A design method of a multi-channel parallel three-power combined engine

Abstract

A design method of a multi-channel parallel three-power combined engine belongs to the field of combined engines, and comprises the following steps of 1) making overall performance requirements according to a flight task, determining the capture area of an air inlet channel, and obtaining a three-dimensional inward rotation air inlet channel through streamline tracking; 2) calculating inlet and outlet parameters of the scramjet combustion chamber, and designing a scramjet channel and the scramjet combustion chamber; 3) designing an upper molded surface and a lower adjusting plate of the exhaust nozzle; 4) arranging turbine channels, turbine engines and turbine channel splitter plates at openings in the two side walls of the three-dimensional internal rotation air inlet channel according tothe flow requirements of the engines at the Ma0-2 stages; 5) calculating an injection rocket-sub-combustion channel maximum flow demand based on the thrust demands of the working state of the Ma2-3 rocket engine and the working state of the Ma3-4.5 sub-combustion chamber, so that an inlet of the injection rocket-sub-combustion channel, the rocket engine with corresponding size and the injection rocket-sub-combustion channel splitter plate are arranged. According to the invention, the higher low-speed climbing performance and high-speed cruising performance can be provided while a thrust gap can be effectively spanned.

Description

technical field [0001] The invention relates to the field of combined engines, in particular to a design method for a multi-channel parallel three-power combined engine. Background technique [0002] For a century, people have promoted the development of hypersonic vehicles under the ideal of flying "higher, faster and farther". As early as the early 1970s, high-altitude reconnaissance aircraft with a Mach number of 3 appeared, and in the mid-1970s, civil aviation airliners with a Mach number of 2 began to travel to and from Europe and the United States. In recent years, the United States, the European Union, Russia, Japan and other countries and international Organizations are accelerating various hypersonic flight technology research projects, aiming to pursue ground takeoff, cross-speed domain (Ma0~6+), and reusable hypersonic aircraft. [0003] Existing aerospace power is mainly turbine, ramjet and rocket engines, among which the best working range of turbine engine is ...

AI Technical Summary

Problems solved by technology

[0004] From a technical point of view, the core of achieving hypersonic flight lies in the combined power technology. The comparison shows that there are still the following main problems in the field of combined engines in China: 1. The thrust trap of multi-channel combined power, the working speed range of turbine engines and ramjet engines is currently There is still a gap, and it is difficult to achieve the problem of thrust convergence, and it is currently a more reasonable solution to use the power of ejection rockets to fill the insufficient thrust of the transfer stage; Dual-mode work is still facing great challenges and is far away from engineering practice; 3. At present, most of the combined engine schemes in China adopt the dual-channel form, so the working pressure assigned to each channel is relatively high. The self-starting capability is maintained under the premise of the chamber inlet speed requirement, and the thrust of the turbine is insufficient at low speed

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