A High Thrust-to-Weight Ratio Gas Turbine Generator for Unmanned Aerial Vehicles

Abstract

The invention belongs to the technical field of gas turbine engines, and relates to a high thrust-to-weight ratio gas turbine generator suitable for unmanned aerial vehicles, which includes a rotating casing and a diagonal flow compressor impeller arranged in the rotating casing, a rotating combustion chamber, a centripetal The trailing edge of each blade of the turbine and the oblique flow compressor impeller is wedge-shaped without any backsweep and has a thickness, and radial fuel injection holes are provided on the trailing edge of at least part of the blades of the oblique flow compressor impeller, and each radial fuel injection The hole is in fluid communication with the fuel supply passage provided in the hollow rotating shaft. The rotary combustion chamber includes an inlet section located upstream and a step-shaped sudden expansion section located downstream of the inlet section. An ignition device is arranged on the inner wall of the inlet section of the rotary combustion chamber. . The high thrust-to-weight ratio gas turbine generator of the present invention maintains a high level of efficiency at both low and high speeds, and has lower fuel consumption at high Mach numbers, and is suitable for power requirements of unmanned aerial vehicles with a wide range of flight envelopes.

Description

technical field [0001] The invention relates to the technical field of gas turbine engines, relates to a gas turbine generator, in particular to a gas turbine generator with a high thrust-to-weight ratio suitable for unmanned aerial vehicles, which satisfies the power requirements of multi-working conditions of unmanned aerial vehicles, and simultaneously Features of high efficiency and low fuel consumption. Background technique [0002] Unmanned aerial vehicles are the fastest growing field in the aerospace industry today. In existing UAVs, piston engines are often used because the thermal efficiency of small gas turbine engines decreases rapidly as the size of the engine decreases. As the operating range of UAVs expands from high subsonic to supersonic speeds, engines are required to have high thrust-to-weight ratios (the ratio of thrust to weight). Because small gas turbines have a higher thrust-to-weight ratio than piston engines. Also, at high flight Mach numbers, sm...

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