GAS TURBINE ROTOR ASSEMBLY AND METHOD OF ASSEMBLY

A gas turbine engine rotor assembly includes a rotor disk (68) with a slot (104). A rotor blade (64) has a root (74) supported within the slot (104). A heat shield (106) is arranged in a cavity in the slot (104) between the root (74) and the rotor disk (68). An axial retention feature (116,118) is c...

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Bibliographische Detailangaben
Hauptverfasser:	HIMES, JASON D, TRESSER, JORDAN, MECKLENBURG, DWAYNE K, WILSON, ROSS, GRIFFIN, DAVID RICHARD, VIRKLER, SCOTT D
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING 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 gas turbine engine rotor assembly includes a rotor disk (68) with a slot (104). A rotor blade (64) has a root (74) supported within the slot (104). A heat shield (106) is arranged in a cavity in the slot (104) between the root (74) and the rotor disk (68). An axial retention feature (116,118) is configured to axially maintain the heat shield (106) within the slot (104).