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.

Inactive Publication Date: 2008-06-18
MTU AERO ENGINES GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The main disadvantage of known casing treatments is that while they raise the surge limit, they also reduce compressor efficiency at the same time

Method used

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  • Recirculation structure for turbo chargers
  • Recirculation structure for turbo chargers
  • Recirculation structure for turbo chargers

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0017] The circuit arrangement 1 shown in FIG. 1 is installed in the casing 5 of a turbocompressor and can therefore be referred to as a "casing treatment". The direction of flow in the vaned main flow duct 9 is indicated on the left by an arrow, ie it flows from left to right. In the region shown, the flow impinges first on a guide vane ring 13 , then on a rotor vane ring 20 and finally on a guide vane ring 14 again. The radial outer contour 11 of the main flow duct 9 conforms to the inner shape of the casing 5 and, in order to show this clearly, is extended by a dotted line to the left and right of the actual figure. The static circulation structure 1 interacts with the rotor blade ring 20 and is mostly located axially in front of the rotor blade ring, that is to say upstream of the rotor blade ring. The annular chamber 29 forming the circulation structure 1 together with the guide element 37 is located radially outside and adjoins the main flow duct 9 and opens into the ma...

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PUM

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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.

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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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D11/08F04D29/54F01D1/00F01D5/14F04D27/02
CPCF01D5/145F04D27/0207F05D2220/40Y10S415/914F04D29/545F04D29/685F01D11/08F04D29/547F05B2220/40F04D29/321
Inventor 彼得·塞茨
Owner MTU AERO ENGINES GMBH
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