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Fuel nozzle suitable for wide-range ramjet engine

A technology of ramjet and fuel nozzle, which is applied in the direction of combustion chamber, controlled combustion, combustion method, etc. It can solve the problems of complicated system and difficulty in multiple injection methods, and achieve the effect of strengthening the mixing effect and facilitating replacement

Active Publication Date: 2022-04-05
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The conventional way is to set up different fuel injection pipelines. The disadvantage is that the system is complicated and it is difficult to take into account multiple injection methods at one fuel injection position.

Method used

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  • Fuel nozzle suitable for wide-range ramjet engine
  • Fuel nozzle suitable for wide-range ramjet engine
  • Fuel nozzle suitable for wide-range ramjet engine

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Embodiment Construction

[0035] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0036] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relationship between the components in a certain posture (as shown in the accompanying drawings). Relative positional relationship, movement conditions, etc., if the specific posture changes, the directional indication will also change accordingly.

[0037] In addition, in t...

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Abstract

The fuel nozzle suitable for the wide-range ramjet engine comprises a shell and an oil way controller, and a first injection opening and a second injection opening are formed in the shell; the oil path controller is provided with an oil-saving pipeline and a straight pipeline, the oil-saving pipeline is communicated with the first injection port and the second injection port through a first connecting channel and a second connecting channel, and the straight pipeline is communicated with the first injection port and the second injection port through the first connecting channel and the second connecting channel; and electromagnetic valves are arranged on the oil-saving pipeline, the straight pipeline, the first connecting channel and the second connecting channel. According to the fuel nozzle, small-hole injection, large-hole injection and large-hole and small-hole combined injection can be taken into consideration at one injection point on an engine, the injection pressure can be quickly adjusted, the thrust state of the engine can be quickly responded, the design difficulty of a fuel pipeline of the ramjet is greatly simplified, a fuel injection scheme is integrated and optimized, and the fuel injection efficiency is improved. And the engine can obtain a better fuel supply state in a wider Mach number range.

Description

technical field [0001] The invention relates to the technical field of ramjet injection, in particular to a fuel nozzle suitable for a wide range of ramjet engines. Background technique [0002] The flight envelope of the wide-range ramjet engine is wide, so the flow velocity and pressure of the airflow inside the engine vary greatly with the change of the flight Mach number. Therefore, during the entire flight, the fuel injection method has a great change. For higher flight Mach numbers, the fuel needs to be injected with small holes, and for higher flight Mach numbers, the fuel needs to be injected with large holes. Under different flight Mach numbers and states, the demand for fuel injection pressure is also different, but the change of the upstream fuel supply pressure of the fuel pipeline is relatively slow and cannot meet the rate of change of the fuel injection pressure of the aircraft during maneuvering flight need. When the engine needs to accelerate, a larger fu...

Claims

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Application Information

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IPC IPC(8): F23R3/38F23N1/00
Inventor 孙明波顾瑞李佩波安彬蔡尊董泽宇姚轶智王泰宇陈继凯李梦磊
Owner NAT UNIV OF DEFENSE TECH
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