Gas turbine engine sheet metal vane

Inactive Publication Date: 2011-04-07
PRATT & WHITNEY CANADA CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Furthermore, the grinding and polishing operations may compromise the quality of the butt welds.
Finally, the presence of a butt weld at the trailing edge of the airfoil does not allow altering the trailing edge section of the airfoil such as to provide for vane flow adjustment area.

Method used

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  • Gas turbine engine sheet metal vane
  • Gas turbine engine sheet metal vane
  • Gas turbine engine sheet metal vane

Examples

Experimental program
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Embodiment Construction

[0011]FIG. 1 illustrates a turbofan gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a multistage compressor 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.

[0012]As well know in the art, the compressor and the turbine sections 14 and 18 are provided with respective arrays of stator vanes located immediately upstream of an associated rotor so as to direct the gases onto rotor blades extending from the rotor disc. FIGS. 2a and 2b show a cross-sectional view of one of such stator vanes. The vane 20 comprises a hollow airfoil 22 having a sheet metal body or skin extending in a chordwise direction between a leading edge 24 and a trailing edge 26. The airfoil 22 may be formed f...

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Abstract

A gas turbine engine stator vane has a sheet metal body with a pressure surface and a suction surface extending chordwise from a leading edge to a trailing edge. The sheet metal body has opposed pressure and suction side trailing end portions that meet at a joint upstream from the trailing edge of the airfoil. The pressure and suction surfaces of the sheet metal body are parallel to one another between the joint and the trailing edge, thereby forming a straight non-tapering trailing edge section from the joint to the trailing edge of the airfoil.

Description

TECHNICAL FIELD[0001]The application relates generally to gas turbine engines and, more particularly, to gas turbine engine vanes.BACKGROUND OF THE ART[0002]Sheet metal vanes usually have an airfoil tapering from a rounded leading edge to a sharp trailing edge. The airfoil is typically formed from a suction side sheet and a pressure side sheet welded together at the airfoil leading and trailing edges by butt welds. The butt welds need to be ground to the parent sheet material and polished to obtain smooth airfoil leading and trailing edges. Accordingly, extra manufacturing operations must be performed in order to obtain adequate aerodynamic surface finishes. Furthermore, the grinding and polishing operations may compromise the quality of the butt welds. Finally, the presence of a butt weld at the trailing edge of the airfoil does not allow altering the trailing edge section of the airfoil such as to provide for vane flow adjustment area.SUMMARY[0003]In one aspect, there is provided ...

Claims

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Application Information

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IPC IPC(8): F01D9/02
CPCF01D9/02F05D2240/122F05D2230/232F05D2230/50F05D2240/12F05D2240/304
InventorDUROCHER, ERICFOURNIER, JEAN
OwnerPRATT & WHITNEY CANADA CORP