Recirculation structure for turbo chargers

A technology of turbo compressor and circulation structure, which is applied to the components, mechanical equipment, engine components, etc. of the pumping device for elastic fluid, which can solve the problems of increasing the surge limit and reducing the efficiency of the compressor.
CN100395432CInactive Publication Date: 2008-06-18MTU AERO ENGINES GMBH
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Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Patents(China)
Current Assignee / Owner
MTU AERO ENGINES GMBH
Publication Date
2008-06-18
Estimated Expiration
Not applicable Β· inactive patent

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Abstract

Recirculation structure for turbocompressors, having a ring chamber which is arranged in the area of the free blade ends of a blade ring largely upstream of the latter and adjoins the main flow duct. A plurality of guiding elements are arranged in the ring chamber distributed over its circumference and are arranged and shaped in a fluidically advantageous manner with respect to the recirculation flow, with recesses provided in the leading and / or trailing area of the ring chamber. The side of the ring chamber which adjoins the contour of the main flow duct is open along its axial length as well as along its entire circumference, the free edges of the guiding elements being situated on the or close to the contour of the main flow duct.
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Description

technical field

[0001] The present invention relates to a cycle structure for a turbocompressor, and to an aeroengine and a static gas turbine. Background technique

[0002] Cycle configurations for turbocompressors have been known for some time and are commonly referred to by those skilled in the art as "casing treatment". Their main function is to increase the aerodynamically stable operating range of the compressor while shifting the so-called surge limit towards higher compressor pressures, ie towards higher compressor loads. A disturbance to a local flow separation and ultimately to compressor surge that occurs at both ends of the rotor blades of one or more compressor stages on the casing side and radially inward on the hub side occurs at the tips of the vanes because the aerodynamic loads are greatest in these areas. "Air particles" circulating at blade speed between the blade tips and having a reduced energy circulate into the main flow, thus increasing their energ...

Claims

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