Wake flow impact generator of circumferential multiple partitions

Abstract

The invention relates to a wake flow impact generator of circumferential multiple partitions, which is applied to the inlet guide vanes of an axial compressor, and comprises a casing, a wheel hub, four torrent areas with guide vanes and four buffer areas without guide vanes. In the design, mobile loss of strong unordered unsteady multi-eddy structure in the compressor is taken into consideration. When the number and circumferential distributing forms of inlet guide vanes are arranged reasonably, the multi-frequency wakes of IGV can generate beneficial unsteady coupled exciting function for the downstream rotor flow field. Compared with the wake current impact scheme with the inlet guide vanes distributed uniformly and circumferentially, the wake current impact plan with circumferential multiple partitions, maintaining the beneficial high frequency exciting signal, introduces appropriate low frequency square exciting signal and other beneficial sub-frequency exciting signals so that the wakes of the guide vanes are easy to generate the coupled exciting function with various eddies in the compressor, the adiabatic efficiency of the compressor is obviously improved, the total voltage rise of the compressor is improved, and the stability margin of the compressor is expanded.

Description

technical field [0001] The invention relates to a wake impingement generator with multiple partitions in the circumferential direction of an inlet guide vane, which can improve the thermal insulation efficiency of a compressor used in an aero-engine, and at the same time slightly increase the total pressure rise and stability margin of the compressor. Background technique [0002] At present, the impeller machinery industry has become a pillar of national economy and military power, and plays a leading role in national strategy. But those in the field know that there are strong and complex unsteady flows inside the compressor of an aeroengine. On the one hand, the mutual interference of the rotor / stator blades forms the unique unsteadiness in the compressor; on the other hand, there are various vortex structures and abundant secondary flows in the internal flow of the compressor. This strong and disordered unsteady flow greatly limits the further improvement of compressor p...

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Problems solved by technology

[0004] However, the above-mentioned acoustic excitation and synthetic jet methods are very difficult in practical engineering applications; although the treatment of the casing can greatly improve the surge margin of the compressor, it is often at the expense of reducing the adiabatic efficiency of the compressor; The impingement generator has slightly improved the total pressure rise, efficiency and stall margin of the compressor in the experiment, but the improvement of the compressor efficiency is still very small

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