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Static guide vane with internal hollow channels

a technology of static guide and hollow channel, which is applied in the direction of stators, machines/engines, liquid fuel engines, etc., can solve the problems of undesired and achieve the effect of reducing the weight of the van

Inactive Publication Date: 2015-09-10
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent text describes a gas turbine engine with a fan section and a compressor section. The fan section includes a fan rotor and a row of static guide vanes. The vanes have channels in their airfoil to make them lighter. A cover closes off the channels and provides a portion of the airfoil. The technical effect of this design is to improve the performance and efficiency of the gas turbine engine.

Problems solved by technology

As the guide vanes have become structural components and have become larger, their weight has become undesirably large.

Method used

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  • Static guide vane with internal hollow channels
  • Static guide vane with internal hollow channels
  • Static guide vane with internal hollow channels

Examples

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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 flow path B in a bypass duct defined within a nacelle 15, while the compressor section 24 drives air along a core flow path C 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 hig...

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PUM

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Abstract

A static guide vane for use in a fan section of a gas turbine engine includes an outer platform and an inner platform. The inner and outer platforms are connected by an airfoil. The airfoil have channels extending into a main body of the airfoil to reduce the weight of the vane. A cover closes off the channels with the cover providing a portion of the airfoil.

Description

BACKGROUND OF THE INVENTION[0001]This application relates to a static guide vane which is provided with hollow channels to reduce weight.[0002]Gas turbine engines typically include a fan delivering air into a compressor. The air is compressed and passed into a combustor section where it is mixed with fuel and ignited. Products of the combustion pass downstream over turbine rotors, driving them to rotate. The turbine rotors, in turn, drive compressor and fan rotors.[0003]Traditionally, a low pressure turbine would drive a low pressure compressor and the fan as one spool. Thus, all three components rotated at a common speed. More recently, it has been proposed to include a gear reduction between the fan and the low pressure turbine. With the use of the gear reduction, the fan can rotate at a slower speed than the low pressure turbine or the low pressure compressor.[0004]As fan speed has decreased, the diameter of the fan could be increased. The fan typically also delivers air into a b...

Claims

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Application Information

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IPC IPC(8): F01D9/02F01D1/02
CPCF01D1/02F01D9/02F01D5/147F01D9/041F05D2230/23F05D2240/12Y02T50/60
Inventor POPE, ANDREWYUDICHAK, DAVID J.LUCASHU, JOHN P.REINHARDT, GREGORY E.DITOMASSO, JOHN C.CONNER, STEVEN L.KLINETOB, CARL BRIANLEROUX, JASON
Owner UNITED TECH CORP