BEARING COMPARTMENT SEAL CONFIGURATION FOR A GAS TURBINE ENGINE

A bearing compartment seal (120) for a gas turbine engine (20) includes at least one seal ring (222) defining an axis and having a radially inward facing sealing surface and a seal runner (224) having a support (228) constructed of a first material and an interface portion (226) constructed of a sec...

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Bibliographische Detailangaben
Hauptverfasser:	MILLER, Jonathan Logan, ULLAH, M. Rifat
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CYLINDERS ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PISTONS SEALINGS STEAM ENGINES THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	A bearing compartment seal (120) for a gas turbine engine (20) includes at least one seal ring (222) defining an axis and having a radially inward facing sealing surface and a seal runner (224) having a support (228) constructed of a first material and an interface portion (226) constructed of a second material. The interface portion (226) includes a radially outward facing surface. A first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring (222).