A gas turbine with embedded blades

Abstract

The invention provides a gas turbine with embedded blades. A turbine box and a supporting cylinder are coaxially arranged, and a wheel hub is coaxially arranged in the turbine box and can rotate relative to the turbine box. Gas compressor movable blades are arranged on the side, close to a gas compressor air inlet, of the wheel hub, and gas compressor fixed blades are arranged on the position, corresponding to the gas compressor movable blades, of the turbine box. Turbine movable blades are arranged on the side, close to a turbine air outlet, of the wheel hub, and turbine fixed blades are arranged on the position, corresponding to the turbine movable blades, of the turbine box. A combustion chamber is an annular combustion chamber and fixed to the periphery of the turbine box. According to the gas turbine with the embedded blades, the two ends of the gas compressor blades and the turbine blades are all fixed, leakage flow can be eliminated, and efficiency of a gas compressor and a turbine body is improved; the blades with the sizes being larger than cantilever type blades can be adopted, the single-stage compression ratio of the gas compressor is improved, the capacity of single-stage working of the turbine body is improved, and the weight of the blades is reduced; and performance of the gas compressor and the turbine body is improved.

Description

technical field [0001] The invention relates to the technical field of thrusters, in particular to a gas turbine with embedded blades. Background technique [0002] Gas turbines are widely used in industries such as aviation and electric power. Industrial gas turbines require high efficiency, stable and safe operation; aviation gas turbines, as the heart of aircraft, play an important role in the development of aircraft. The continuous improvement of modern aircraft technical and tactical indicators has put forward higher requirements for aero-engines: the requirements for engine It has high thrust-to-weight ratio, high efficiency, large flow, low fuel consumption and wide stable working range. The compressor and the turbine are the two core components of a gas turbine, and the traditional design methods include axial flow and centrifugal. The advantage of the axial flow compressor is that the flow rate is large, but the disadvantage is that the single-stage pressure ratio...

AI Technical Summary

Problems solved by technology

The advantage of the axial flow compressor is that the flow rate is large, but the disadvantage is that the single-stage pressure ratio is small. Therefore, a multi-stage axial flow compressor design is required to increase the pressure ratio, resulting in high manufacturing costs, complex structures, and device weight. Centrifugal compressors The advantage of the machine is that the single-stage pressure ratio is high, and the disadvantage is that the flow area is small and the flow rate is small.

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