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 compression-ignition internal combustion engine includes a fuel injection nozzle including a tip end portion exposed in a combustion chamber and a nozzle hole formed at the tip end portion; and a passage forming member forming a flow guide passage through which fuel injected from the nozzle hole passes. The passage forming member includes a passage wall portion located radially outward of the flow guide passage. The passage wall portion includes a first layer that is a base portion connected to a cylinder head, and a second layer located radially outward or radially inward of the first layer. The toughness of the first layer is higher than the toughness of the second layer. The thermal conductivity of the second layer is lower than the thermal conductivity of the first layer.

A diaphragm pump includes a pump chamber, a diaphragm, and a diaphragm deformer. The pump chamber is box-shaped and includes at least an inlet opening, an outlet opening, and a diaphragm attaching opening. The pump chamber is provided with an inner space. A diaphragm is made of an elastically deformable material, and is provided in the pump chamber so as to cover the diaphragm attaching opening. The diaphragm deformer elastically deforms the diaphragm to change a capacity of the inner space. The outlet opening is located at a highest position in the inner space of the pump chamber.

The invention relates to a highly heat conductive valve seat ring (1) comprising a carrier layer (2) and a functional layer (3), wherein the carrier layer (2) consists of a solidified copper matrix containing 0.10 to 20% w/w of a solidifying component s and the functional layer (3) consists of a solidified copper matrix which further contains, based on the copper matrix, 5 to 35% w/w of one or more hard phases.

The invention relates to a powdermetallurgically produced valve seat ring having a carrier layer and a function layer. It is the objective of the invention to provide a valve seat ring of the kind mentioned above that offers significantly higher thermal conductivity properties. To achieve this objective and based on a valve seat ring of the kind first mentioned above the invention proposes that the carrier material of the carrier layer has a thermal conductivity higher than 55 W/m*K at a total copper content ranging between >25 and 40% w/w.

A diaphragm pump includes a pump chamber, a diaphragm, and a diaphragm deformer. The pump chamber is box-shaped and includes at least an inlet opening, an outlet opening, and a diaphragm attaching opening. The pump chamber is provided with an inner space. A diaphragm is made of an elastically deformable material, and is provided in the pump chamber so as to cover the diaphragm attaching opening. The diaphragm deformer elastically deforms the diaphragm to change a capacity of the inner space. The outlet opening is located at a highest position in the inner space of the pump chamber.

A housing assembly for a rotary engine, has: a rotor housing extending around an axis, the rotor housing having an inner face facing a rotor cavity; side housings secured to opposite sides of the rotor housing, the rotor cavity bounded axially between the side housings; and a seal received within a groove at an interface between the rotor housing and a first side housing, the groove annularly extending around the axis, located outwardly of the inner face, and overlapping a peripheral section of the first side housing, the seal having: an elastomeric member compressed between the peripheral section and the rotor housing; and a shield disposed inwardly of the elastomeric member, the shield having a melting point above a temperature of combustion gases, the shield in contact with both of the peripheral section of the first side housing and the rotor housing.

A housing (10) of a compressor (1) according to the present embodiment includes at least one compression chamber (101) that compresses a gas aspirated into the inside thereof and is composed of a metal-resin composite (16) in which a resin member (14) composed of a thermosetting resin composition and a metal member (12) are bonded to each other. In a case where the metal-resin composite (16) is made into a test piece in which the resin member (14) having a thickness d.sub.1 and the metal member (12) having a thickness d.sub.2 are laminated on and bonded to each other and a ratio of d.sub.1/d.sub.2 is 3, and the test piece is put in a first state where the test piece is disposed, the surface on the resin member (14)-exposed side up, on two supports with no stress applied thereto and a second state where a 1-point bending stress of 140 MPa is applied in a thickness direction to the center of the surface on the resin member (14) side such that the center caves in after the first state, when putting in the first and second states is alternately repeated 1,000,000 times at a frequency of 30 Hz under a temperature condition of 25 C., the metal-resin composite exhibits bending fatigue resistance in which neither peeling nor fracture occurs.

A Stirling engine has a housing containing a displacer and a power piston arranged to reciprocate relatively to one another. A head is adjacent to the displacer to absorb heat, and is surrounded by a block of copper or aluminum. A substantial proportion of the block is clad with a layer of stainless steel or Inconel having a thickness of between 3 mm and 0.15 mm.

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.