Abstract: A seal system for a bearing compartment of a gas turbine engine includes an annular rotating seal seat in contact with the seal element to form a dry seal interface therebetween to separate am oil-wetted zone from a dry zone. The annular rotating seal seat forms a dry zone annular space adjacent to the annular seal element and the rotating component. The annular rotating seal seat having an oil return passageway through the rotating seal seat to provide a communication path from the dry zone annular space outboard of the rotating component back to the oil-wetted zone.

Abstract: An assembly is provided for a piece of rotational equipment. This assembly includes a stationary component, a rotating component, and a dry seal assembly. The dry seal assembly is configured to substantially seal an annular gap between the stationary component and the rotating component. The dry seal assembly includes a seal element and a seal land. The seal element is mounted to the stationary component and is configured to sealingly engage the seal land. The seal land is mounted to the rotating component and is configured to permit gas leakage across the dry seal assembly through a passageway in the seal land.

Abstract: A seal system for a bearing compartment of a gas turbine engine includes an annular rotating seal seat in contact with the seal element to form a dry seal interface therebetween to separate am oil-wetted zone from a dry zone. The annular rotating seal seat forms a dry zone annular space adjacent to the annular seal element and the rotating component. The annular rotating seal seat having an oil return passageway through the rotating seal seat to provide a communication path from the dry zone annular space outboard of the rotating component back to the oil-wetted zone.

Abstract: An assembly is provided for a piece of rotational equipment. This assembly includes a stationary component, a rotating component, and a dry seal assembly. The dry seal assembly is configured to substantially seal an annular gap between the stationary component and the rotating component. The dry seal assembly includes a seal element and a seal land. The seal element is mounted to the stationary component and is configured to sealingly engage the seal land. The seal land is mounted to the rotating component and is configured to permit gas leakage across the dry seal assembly through a passageway in the seal land.

Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.

Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.

Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.

Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.

Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.

Abstract: An exemplary valve device for controlling flow of a turbomachine fluid includes a housing and a flow control assembly within the housing. The housing has a first inlet, a second inlet, and an outlet. Movement of the housing to a first orientation causes the flow control assembly to move to a first position to restrict flow of a turbomachine fluid into the housing through the second inlet. Movement of the housing to a second orientation causes the flow control assembly to move to a second position to restrict flow of the turbomachine fluid into the housing through the first inlet.

Abstract: An assembly includes a gas turbine engine, a compartment wall, and a gutter system. The gas turbine engine has a spool connected to a fan shaft via a gear system. The compartment wall is positioned radially outward from the gear system. The gutter system is positioned radially outward from the gear system for capturing lubricating liquid slung from the gear system and positioned radially inward of the compartment wall. The gutter system includes a gutter and a flow passage fluidically connected to the gutter. The flow passage has a plurality of holes that allow the lubricating liquid to pass through the flow passage into a space between the flow passage and the compartment wall.

Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.

Abstract: A rotating element is associated with at least one bearing compartment that includes a bearing to support the rotating element. A seal resists leakage of lubricant outwardly of the bearing compartment and allows air to flow from a chamber across the seal and into the bearing compartment. The seal has a seal face facing a rotating face rotating with the rotating element. The seal is a non-contact seal. A gas turbine engine is also disclosed.

Abstract: A rotating element is associated with at least one bearing compartment that includes a bearing to support the rotating element. A seal resists leakage of lubricant outwardly of the bearing compartment and allows air to flow from a chamber across the seal and into the bearing compartment. The seal has a seal face facing a rotating face rotating with the rotating element. The seal is a non-contact seal. A gas turbine engine is also disclosed.

Abstract: An exemplary valve device for controlling flow of a turbomachine fluid includes a housing and a flow control assembly within the housing. The housing has a first inlet, a second inlet, and an outlet. Movement of the housing to a first orientation causes the flow control assembly to move to a first position to restrict flow of a turbomachine fluid into the housing through the second inlet. Movement of the housing to a second orientation causes the flow control assembly to move to a second position to restrict flow of the turbomachine fluid into the housing through the first inlet.

Abstract: An assembly includes a gas turbine engine, a compartment wall, and a gutter system. The gas turbine engine has a spool connected to a fan shaft via a gear system. The compartment wall is positioned radially outward from the gear system. The gutter system is positioned radially outward from the gear system for capturing lubricating liquid slung from the gear system and positioned radially inward of the compartment wall. The gutter system includes a gutter and a flow passage fluidically connected to the gutter. The flow passage has a plurality of holes that allow the lubricating liquid to pass through the flow passage into a space between the flow passage and the compartment wall.

Abstract: An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting liquid oil from interfacial shear. A multiple of apertures are located through the shield to permit oil flow through the shield and into the duct. The scavenge scoop forms a partition which separates the duct into a first portion and a second portion. The first portion processes upstream air/oil mixture that is captured by the tangential scoop while the second portion receives the oil collected in the settling area.

Abstract: An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting liquid oil from interfacial shear. A multiple of apertures are located through the shield to permit oil flow through the shield and into the duct. The scavenge scoop forms a partition which separates the duct into a first portion and a second portion. The first portion processes upstream air/oil mixture that is captured by the tangential scoop while the second portion receives the oil collected in the settling area.

Abstract: An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting liquid oil from interfacial shear. A multiple of apertures are located through the shield to permit oil flow through the shield and into the duct. The scavenge scoop forms a partition which separates the duct into a first portion and a second portion. The first portion processes upstream air/oil mixture that is captured by the tangential scoop while the second portion receives the oil collected in the settling area.

Abstract: An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting liquid oil from interfacial shear. A multiple of apertures are located through the shield to permit oil flow through the shield and into the duct. The scavenge scoop forms a partition which separates the duct into a first portion and a second portion. The first portion processes upstream air/oil mixture that is captured by the tangential scoop while the second portion receives the oil collected in the settling area.