-volatile fuels such as kerosene, and the coaxial arrangement The gas swirler forms a low-velocity recirculation zone, which is beneficial to the flame stabilization of the combustion chamber.

[0059] The injector includes a top cover 1, a centrifugal nozzle 2, an upper bottom 3, a middle bottom 4, a gas cy...

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Abstract

The invention provides a dual-rotational-flow inspirator, which comprises a top cover, a nozzle, an upper bottom, a middle bottom, a gas whirlcone and an inspirator cavity, wherein the inspirator cavity is a barrel-shaped hollow cylinder; a fuel cavity is formed between the top cover and the upper bottom of the inspirator; a gas oxidizing agent cavity is formed between the upper bottom and the middle bottom of the inspirator; a water cavity is formed between the middle bottom of the inspirator and the base of the inspirator; an inner nozzle passes through mounting holes in the upper bottom, the middle bottom and the inspirator cavity and is fixedly arranged on the upper bottom via a thread; the gas whirlcone is installed on the nozzle by a thread; water nozzles are water holes evenly distributed on the circumstance on the base of the inspirator. The inspirator provided by the invention has the characteristics of simple structure, low cost, good atomization performance and stable flame.

Description

technical field [0001] The invention relates to injectors for liquid rocket engines and gas generators, in particular to fuel injection atomization for liquid rocket engines and gas generators. Background technique [0002] The injector is a device that injects the propellant into the combustion chamber in an appropriate ratio and state to produce efficient and stable combustion. It is an important part of liquid rocket engines and gas generators, and is the core of the above-mentioned engine designs. [0003] At present, the injection units widely used in liquid rocket engines are impact type and coaxial type. "Modern Engineering Design of Liquid Rocket Engine" (China Aerospace Press, 2003) introduces various forms of injection units on the liquid rocket engine. Among them, the impact injection unit guides one jet to collide with another or several jets so that the jets are broken and atomized to form a spray field with a certain range and size distribution. Further, the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/52
Inventor 康忠涛张新桥李清廉成鹏张建强
Owner NAT UNIV OF DEFENSE TECH
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