A TURBINE ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF MANUFACTURING THE SAME

A turbine assembly is provided. A turbine assembly includes at least one stator assembly (32, 36, 40) including a radially inner band (56) and at least one stator vane extending radially outward from the inner band, the stator vane includes an airfoil (53) including a root portion (284) adjacent the...

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Bibliographische Detailangaben
Hauptverfasser:	BURTON, SCOTT ANDREW, LEE, CHING-PANG, BEACOCK, ROBERT JOHN, MACHNAIM, JOSEPH, CHERRY, DAVID GLENN, PRAKASH, CHANDER, CARSON, SCOTT MICHAEL
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES 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 WEAPONS
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Beschreibung
Zusammenfassung:	A turbine assembly is provided. A turbine assembly includes at least one stator assembly (32, 36, 40) including a radially inner band (56) and at least one stator vane extending radially outward from the inner band, the stator vane includes an airfoil (53) including a root portion (284) adjacent the inner band and a tip portion (282), the airfoil further includes at least one lean directional change (128, 174, 176) defined between the root portion and the tip portion. A turbine assembly further includes at least one turbine blade assembly including at least one rotor blade (85), the blade assembly coupled in flow communication with the stator assembly (32) such that an axial spacing is defined therebetween, wherein the axial spacing (334) defined adjacent to the at least one lean directional change (128, 174, 176) is wider than the axial spacing defined adjacent to the root portion