Countering laser shock peening induced airfoil twist using shot peening

A gas turbine engine blade is laser shock peened by laser shock peening a thin airfoil of the blade, forming a laser shock induced twist in the airfoil, and shot peening a portion of the airfoil to counter the laser shock induced twist in the airfoil. The shot peening may be performed before or afte...

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Hauptverfasser:	ROCKSTROH TODD JAY, BARBE ROGER OWEN, MANNAVA SEETHA RAMAIAH
Format:	Patent
Sprache:	eng
Schlagworte:	ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS GRINDING HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS POLISHING STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION TECHNICAL SUBJECTS COVERED BY FORMER USPC TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine blade is laser shock peened by laser shock peening a thin airfoil of the blade, forming a laser shock induced twist in the airfoil, and shot peening a portion of the airfoil to counter the laser shock induced twist in the airfoil. The shot peening may be performed before or after the laser shock peening. The shot peening may be applied over a laser shock peened surface formed by the laser shock peening. The shot peening may be performed asymmetrically on asymmetrically shot peened pressure and suction side areas of pressure and suction sides, respectively, of the airfoil. A shot peened patch near a blade tip may be formed on one of pressure and suction sides of the airfoil wherein the airfoil extends radially outwardly from a blade platform to the blade tip of the blade.