Abstract: A bearing is mounted to a static structure outwardly of the shaft, and supporting the shaft. A bearing compartment is defined by face seal arrangements on each of two axial sides of a bearing. Each face seal arrangement includes a seal seat rotating with the shaft and a non-rotating sealing ring. The seal housing is exposed to high pressure air outward of the bearing compartment. A coil spring biases the seal housing towards the seal seat, such that the sealing face is biased into contact with the seal seat by a bias force including a net fluid force acting on the seal housing and the coil spring. The sealing face is defined by a contact portion contacting the seal seat and a feed portion recessed from the seal seat. The feed portion includes a plurality of circumferentially spaced feed slots fluidly connected to at least one annular groove.

Abstract: A bearing is mounted to a static structure outwardly of the shaft, and supporting the shaft. A bearing compartment is defined by face seal arrangements on each of two axial sides of a bearing. Each face seal arrangement includes a seal seat rotating with the shaft and a non-rotating sealing ring. The seal housing is exposed to high pressure air outward of the bearing compartment. A coil spring biases the seal housing towards the seal seat, such that the sealing face is biased into contact with the seal seat by a bias force including a net fluid force acting on the seal housing and the coil spring. The sealing face is defined by a contact portion contacting the seal seat and a feed portion recessed from the seal seat. The feed portion includes a plurality of circumferentially spaced feed slots fluidly connected to at least one annular groove.

Abstract: A bearing is mounted to a static structure outwardly of the shaft, and supporting the shaft. A bearing compartment is defined by face seal arrangements on each of two axial sides of a bearing. Each face seal arrangement includes a seal seat rotating with the shaft and a non-rotating sealing ring. The seal housing is exposed to high pressure air outward of the bearing compartment. A coil spring biases the seal housing towards the seal seat, such that the sealing face is biased into contact with the seal seat by a bias force including a net fluid force acting on the seal housing and the coil spring. The sealing face is defined by a contact portion contacting the seal seat and a feed portion recessed from the seal seat. The feed portion includes a plurality of circumferentially spaced feed slots fluidly connected to at least one annular groove.

Abstract: A bearing is mounted to a static structure outwardly of the shaft, and supporting the shaft. A bearing compartment is defined by face seal arrangements on each of two axial sides of a bearing. Each face seal arrangement includes a seal seat rotating with the shaft and a non-rotating sealing ring. The seal housing is exposed to high pressure air outward of the bearing compartment. A coil spring biases the seal housing towards the seal seat, such that the sealing face is biased into contact with the seal seat by a bias force including a net fluid force acting on the seal housing and the coil spring. The sealing face is defined by a contact portion contacting the seal seat and a feed portion recessed from the seal seat. The feed portion includes a plurality of circumferentially spaced feed slots fluidly connected to at least one annular groove.

Abstract: A gas turbine engine includes an engine static structure. A rotating structure is configured to rotate relative to the engine static structure. The rotating structure has a target area with first and second directions. The first direction is greater than the second direction. A lubrication system includes a nozzle having a non-circular exit aimed at the target area. The exit provides a width and a height. The width is greater than the height. The width is oriented in the first direction.

Abstract: A carbon seal assembly may comprise a seal support, a seal housing coupled to the seal support, and a carbon seal adjacent an aft portion of the seal housing. The carbon seal may comprise a nose defined by an axial surface of the carbon seal, a first radial surface of the carbon seal, and a second radial surface of the carbon seal radially inward of the first radial surface. The first radial surface and the second radial surface may extend forward from the axial surface. A first axial length of the first radial surface may be greater than a second axial length of the second radial surface.

Abstract: A gas turbine engine includes an engine static structure. A rotating structure is configured to rotate relative to the engine static structure. The rotating structure has a target area with first and second directions. The first direction is greater than the second direction. A lubrication system includes a nozzle having a non-circular exit aimed at the target area. The exit provides a width and a height. The width is greater than the height. The width is oriented in the first direction.

Abstract: A ring seal in a gas turbine engine includes a ring seal body, an axial sealing dam, a radial sealing dam, and at least one bleed slot. The ring seal body is annular in shape and has a first axial side, a second axial side, a radially outer side, and a radially inner side. The axial sealing dam is on the first axial side and is configured to provide a first sealing surface with a first component. The radial sealing dam is on the radially outer side and is configured to provide a second sealing surface with a second component radially outward from the radially outer side. The at least one bleed slot is on the second axial side and configured to allow fluid to pass through when the ring seal is incorrectly oriented such that the at least one bleed slot is adjacent to the first component.

Abstract: A gas turbine engine may have a fan section that includes a variable pitch mechanism for changing the pitch of fan blades. The gas turbine engine may include a fan hub that is rotatable about an engine central longitudinal axis of the gas turbine engine and a blade receiver that is for holding a fan blade and that is rotatably coupled to the fan hub and may be rotatable about a radial axis of the gas turbine engine. The gas turbine engine may include a spring element disposed between the fan hub and the blade receiver to bias the blade receiver radially outward and an annular retaining ring may be disposed around the radial axis and between the fan hub and the blade receiver to limit radially outward movement of the blade receiver to prevent the blade receiver from decoupling and disengaging from the fan hub.

