Support arrangement for a transition piece of a gas turbine engine

A support arrangement (10) for a transition piece (12) of a gas turbine engine (14). The support arrangement includes a mounting bracket (16) for the transition piece and a pin (18) supporting the mounting bracket in an interior (20) of the gas turbine engine and extending through an opening (22) in...

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Bibliographische Detailangaben
Hauptverfasser:	Pankey William W, Carlson Andrew
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS 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 WEAPONS
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Beschreibung
Zusammenfassung:	A support arrangement (10) for a transition piece (12) of a gas turbine engine (14). The support arrangement includes a mounting bracket (16) for the transition piece and a pin (18) supporting the mounting bracket in an interior (20) of the gas turbine engine and extending through an opening (22) in a casing (24) to an exterior (26) of the gas turbine engine. The support arrangement further includes a spherical washer (28, 38) positioned between the pin and either the mounting bracket or the casing.