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1. (WO2013163037) GAS TURBINE ENGINE AIRFOIL IMPINGEMENT COOLING

Pub. No.:    WO/2013/163037    International Application No.:    PCT/US2013/037387
Publication Date: Fri Nov 01 00:59:59 CET 2013 International Filing Date: Sat Apr 20 01:59:59 CEST 2013
IPC: F01D 5/12
F01D 5/18
F01D 9/00
F02C 7/12
Applicants: UNITED TECHNOLOGIES CORPORATION
Inventors: PROPHETER-HINCKLEY, Tracy A.
ZELESKY, Mark F.
MONGILLO, JR., Dominic J.
DEVORE, Matthew A.
GAUTSCHI, Steven Bruce
FISK, Benjamin T.
Title: GAS TURBINE ENGINE AIRFOIL IMPINGEMENT COOLING
Abstract:
An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil.