A hypersonic vehicle and its propulsion system

Abstract

The invention provides a new concept hypersonic flight vehicle propulsion system layout. The new concept hypersonic flight vehicle propulsion system layout comprises a front end rotating shaft and a rear end rotating shaft, wherein the front end rotating shaft sequentially supports a core gas compressor and a fuel gas turbine; the rear end rotating shaft supports a medium turbine; and a clutch mechanism controlling connection or disconnection of the front end rotating shaft and the rear end rotating shaft is arranged between the front end rotating shaft and the rear end rotating shaft. The newconcept hypersonic flight vehicle propulsion system layout further comprises a control device and a pre-cooled closed circulation system, wherein when a value is higher than a flight state setting value, the control device connects the clutch mechanism and controls the closure of a fuel gas turbine runner; when the value is lower than the flight state setting value, the control device disconnectsthe clutch mechanism and controls the opening of the fuel gas turbine runner; the pre-cooled closed circulation system communicates with the medium turbine; and when the clutch mechanism is connected, the pre-cooled closed circulation system drives the medium turbine to work. According to the new concept hypersonic flight vehicle propulsion system layout, the rotating shafts are arranged as sectional control structures, and the switchover of the working conditions of the fuel gas turbine and the medium turbine is controlled under different connecting states of the rotating shafts, and the pre-cooled closed circulation system works only at high mach numbers, and the economical efficiency is improved, and the operation performance of hypersonic flight vehicles is optimized. The invention also provides a new concept hypersonic flight vehicle.

Description

[0001] This application claims the priority of the Chinese patent application with the application number 201810744376.1 and the invention title "High Speed ​​Aircraft and Turbojet Engine" submitted to the China Patent Office on July 09, 2018, the entire contents of which are incorporated by reference in this application. technical field [0002] The present invention relates to the technical field of hypersonic aircraft, and more specifically, relates to a hypersonic aircraft and its propulsion system. Background technique [0003] The development of hypersonic aircraft is an important direction of aircraft development. In terms of military use, the implementation of global strategic strikes and time-sensitive attacks will inevitably require hypersonic aircraft; in terms of civilian use, the development of hypersonic aircraft will greatly increase the speed of transportation, which will bring great economic benefits to the civil air transport industry. Human beings bring gr...

AI Technical Summary

Problems solved by technology

However, in the existing hypersonic vehicle power system with strong pre-cooling mode, the pre-cooling circulation system needs to work all the time when flying at a low Mach number. Under most working conditions, the amount of fuel required for cooling is much greater than the amount of fuel required for combustion, so that the fuel used as a cold source for cooling can only be discharged directly, resulting in a huge waste of fuel

When flying at low speed, the fuel waste is serious and the economy is poor, which limits its application prospect

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