Abstract: A ring seal assembly includes a first ring seal that is symmetrical with respect to a radially extending plane. A second ring seal is separated axially from the first ring seal by a spring. The second ring seal includes a first inner circumferential surface. An interference feature extends radially inward from the first inner circumferential surface to a second inner circumferential surface.

Abstract: A force balanced face seal may comprise a seal housing comprising an annular extrusion, a seal support, wherein the annular extrusion is disposed within the seal support, and a primary seal coupled to the seal housing, wherein the primary seal comprises a sealing face and a base opposite the sealing face and proximate the seal housing.

Abstract: A carbon seal assembly may comprise a seal support, a seal housing coupled to the seal support, and a carbon seal adjacent an aft portion of the seal housing. The carbon seal may comprise a nose defined by an axial surface of the carbon seal, a first radial surface of the carbon seal, and a second radial surface of the carbon seal radially inward of the first radial surface. The first radial surface and the second radial surface may extend forward from the axial surface. A first axial length of the first radial surface may be greater than a second axial length of the second radial surface.

Abstract: A ring seal in a gas turbine engine includes a ring seal body, an axial sealing dam, a radial sealing dam, and at least one bleed slot. The ring seal body is annular in shape and has a first axial side, a second axial side, a radially outer side, and a radially inner side. The axial sealing dam is on the first axial side and is configured to provide a first sealing surface with a first component. The radial sealing dam is on the radially outer side and is configured to provide a second sealing surface with a second component radially outward from the radially outer side. The at least one bleed slot is on the second axial side and configured to allow fluid to pass through when the ring seal is incorrectly oriented such that the at least one bleed slot is adjacent to the first component.

Abstract: A ring seal assembly includes a first ring seal that is symmetrical with respect to a radially extending plane. A second ring seal is separated axially from the first ring seal by a spring. The second ring seal includes a first inner circumferential surface. An interference feature extends radially inward from the first inner circumferential surface to a second inner circumferential surface.

Abstract: A carbon ring for a seal assembly in a gas turbine engine includes an outer face extending circumferentially around a center axis of the carbon ring. The carbon ring also includes an inner face extending around the center axis and disposed radially inward from the outer face. A forward face of the carbon ring extends radially between the inner face and the outer face. A rear face of the carbon ring extends radially between the inner face and the outer face and is disposed axially opposite the forward face. At least one tab extends axially from at least one of the forward face and the rear face.

Abstract: A gas turbine engine may have a fan section that includes a variable pitch mechanism for changing the pitch of fan blades. The gas turbine engine may include a fan hub that is rotatable about an engine central longitudinal axis of the gas turbine engine and a blade receiver that is for holding a fan blade and that is rotatably coupled to the fan hub and may be rotatable about a radial axis of the gas turbine engine. The gas turbine engine may include a spring element disposed between the fan hub and the blade receiver to bias the blade receiver radially outward and an annular retaining ring may be disposed around the radial axis and between the fan hub and the blade receiver to limit radially outward movement of the blade receiver to prevent the blade receiver from decoupling and disengaging from the fan hub.

Abstract: An oil accumulator assembly may comprise a scavenge tube including an aperture defined by a break in the scavenge tube and/or an annular cylindrical structure concentrically situated about the scavenge tube. The aperture may be configured to receive oil flowing through the scavenge tube, and the annular cylindrical structure may be configured to accumulate oil flowing through the aperture. The oil accumulator assembly may further comprise a drainage outlet disposed in the annular cylindrical structure. Oil accumulated within the annular cylindrical structure may drain through the drainage outlet in response to an engine being shut down. The oil accumulated within the annular cylindrical structure may fill a portion of the scavenge tube situated within an engine fan case to prevent coking within the scavenge tube.

Abstract: A carbon ring for a seal assembly in a gas turbine engine includes an outer face extending circumferentially around a center axis of the carbon ring. The carbon ring also includes an inner face extending around the center axis and disposed radially inward from the outer face. A forward face of the carbon ring extends radially between the inner face and the outer face. A rear face of the carbon ring extends radially between the inner face and the outer face and is disposed axially opposite the forward face. At least one tab extends axially from at least one of the forward face and the rear face.

Abstract: An oil accumulator assembly may comprise a scavenge tube including an aperture defined by a break in the scavenge tube and/or an annular cylindrical structure concentrically situated about the scavenge tube. The aperture may be configured to receive oil flowing through the scavenge tube, and the annular cylindrical structure may be configured to accumulate oil flowing through the aperture. The oil accumulator assembly may further comprise a drainage outlet disposed in the annular cylindrical structure. Oil accumulated within the annular cylindrical structure may drain through the drainage outlet in response to an engine being shut down. The oil accumulated within the annular cylindrical structure may fill a portion of the scavenge tube situated within an engine fan case to prevent coking within the scavenge tube.

Abstract: An oil accumulator assembly may comprise a scavenge tube including an aperture defined by a break in the scavenge tube and/or an annular cylindrical structure concentrically situated about the scavenge tube. The aperture may be configured to receive oil flowing through the scavenge tube, and the annular cylindrical structure may be configured to accumulate oil flowing through the aperture. The oil accumulator assembly may further comprise a drainage outlet disposed in the annular cylindrical structure. Oil accumulated within the annular cylindrical structure may drain through the drainage outlet in response to an engine being shut down. The oil accumulated within the annular cylindrical structure may fill a portion of the scavenge tube situated within an engine fan case to prevent coking within the scavenge tube.