METHODS AND APPARATUS FOR RADIALLY COMPLIANT COMPONENT MOUNTING

A mounting assembly for a liner of a gas turbine engine combustor and a gas turbine engine are provided to reduce in the combustor pressure drop and increase net power output of a gas turbine. A mounting assembly(200) for a liner of a gas turbine engine combustor includes an inner ring(208) and a ra...

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Bibliographische Detailangaben
Hauptverfasser:	BULMAN DAVID EDWARD, SCHRODER MARK STEWART, STUMPF JAMES ANTHONY, DARKINS TOBY GEORGE, LIPINSKI JOHN JOSEPH
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 mounting assembly for a liner of a gas turbine engine combustor and a gas turbine engine are provided to reduce in the combustor pressure drop and increase net power output of a gas turbine. A mounting assembly(200) for a liner of a gas turbine engine combustor includes an inner ring(208) and a radially outer ring(226). The inner ring surrounds the radial outer surface of a liner(9), and includes a plurality of fingers(210) extended in the axial direction. The radially outer ring is joined to the inner ring via a plurality of spacers. The spacers are extended from the radially outer surface of the inner ring to the radially outer ring in a radial direction.