A Multistage Axial Flow Compressor with Rotor-Stator Combined with Self-Adaptive Adjustment

Abstract

The invention relates to a multi-stage axial flow compressor, and discloses a multi-stage axial flow compressor with combined adjustment of rotor and stator blades, which includes target rotor blades, downstream stator blades, downstream stator blade discs, target rotor blade discs and an engine. Rotor disc drainage cavity structure with synchronous rotation of the shaft; through the guide vanes in the jet gas guidance cavity, the drainage gas has the same dragging speed as the rotor, and further acts on the target rotor blade end area and blade tip through the jet groove. According to the characteristics of step-by-step pressurization of multi-stage compressors, adaptive suction and wall jets are formed in the combined suction slot of the downstream stator and the target rotor end area and blade tip, effectively suppressing the three-dimensional corner area of ​​the rotor stator of the multi-stage compressor The separated flow improves the rotor tip leakage flow, effectively prevents the rotational stall caused by the separation of the three-dimensional corner area and the leading edge overflow and trailing edge backflow at the tip, enhances the rotational stability of the target rotor, and improves the margin , broaden the range of stable working conditions of the compressor.

Description

technical field [0001] The invention relates to the field of multi-stage axial-flow compressors, in particular to a multi-stage axial-flow compressor with rotor-stator blades combined with self-adaptive adjustment. Background technique [0002] The compressor is the core component of the aviation gas turbine engine. It is composed of multi-stage rotors and stators arranged in a staggered order. Its function is to increase the gas pressure rise; in the flow inside the compressor, due to the small flow space, the reverse pressure of the fluid The gradient effect is strong, and it has a complex vortex structure; the corner separation structure located at the stator end zone and the leakage flow structure located at the rotor tip are the main secondary flow structures inside the compressor, and are the main causes of flow loss and blockage inside the compressor. The source has a vital impact on the performance of the compressor's pressure ratio, efficiency, and margin. In severe...

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Problems solved by technology

[0002] The compressor is the core component of the aviation gas turbine engine. It is composed of multi-stage rotors and stators arranged in a staggered order. Its function is to increase the gas pressure rise; in the flow inside the compressor, due to the small flow space, the reverse pressure of the fluid The gradient effect is strong, and it has a complex vortex structure; the corner separation structure located at the stator end zone and the leakage flow structure located at the rotor tip are the main secondary flow structures inside the compressor, and are the main causes of flow loss and blockage inside the compressor. The source has a vital impact on the performance of the compressor's pressure ratio, efficiency, and margin. In severe cases, it will cause the stall and surge of the compressor, which will bring disastrous consequences; after decades of research, many scientific research works Researchers have had a deep understanding of the corner separation flow and tip leakage flow of the compressor, but due to the limitation of space and the complexity of the flow, it has not been well realized according to the existing research results. Effective control of the flow in the machine; especially by making full use of the characteristics of step-by-step pressurization of the flow in the compressor, through a certain self-circulation adjustment mechanism, while using and improving the flow structure that is not conducive to performance, to achieve the purpose of improving the performance of the compressor

[0003] For the rotor-stator end zone of the compressor, the flow congestion caused by the separation / stall of the three-dimensional angular zone makes the performance of the compressor drop sharply; Larger and wider effective working range; however, with the increase of compressor load, the degree of three-dimensional angular separation increases sharply, and the range of effective working angle of attack decreases sharply; at present, the three-dimensional angular separation and stall The flow control technology in the field can be divided into two categories: active control technology and passive control technology in terms of whether additional energy is introduced: active control technology mainly includes plasma excitation, boundary layer blowing and suction technology, synthetic jet, etc.; passive control technology mainly includes Vortex generators, wing knives, end wall shapes, etc.; the boundary layer suction technology in the active control technology has the characteristics of a wide range of applications and obvious benefits, but it requires additional energy and is not easy to implement in engineering; the existing traditional passive control technology , not self-adaptive, and the range of effective working conditions is often limited, failing to solve the problem of corner separation of the next generation of high-load compressors in engineering

[0004] For the compressor rotor tip, the tip leakage flow has an important influence on the stable working state of the compressor. The overflow of the leading edge of the rotor tip and the reverse flow of the trailing edge are the two precursors of the stall of the compressor. Reasonable introduction of the jet at the tip of the rotor can effectively improve the leakage flow of the rotor tip, increase the stall margin of the rotor, and achieve a better stability expansion effect; the traditional air blowing technology of the rotor tip is mostly active control, which requires additional energy to be introduced. Conducive to engineering realization; there is also a scheme of using a self-circulating casing, but its jet outlets are distributed in an intermittent array along the circumferential direction, which cannot form a uniform jet flow in the circumferential direction, which interferes with the rotation stability

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