Method of forming cooling holes

A method of forming cooling holes (20) in a gas turbine engine component (10). The method includes the steps of forming a hole (20) in the component (10) extending between a first surface (22) of the component (10) and a second surface (24) of the component (10) opposite the first surface (22) and s...

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Bibliographische Detailangaben
Hauptverfasser:	SCHEIDT, WILBUR DOUGLAS, ROCKSTROH, TODD JAY, ASH, CLARENCE ALBERT
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLADDING OR PLATING BY SOLDERING OR WELDING COMBINED OPERATIONS COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES OTHER WORKING OF METAL PERFORMING OPERATIONS SOLDERING OR UNSOLDERING STEAM ENGINES TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS WELDING WORKING BY LASER BEAM
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Beschreibung
Zusammenfassung:	A method of forming cooling holes (20) in a gas turbine engine component (10). The method includes the steps of forming a hole (20) in the component (10) extending between a first surface (22) of the component (10) and a second surface (24) of the component (10) opposite the first surface (22) and supplying pressurized air to the hole (20) from the second surface (24) of the component (10). The method also includes the step of sensing a parameter representative of air flow through the hole (20). Further, the method includes enlarging the hole (20) until the sensed parameter represents a preselected air flow rate through the hole (20).