TRANSITION PIECE FOR A GAS TURBINE ENGINE

A combustion system including a transition piece (44) and method of forming the transition piece (44) using a cast nickel-based superalloy is provided. The transition piece (44) includes a body (68) defining a flowpath (72) and enclosure (70), the body (68) having a circular inlet section (60) for r...

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Bibliographische Detailangaben
Hauptverfasser:	Peck, Arthur, McMahan, Kevin Weston, Vlessis, Nicholas
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING CASTING CASTING OF METALS CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES ENGINE PLANTS IN GENERAL FOUNDRY MOULDING HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS POWDER METALLURGY STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A combustion system including a transition piece (44) and method of forming the transition piece (44) using a cast nickel-based superalloy is provided. The transition piece (44) includes a body (68) defining a flowpath (72) and enclosure (70), the body (68) having a circular inlet section (60) for receiving combustion product from the combustor (40) and an outlet end (62) for flowing the combustor products into a first stage nozzle of a gas turbine. The transition piece (44) comprises a one-piece single casting construction of the circular inlet section (60), the body (68), and the outlet end (62). The transition piece (44) is formed from a nickel-based superalloy. The transition piece has a thick-to-thin ratio of wall thickness (84) of thick transition (80) to wall thickness (84) of thin transition (82) of about 1.1 to about 2.5.