A gas turbine engine includes a device for providing sealing between one rotor section and one stator section. The device includes a coating made of an abradable material attached to the stator section. The device further includes a lip on a portion of the rotor section. The lip is configured to form a seal with the abradable material. The gas turbine engine further includes passages for a gaseous fluid and means for blowing such gaseous fluid. The passages open into the rotor section provided with the lip, so that blown gaseous fluid can be present in a zone radially located between the coating and the lip.

A gas turbine engine includes, among other things, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, an inner shaft that interconnects the low pressure compressor and the low pressure turbine, an outer shaft that interconnects the high pressure compressor and the high pressure turbine, a bearing structure that supports at least one of the inner and outer shafts, and a buffer system. The buffer system prepares buffer air, communicates the buffer air to the bearing structure to pressurize a bearing compartment, and then from the bearing structure along at least one of the shafts.

A gas turbine engine includes, among other things, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, an inner shaft that interconnects the low pressure compressor and the low pressure turbine, an outer shaft that interconnects the high pressure compressor and the high pressure turbine, a bearing structure that supports at least one of the inner and outer shafts, and a buffer system. The buffer system prepares buffer air, communicates the buffer air to the bearing structure to pressurize a bearing compartment, and then from the bearing structure along at least one of the shafts.

A seal assembly for a turbomachine. The turbomachine includes a rotating shaft extending along a centerline and a fixed housing positioned exterior to the rotating shaft in a radial direction relative to the centerline. The seal assembly includes a sump housing at least partially defining a bearing compartment for holding a cooling lubricant. The seal assembly further includes a bearing supporting the rotating shaft. In addition, the seal assembly also includes a sump seal at least partially defining the bearing compartment. A pressurized housing of the seal assembly is positioned exterior to the sump housing and defines a pressurized compartment to at least partially enclose the sump housing. Further, a non-contacting carbon seal is positioned between the rotating shaft and the fixed housing to at least partially define the pressurized compartment to enclose the sump housing.

A seal assembly for a turbomachine. The turbomachine includes a rotating shaft extending along a centerline and a fixed housing positioned exterior to the rotating shaft in a radial direction relative to the centerline. The seal assembly includes a sump housing at least partially defining a bearing compartment for holding a cooling lubricant. The seal assembly further includes a bearing supporting the rotating shaft. In addition, the seal assembly also includes a sump seal at least partially defining the bearing compartment. A pressurized housing of the seal assembly is positioned exterior to the sump housing and defines a pressurized compartment to at least partially enclose the sump housing. Further, a non-contacting carbon seal is positioned between the rotating shaft and the fixed housing to at least partially define the pressurized compartment to enclose the sump housing.

An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.

A turbomachine includes a compressor section, a turbine section, and a rotary component. The rotary component is attached to and rotatable with a portion of at least one of the compressor section and the turbine section. The turbomachine additionally includes a seal having a gas bearing. The gas bearing defines an inner surface along a radial direction of the turbomachine, a high pressure end, and a low pressure end. The gas bearing supports the rotary component and also prevents an airflow from the high pressure end to the low pressure end between the rotary component and the inner surface of the gas bearing.

A turbomachine includes a compressor section, a turbine section, and a rotary component. The rotary component is attached to and rotatable with a portion of at least one of the compressor section and the turbine section. The turbomachine additionally includes a seal having a gas bearing. The gas bearing defines an inner surface along a radial direction of the turbomachine, a high pressure end, and a low pressure end. The gas bearing supports the rotary component and also prevents an airflow from the high pressure end to the low pressure end between the rotary component and the inner surface of the gas bearing.

A hydrostatic seal assembly includes a primary seal configured to maintain a selected gap between the primary seal and a rotating component. The primary seal includes a seal support, a seal shoe, and one or more seal beams operably connecting the seal support to the seal shoe. The one or more seal beams are configured as spring elements integral with the seal shoe to allow radial movement of the seal shoe relative to the seal support. A seal carrier including a radial outer wall is configured to radially position the primary seal. The seal carrier is configured for a non-contact relationship with the seal shoe during operation of the hydrostatic seal assembly.

A bearing housing cover for a gas turbine engine having an impeller. The bearing housing comprises an annular collar having a flange mountable to an exterior surface of a bearing housing. The bearing housing further comprises an impeller baffle integrated with the annular collar, the impeller baffle having an annular body with a front baffle face positionable adjacent a rear face of the impeller, a rear baffle face having a plurality of stiffening elements extending between the rear baffle face and the annular collar, and a central baffle opening.