Axial flow machine having an asymmetrical compressor inlet guide baffle

Inactive Publication Date: 2011-07-07
MTU AERO ENGINES GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

Another advantageous specific embodiment of the present invention provides that one individual control be provided in each case for some or all of the guide vanes. This makes it possible to individually correct in the case of altered flow conditions.

Problems solved by technology

The asymmetry of the incident flow of the first compressor stage can cause problems related thereto, which can lead to a partial flow separation at this vane stage, along with the surging and efficiency loss resulting therefrom.

Method used

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  • Axial flow machine having an asymmetrical compressor inlet guide baffle
  • Axial flow machine having an asymmetrical compressor inlet guide baffle
  • Axial flow machine having an asymmetrical compressor inlet guide baffle

Examples

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Embodiment Construction

FIG. 1 shows a schematic representation of a developed view of an inlet guide baffle 20 in accordance with the present invention having multiple profiles, i.e., of individual profiling of each individual vane of the inlet guide baffle. In this manner, the vanes are adapted to the variable circumferentially asymmetric angle of incidence of the inlet guide baffle. This asymmetrical incident flow is caused by the asymmetric air inlet 10, shown schematically. The inlet guide baffle according to the present invention produces a constant outflow angle over the entire periphery, and substantially circumferentially symmetrical inlet conditions are passed onto the first compressor stage. This leads to an improved stability and an enhanced efficiency of the compressor.

FIG. 2 shows a schematic representation of a developed view of an inlet guide baffle according to the related art, having a circumferentially asymmetrical incident flow that is caused by an asymmetric air inlet. Here, the extrem...

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Abstract

An axial flow machine having an asymmetrical air inlet and, downstream therefrom, a compressor having an inlet guide baffle composed of guide vanes is characterized in that at least some of the guide vanes of the inlet guide baffle have a vane profile and/or an angle of attack that deviate(s) from the remaining guide vanes. The inlet flow angle of the first compressor stage is hereby evened out circumferentially symmetrically. This is accomplished in that the different inlet angles resulting at various circumferential positions of the inlet guide baffle due to the asymmetry of the air inlet, are influenced by selective profiling and/or by selectively modifying the angle of incidence of individual guide vanes in such a way that a circumferentially symmetrical outflow angle from the inlet vane ring results. In this way, the circumferential distortions caused by the asymmetrical air inlet are minimized and, thus, circumferentially symmetrical inlet conditions are passed onto the first compressor stage, which results in an improved stability and an enhanced efficiency of the compressor.

Description

The present invention relates to an axial flow machine having an asymmetrical air inlet and, directly downstream therefrom, a compressor having an inlet guide baffle composed of guide vanes.BACKGROUNDSuch axial flow machines having an asymmetrical air inlet are used as core engines in the case of turboprop or helicopter engines, for example. The asymmetry of the incident flow of the first compressor stage can cause problems related thereto, which can lead to a partial flow separation at this vane stage, along with the surging and efficiency loss resulting therefrom.For stationary gas turbines, the European Patent Application EP 1 508 669 A1 teaches that, by forming different profile curvatures of at least two inlet guide vanes, it is possible to increase the efficiency of a stationary gas turbine. The increase in the efficiency is achieved by reducing the flow losses at the inlet guide baffle.SUMMARY OF THE INVENTIONIt is an object of the present invention to avoid the disadvantages...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F04D29/54
CPCF04D29/542F04D29/544
Inventor ELORZA GOMEZ, SERGIOHALCOUSSIS, ALEXANDER
Owner MTU AERO ENGINES GMBH
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