METHODS AND APPARATUS FOR COOLING GAS TURBINE ENGINE BLADE TIPS

A turbine (20) for a gas turbine engine (10) including a turbine nozzle assembly (42) that facilitates reducing an operating temperature of rotor blades (56) in a cost-effective and reliable manner is described. Each rotor blade includes a tip that rotates in close proximity to a shroud (80) that ex...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	BEACOCK, ROBERT, JOHN, RIECK, HAROLD, PAUL, JR, ERDMANN, OMER, DUANE, ATHANS, ROBERT, EDWARD
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 INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING 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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A turbine (20) for a gas turbine engine (10) including a turbine nozzle assembly (42) that facilitates reducing an operating temperature of rotor blades (56) in a cost-effective and reliable manner is described. Each rotor blade includes a tip that rotates in close proximity to a shroud (80) that extends circumferentially around the rotor assembly (40). The turbine nozzle assembly includes a plurality of turbine vane segments (92) that channel combustion gases to downstream rotor blades. Each turbine vane segment extends radially outward from an inner platform (96) and includes a tip (100), a root (102), and a body (94) that extends therebetween . The turbine vane segment tip is formed integrally with an outer band (150) that mounts the vane segments within the gas turbine engine. The outer band is in flow communication with a cooling fluid source, and includes at least one opening (158). L'invention concerne une turbine (20) de moteur (10) à turbine à gaz comprenant un ensemble (42) distributeur de turbine permettant de réduire la température d'exploitation des aubes (56) de rotor de manière rentable et fiable. Chaque aube de rotor comprend une pointe tournant à proximité d'un anneau de renforcement (80) s'étendant de manière circulaire autour de l'ensemble rotor (40). Le distributeur de turbine comprend une pluralité de segments (92) de palette de turbine acheminant les gaz de combustion jusqu'aux aubes de rotor en aval. Chaque segment de palette de turbine s'étend radialement vers l'extérieur à partir d'une plate-forme intérieure (96) et comprend une pointe (100), une base (102), et un corps (94) s'étendant entre les deux. La pointe du segment de palette de turbine est intégrée à une bande extérieure (150) permettant de monter les segments de palette dans le moteur à turbine à gaz. La bande extérieure est en communication fluidique avec une source de fluide de refroidissement, et comprend au moins une ouverture (158).