The present disclosure relates to turbine blades adapted for use in gas turbine engines. In particular, this disclosure is directed to turbine blades that include components made from ceramic matrix composite materials and that incorporate abradable materials.

A component for a gas turbine engine includes an airfoil. A first trunnion has an outer surface and extends from a first end of the airfoil. A first bushing at least partially surrounds the outer surface. At least one of the first bushing or the first trunnion includes a plurality of surface irregularities.

To provide a sliding bearing for an electric water pump, the sliding bearing being superior in low friction performance in water or an antifreeze solution. A sliding bearing 3 is for an electric water pump that comprises a rotor 1 having the sliding bearing 3 that is formed in a substantially hollow cylindrical shape and rotatably supports a shaft, and a stator that is disposed on a circle coaxial with the shaft and rotationally drives the rotor 1. The sliding bearing 3 is formed of a resin composition that contains synthetic resin as a main component. The resin composition contains 5-30 vol % of carbon fiber that has a density of 2.00-2.25 g/cm.sup.3 and an average fiber length of 30-300 μm, to a whole volume of the resin composition.

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.

A turbine engine strut stage extends through a gaspath upstream of a guide vane stage. A carbon seal system seals a bearing compartment and has: a carbon seal mounted to the case and a seal runner on the spool; and a seal carrier carrying the carbon seal. The engine passes buffer air along a buffer air supply path internally through one or more first struts of the stage of struts. The engine drains oil along an oil drain path internally through one or more second struts of the stage of struts.

A seal system may include a static housing, a carbon seal positioned in the static housing, a runner having a sealing surface aligned with the carbon seal, a number of electromagnets positioned in the static housing, and a controller circuitry. The controller circuitry may control a variable flow of electric current to control an electromagnetic field respectively generated by each of the electromagnets. The controller circuitry may variably apply the electromagnetic field to move at least one of the carbon seal or the runner and correspondingly adjust an applied force loading of an interface of the carbon seal and the sealing surface of the runner.

A centrifugal pump has an open impeller conveying media containing solids with at least one blade that projects in the direction of an inflow. The surface of the open impeller is at least partially provided with a carbon layer, preferably a tetrahedral hydrogen-free amorphous carbon layer. A surface of an adjacent wear plate may also be coated with tetrahedral hydrogen-free amorphous carbon layer.

A centrifugal pump for conveying media containing solids includes at least one arrangement for reducing a backflow from a first chamber into a second chamber. The at least one arrangement includes at least one non-rotating element that cooperates with at least one rotating counter element. At least one of the at least one non-rotating element and the at least one rotating element I coated at least in parts by a tetrahedral hydrogen-free amorphous carbon layer.

A compressor blade of a gas turbine includes a compressor blade portion including a plurality of layers; and a carbon fiber reinforcement embedded in the plurality of layers of the compressor blade portion and oriented in a direction of stress fields of the compressor blade when in operation. A method of manufacturing the compressor blade includes preparing a composite material including fiber-reinforced layers; forming a first layer of the composite material to extend in a radial direction of the compressor blade; and stacking a second layer of the composite material on the first layer in an axial direction of the compressor blade. The compressor blade is 3D-printed by forming each composite material layer in a radial direction, which layers are stacked in an axial direction. Fiber reinforcement in the composite compressor blade is oriented in line with the stress fields inherent in the operation of the compressor blade.

A turbine engine strut stage extends through gaspath upstream of a guide vane stage. A carbon seal system seals a bearing compartment and has: a carbon seal mounted to the case and a seal runner on the spool; and a seal carrier carrying the carbon seal. The engine passes buffer air along a buffer air supply path internally through one or more first struts of the stage of struts. The engine drains oil along an oil drain path internally through one or more second struts of the stage of struts.