LASER SHOCK PEENING INTEGRALLY BLADED ROTOR BLADE EDGES

A method for laser shock peening rotor blade (108) leading and trailing edge s (LE, TE) of gas turbine engine integrally bladed rotors and disks that are not blocked by other rows of blades. The method includes continuously firing a stationary laser beam (102), which repeatable pulses between relati...

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Bibliographische Detailangaben
Hauptverfasser:	COWIE, WILLIAM D, ZISSON, JAMES R, NUSSBAUM, JEFFREY H, MANNAVA, SEETHARAMAIAH, MCDANIEL, ALBERT E, ASSA, ABRAHAM S, COX, ANDREA G. M
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	BLASTING CHEMISTRY CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ENGINE PLANTS IN GENERAL GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUSMETALS OR ALLOYS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MAKING METAL MALLEABLE BY DECARBURISATION, TEMPERING OR OTHERTREATMENTS MECHANICAL ENGINEERING METALLURGY METALLURGY OF IRON MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	A method for laser shock peening rotor blade (108) leading and trailing edge s (LE, TE) of gas turbine engine integrally bladed rotors and disks that are not blocked by other rows of blades. The method includes continuously firing a stationary laser beam (102), which repeatable pulses between relatively constant periods, along at least a portion of leading or trailing edges (LE, TE) of the blade (108), with the laser beam (102) aimed at an oblique angle (110) with respect to a surface of the edge such that laser pulses form overlapping elliptical shaped laser spots (60). In the exemplary embodiment of the invention, the elliptical shaped laser spots (60) have an overlap of about 50% and are on the order of 11.7 mm by 4 mm in diameter. Another metho d is for laser shock peening rotor blade leading and trailing edges (LE, TE) of g as turbine engine integrally bladed rotors and disks that are blocked by other rows of blades. The method includes continuously firing the stationary laser beam (102), whi ch repeatable pulses between relatively constant periods, along at least a portion of leading or trailing edges (LE, TE) of the blade (108), with the laser beam (102) compoundly angled such that it is aimed at a first oblique angle (110) with respect to a surface of the edge and at a second oblique angle(114) with respect to an axis about which the rotor is circumscribed. Laser pulses form the elliptical shaped laser spots (60) that are angled from the leading edge (LE) radially inwardly towards th e axis. In the exemplary embodiment, the elliptical shaped laser spots (60) have an overlap of about 50%.