Interstage rotary detonation variable cycle turboshaft engine

Abstract

Interstage rotary detonation variable cycle turboshaft engine, the core machine, central chamber and power turbine are arranged in sequence inside the inner casing; the central chamber and power turbine are connected to the power shaft; a cooling flow path is formed between the inner casing and the outer casing , the inner casing and the outer wall of the central cavity form an interstage rotary detonation combustion chamber, and a mixing cooling chamber is formed between the central cavity and the power turbine; the splitter plate connects the inner casing to control the cooling bleed air; the oil circuit components are controlled and connected to the The interstage rotary detonation combustion chamber; the igniter is arranged in the interstage rotary detonation combustion chamber, and ignites the kerosene-air mixed gas entering the interstage rotary detonation combustion chamber to form rotary detonation combustion. Avoid the derivative problems caused by the rotating detonation combustion chamber instead of the turboshaft engine isobaric combustion chamber scheme, and take into account the high power demand of the helicopter during the take-off phase and the economic goal of the cruising phase, and solve the problem of using the existing rotating detonation turboshaft engine. When kerosene is used as fuel, it is difficult to detonate and burn directly.

Description

technical field [0001] The invention relates to the field of aeroengines, in particular to an interstage rotary detonation variable cycle turboshaft engine. Background technique [0002] Aviation gas turbine shaft engine (referred to as turboshaft engine) is the main power device of the helicopter, and its development level has a decisive influence on the comprehensive performance of the helicopter. In recent years, rotating detonation combustors have attracted extensive attention due to their advantages such as fast heat release rate, small entropy increase, and simultaneous heating and pressurization. Using the rotary detonation combustor to replace the isobaric combustor of the turboshaft engine can reduce the number of compressor stages and reduce the power consumption of the compression system, thereby improving the overall performance of the engine. However, using a rotating detonation combustor to replace the isobaric combustion chamber of a turboshaft engine will in...

AI Technical Summary

Problems solved by technology

However, the activity of kerosene is low, and it is difficult to detonate directly in the rotating detonation combustion chamber.

Images