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Root bow geometry for airfoil shaped vane

a technology of airfoil and geometry, applied in the field of airfoils, can solve problems such as reducing the efficiency of airfoil, and achieve the effect of reducing secondary flow losses

Inactive Publication Date: 2014-03-06
MTU AERO ENGINES GMBH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This patent is for a new type of vane used in a gas flow duct. The vane has a suction side and a pressure side that extend from its leading edge to its trailing edge. It has a chord line that connects the leading edge to the midpoint of the vane, a radial line that connects the tip of the vane to the assembly, and a bowing region that reduces secondary flow losses. The angle between the suction side surface and the inner diameter endwall is greater than 70 degrees. The vane assembly includes an inner diameter endwall and an outer diameter endwall, and a plurality of vanes arranged between them. Each vane has the same design as described above. The technical effect of this invention is to improve the efficiency of the gas flow duct by reducing secondary flow losses.

Problems solved by technology

The sharpness of the junction between the vane and the inner diameter wall increases secondary flow losses within the system, thereby reducing the efficiency of the airfoil.

Method used

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  • Root bow geometry for airfoil shaped vane
  • Root bow geometry for airfoil shaped vane
  • Root bow geometry for airfoil shaped vane

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Embodiment Construction

[0031]FIG. 1 schematically illustrates a gas turbine engine 20. The gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28. Alternative engines might include an augmentor section (not shown) among other systems or features. The fan section 22 drives air along a bypass flowpath while the compressor section 24 drives air along a core flowpath for compression and communication into the combustor section 26 then expansion through the turbine section 28. Although depicted as a turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures.

[0032]The engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engin...

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Abstract

A vane assembly used for controlling a turning gas flow includes multiple vanes, each of which is bowed toward a pressure side of the vane at the root of the vane.

Description

TECHNICAL FIELD[0001]The present disclosure relates generally to airfoils for controlling a turning gas flow, and more particularly to a geometry for an airfoil shaped vane.BACKGROUND OF THE INVENTION[0002]Power generation systems that incorporate a compressor, a combustor, and a turbine arranged in a flow series from an inlet to an exhaust are typically referred to as gas turbine engines. The compressor compresses air from the inlet, the air is mixed with fuel in a combustor and ignited to produce combustion gasses that drive the turbine and are expelled at the exhaust. The gas turbine engine often includes a duct portion, connecting a high pressure turbine to a low pressure turbine. The duct portion includes a vane assembly with multiple airfoil shaped vanes that are arranged circumferentially about the duct and impart desirable flow characteristics onto the gas flowing through the duct. Similar vane assemblies and airfoil shaped vanes are used in other gas flow control applicatio...

Claims

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Application Information

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IPC IPC(8): F01D9/02F01D9/04
CPCF01D5/141F01D9/041F01D5/145
Inventor JUREK, RENEE J.PRAISNER, THOMAS J.HOEGER, MARTIN
Owner MTU AERO ENGINES GMBH