Abstract: A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an outer platform, an inner platform, an airfoil that extends between the outer platform and the inner platform, a service tube disposed at least partially through the airfoil, and a seal assembly that seals between the service tube and one of the outer platform and the inner platform.

Abstract: A seal for reducing leakage about a rotating shaft having an axis includes a rotating component configured to be positioned radially outward from and surround the rotating shaft, and including a rotating cylinder defining an annular oil chamber for receiving oil. The seal also includes a static component including a sealing plate configured to extend into the annular oil chamber such that the oil fills a gap between the sealing plate and the rotating cylinder to reduce air leakage between the rotating component and the static component in response to rotation of the rotating component.

Abstract: A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an outer platform, an inner platform, an airfoil that extends between the outer platform and the inner platform, a service tube disposed at least partially through the airfoil, and a seal assembly that seals between the service tube and one of the outer platform and the inner platform.

Abstract: A seal for reducing leakage about a rotating shaft having an axis includes a rotating component configured to be positioned radially outward from and surround the rotating shaft, and including a rotating cylinder defining an annular oil chamber for receiving oil. The seal also includes a static component including a sealing plate configured to extend into the annular oil chamber such that the oil fills a gap between the sealing plate and the rotating cylinder to reduce air leakage between the rotating component and the static component in response to rotation of the rotating component.

Abstract: A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an outer platform, an inner platform, an airfoil that extends between the outer platform and the inner platform, a service tube disposed at least partially through the airfoil, and a seal assembly that seals between the service tube and one of the outer platform and the inner platform.

Abstract: A bearing support includes a squirrel cage including a fenestrated portion with a plurality of circumferentially spaced apart windows defined therethrough. A bearing support cage inboard of the squirrel cage defines a plurality of circumferentially spaced apart windows therethrough. The bearing support cage is operatively connected to the squirrel cage to support a bearing from within the squirrel cage.

Abstract: A gas turbine engine includes a service line interface that extends from an outer surface of a bearing support such that a heat shield is spaced from the outer surface. A method of mounting a heat shield to a gas turbine engine includes trapping a heat shield within a gapped overlap spaced from an outer surface of a bearing support.

Abstract: The present disclosure relates generally to a dual oil supply tube for a gas turbine engine. The dual oil supply tube locates a scheduled damper supply tube inside a compartment oil supply tube which remains full while the engine is operating.

Abstract: A bearing support includes a squirrel cage including a fenestrated portion with a plurality of circumferentially spaced apart windows defined therethrough. A bearing support cage inboard of the squirrel cage defines a plurality of circumferentially spaced apart windows therethrough. The bearing support cage is operatively connected to the squirrel cage to support a bearing from within the squirrel cage.

Abstract: A gas turbine engine includes a service line interface that extends from an outer surface of a bearing support such that a heat shield is spaced from the outer surface. A method of mounting a heat shield to a gas turbine engine includes trapping a heat shield within a gapped overlap spaced from an outer surface of a bearing support.

Abstract: A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an outer platform, an inner platform, an airfoil that extends between the outer platform and the inner platform, a service tube disposed at least partially through the airfoil, and a seal assembly that seals between the service tube and one of the outer platform and the inner platform.

Abstract: The present disclosure relates generally to a dual oil supply tube for a gas turbine engine. The dual oil supply tube locates a scheduled damper supply tube inside a compartment oil supply tube which remains full while the engine is operating.