Two aerospace turbofan engines

A turbofan engine, aerospace technology, applied in the direction of engine function, machine/engine, rocket engine device, etc., can solve the problems of uneconomical, affecting flight altitude and endurance, and high consumption, so as to save fuel and facilitate development and application , good effect of technology inheritance

Active Publication Date: 2016-08-10
葛明龙
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

However, this type of engine needs to consume much more high-concentration 90% hydrogen peroxide as an oxidant than aviation kerosene
It is not economical, but also affects flight altitude and endurance

Method used

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  • Two aerospace turbofan engines
  • Two aerospace turbofan engines
  • Two aerospace turbofan engines

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Embodiment Construction

[0035] figure 1 , figure 2 , image 3 , Figure 4 , Figure 5 , Figure 6 and Figure 7 It is the preferred embodiment of two kinds of aerospace turbofan engines of the present invention.

[0036] Such as figure 1 , image 3 , Figure 4 , Figure 5 and Figure 7As shown, the first aerospace turbofan engine of the present invention is composed of an inlet rich oxygen injection assembly 1, a slightly modified main structure 2, an afterburner middle part 3 and an afterburner outer ring part 4. The oxygen-enriched injection assembly 1 includes an oxygen-enriched tee pipe 10, an oxygen-enriched inlet pipe 11, an oxygen-enriched concentrator 12, and an oxygen-enriched injection ring 13. Minor changes to the main structure 2 include an outer wall of the air inlet 20 and a low-pressure compressor 21. , high-pressure compressor 22, main combustion chamber 23, high-pressure turbine 24, low-pressure turbine 25, center tail nozzle 26, outer duct outer wall 27, thickened outer ...

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Abstract

The invention relates to two aerospace turbofan engines. The first one is to feed rich oxygen in an intake way. The second one is to feed rich oxygen singly or synchronously in the intake way and an afterburner. Aiming at limited working height of an aviation turbofan engine, an intake way rich oxygen injecting module is arranged, a main structure of a traditional aviation turbofan engine is continuously used, and two sound cavity and separation regenerative cooling afterburners are adopted, so that the aviation turbofan engine can be changed to two aerospace turbofan engines capable of working at any height. The aerospace turbofan engine is an aerospace integral engine mainly adopting the traditional aviation turbofan engine, is excellent in technical succession, and facilitates development and application. The aerospace turbofan engine can propel an aircraft to fly at a 30-50 km height and a 3-5 M speed, or even more highly and more quickly, and is suitable for multiple aerospace integral aircrafts repeatedly used by multiple times.

Description

technical field [0001] The invention relates to two aerospace turbofan engines, belonging to an aerospace integrated engine that can fully utilize the oxygen in the atmosphere for combustion and work at any altitude. Background technique [0002] After more than 70 years of development, aviation gas turbine engines represented by aviation turbofan engines have reached a very high technical level. However, since the density of the atmosphere and the amount of oxygen decrease with increasing altitude, the thrust of such engines using air as the oxidant decreases, and the propelled aircraft cannot fly too high or too fast. Civil aviation airliners usually cruise at a speed of Mach 1 at an altitude of 10 km. Military aircraft can fly higher at supersonic speeds, but are limited in Mach number and altitude. [0003] In order to make the aircraft fly higher and faster, I proposed "two kinds of regenerative cooling afterburners with acoustic cavity and their application" (Chinese...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/58F02K9/42F02K9/60
CPCF02K9/42F02K9/60F23R3/58F02K3/11F02K9/78F02K9/972F23R3/20F23R3/42F23R3/60F23R7/00Y02E20/34F02K3/10F02K99/00F02K9/64F05D2260/20
Inventor 葛明龙
Owner 葛明龙
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