A pump includes a rotor and a pump housing. The rotor is rotatable about a rotation axis and comprises a rotor hub and a rotor collar. The rotor collar extends from the rotor hub in the radial direction and encircles the rotor hub in an undulating manner. The pump housing comprises a first axial housing component, a central annular housing component, and a second axial housing component. A pump duct is formed (i) in the axial direction by the first and second housing components and (ii) in the radial direction by the central annular housing component and the rotor.

A gas turbine engine has a compressor section including a lower pressure compressor and a higher pressure compressor, and a turbine section. A core engine housing surrounds the compressor section and the turbine section. An outer intermediate housing wall defines an internal chamber between the core housing and the outer intermediate housing. A fan rotor and a fan casing surround the fan rotor to define a bypass duct between the fan case and the outer intermediate housing. A heat exchanger is mounted in the internal chamber and receives high pressure air for cooling the high pressure air and delivering the high pressure air into the core engine housing to be utilized as cooling air for a component. Air from the lower pressure compressor is utilized to cool the higher pressure air in the heat exchanger.

Disclosed is a method for producing a blade comprising a blade airfoil and a blade root for a turbomachine. The method comprises providing a first workpiece based on a first material and a second workpiece based on a second material which is different from the first material and has a higher temperature resistance than the first material; and connecting the first workpiece and the second workpiece by friction welding to form a composite component having a first region of the first material, and a second region of the second material. Optionally upon material-subtracting further processing, the first region forms the blade root, and the second region forms the blade airfoil.

A piston that moves reciprocally in the cylinder of an internal combustion engine and has a piston skirt that makes sliding contact with the inner wall of the cylinder. Solid lubrication parts are provided on the sliding-contact surface of the piston skirt. The solid lubrication parts include at least one type of silver, silver alloy, copper, or copper alloy, and at least one type of carbon material or carbide ceramics.

A pump having a rotor that is rotatable about a rotation axis and comprises a rotor hub and a rotor collar that extends from the rotor hub in the radial direction and encircles it in an undulating manner, and a pump housing which comprises a first axial housing component, a central annular housing component and a second axial housing component, wherein a pump duct is formed in the axial direction by the first and second housing components and in the radial direction by the central annular housing component and the rotor, and also a pump in which the annular pump duct has a constant cross section and connects a first radially external inlet/outlet space to a second radially external inlet/outlet space, and the pump may include a blocking device which is arranged between the first radially external inlet/outlet space and the second radially external inlet/outlet space and which comprises a blocking element which blocks the pump duct in the axial direction on both sides of the rotor collar.

A rotary internal combustion engine includes a rotor housing having a peripheral wall circumscribing a rotor cavity and a rotor disposed within the rotor cavity. A side housing is secured to the rotor housing and a plate defines a seal running surface for the rotor. The plate is disposed between a portion of the side housing and the rotor housing and at least one shim is disposed between the plate and the side housing for spacing the plate apart from contact with the side housing.

A rotary internal combustion engine includes a rotor housing having a peripheral wall circumscribing a rotor cavity and a rotor disposed within the rotor cavity. A side housing is secured to the rotor housing and a plate defines a seal running surface for the rotor. The plate is disposed between a portion of the side housing and the rotor housing and at least one shim is disposed between the plate and the side housing for spacing the plate apart from contact with the side housing.

Disclosed is a method for producing a blade comprising a blade airfoil and a blade root for a turbomachine. The method comprises providing a first workpiece based on a first material and a second workpiece based on a second material which is different from the first material and has a higher temperature resistance than the first material; and connecting the first workpiece and the second workpiece by friction welding to form a composite component having a first region of the first material, and a second region of the second material. Optionally upon material-subtracting further processing, the first region forms the blade root, and the second region forms the blade airfoil.

A gas turbine engine has a compressor section including a lower pressure compressor and a higher pressure compressor, and a turbine section. A core engine housing surrounds the compressor section and the turbine section. An outer intermediate housing wall defines an internal chamber between the core housing and the outer intermediate housing. A fan rotor and a fan casing surround the fan rotor to define a bypass duct between the fan case and the outer intermediate housing. A heat exchanger is mounted in the internal chamber and receives high pressure air for cooling the high pressure air and delivering the high pressure air into the core engine housing to be utilized as cooling air for a component. Air from the lower pressure compressor is utilized to cool the higher pressure air in the heat exchanger.