Abstract: A device for pumping paint includes a pump house adapted to receive paint from a paint source, a pump shaft for driving a pump member to rotate inside the house for pumping paint therethrough. The pump shaft is connected to an output shaft of a motor arranged outside the pump house through an intermediate shaft piece through a wall of the pump house. The motor is arranged to drive the pump shaft and the pump member. A sealing member is arranged to counteract paint leaking out of the pump housing along the pump shaft. The sealing member is arranged to seal by bearing substantially axially against substantially axial surfaces of the pump shaft around the pump shaft, in which the sealing member and/or these axial surfaces are preferably of a ceramic material.

Abstract: For improving characteristic uprising at the right-hand side of head-flow rate characteristic of a turbo machine, as well as for suppressing increase of vibration and/or noises thereof, a plurality of first grooves 24 in direction of gradient in pressure of fluid are formed on an inner flow surface of a casing, for connecting an inlet side of blades of an impeller and an area on the inner flow surface of the casing where the impeller blades reside in, over an inner circumference of the casing. Also, second grooves 25 in a circumferential direction are formed in an area on the inner flow surface of the casing where the impeller blades reside in, for communicating the first grooves in the circumferential direction of the casing.

Abstract: A combination in-line type water pump and power steering pump assembly which includes a power steering shaft with an outer end portion extending into a pumping chamber of the water pump. The outer end portion of the shaft is configured to removably support a tubular shaft sleeve and a water pump impeller thereon. A seal annulus is mounted in the pump housing and encompasses the shaft sleeve in water tight relation therewith at an inwardly location from the impeller. The impeller and the seal annulus are removable from the sleeve by application of an axial force to slip the impeller and seal annulus axially along the outer end of the shaft sleeve.

Abstract: A vane assembly 40 for use within a gas turbine engine has a main vane portion 42 with an internal cavity 44. A cavity insert 46 is located within the cavity 44, close to the wall 48 to define transpiration cooling paths. Cooling air leaves the insert 46 through apertures directed at the wall 48, to produce impingement cooling. The transpiration cooling paths are extended back to the trailing edge 66 by means of a fairing 54. The use of a fairing in addition to the insert allows more complicated cavity shapes to be filled.

Abstract: The invention relates to a method of manufacturing a gas-trubine blade and to a turbine blade. First, a hollow, supporting metal blade body is made, in particular by casting, with a multiplicity of, in particular peg-like, elevations on an outer surface of a blade airfoil of the metal blade body. Impact cooling bores are bored between the elevations from the outer surface to the hollow interior space of the metal blade body. A coating is applied which fills the intermediate spaces between the elevations and closes the impact cooling bores. The coating is made of a heat-resistant, removable material. Then, a covering coat is adhered to the metallically bright top sides of the elevations, and the material in the intermediate spaces between the elevations of the metal blade body and the covering coat is then removed.

Abstract: A hot swap fan tray with fan guard is disclosed. The present invention includes a frame, at least one fan and at least one fan guard. The frame includes a plurality of first holes. The fan includes a plurality of second holes. The fan guard further includes a plane and at least one protrusive terminal. The protrusive terminal projects from the plane and includes at least one bend. During the protrusive terminal passes through the first hole and the second hole, the bend changes shape and then returns original shape elastically, thereby the bend attaching said fan and said fan guard to said frame.

Abstract: A fluid-flow machine includes a rotor which extends along a rotation axis. The rotor has a rotor-shaft slot having a slot root surface and a moving blade having a blade root. The blade root is inserted into the rotor-shaft slot, and a gap is formed between the blade root and the slot root surface. A sealing element is provided for sealing the gap, which sealing element is at least partly accommodated by the blade root and is movable relative to the blade root. In addition, a sealing element, in particular for a rotor of a fluid-flow machine, preferably includes a first sealing element section and a second sealing element section. The sealing element develops its sealing effect under the effect of an external force, in particular of the centrifugal force.

Abstract: A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (34) comprises a generally annular, or frustoconical, cross-section casing (52). At least one corrugated sheet metal ring surrounds the casing (52) wherein the corrugations extend with axial and/or circumferential components.

Abstract: An annular disk side plate for a gas turbine engine rotor assembly includes an annular plate hub and an annular plate shaft extension extending axially forwardly from the plate hub. A plate web extends radially outwardly from the plate hub and a plate rim extends radially outwardly from the plate web. In the exemplary embodiments of the invention illustrated herein, the plate rim is canted aftwardly from the plate web. One or more annular sealing ridges extend aftwardly from the plate rim. The side plate further includes an anti-rotation means for preventing rotation of the disk side plate relative to the disk such as a circumferential row of radially extending circumferentially spaced apart tabs. Cooling air apertures or holes extend axially through the plate web. A rotor assembly further includes an annular rotor disk comprising a disk hub and an annular disk shaft extension extending axially forward from the disk hub.

Abstract: The cap plate has an axially recessed region with a shoulder. The gas guiding ring half shells have a respective projecting rib. A retaining ring consisting of two retaining ring halves abuts with its first leg in the shoulder and is connected by means of fillister head screws to the cap plate. The gas guiding ring half shells are positioned with respect to the cap plate with clearance fit in the radial and axial direction. The ribs have a spacing in the peripheral direction at the separation place of the gas guiding ring half shells in order to form gaps. At the same location, the first leg of the retaining ring halves is interrupted for the formation of recesses aligned with the gaps. Fixing wedges are inserted in the region of the gaps and of the recesses and are screwed to the cap plate. These fixing wedges transfer the tangential forces from the gas guiding ring half shells to the retaining ring halves.

Abstract: The invention relates to a turbo-machine (1) comprising a rotor (25) that extends along a rotational axis (15). Said rotor (25) has a peripheral surface (31) which is defined by the outer radial delimitation surface of the rotor (25) and has a receiving structure (33) as well as a first moving blade (13A) and a second moving blade (13B). Each moving blade comprises a blade footing (43A, 43B) and a blade platform (17A, 17B). The blade platform (17A) of the first moving blade (13A) and the blade platform (17B) of the second moving blade (13B) border one another, and a gap (49) is formed between the blade platforms (17A, 17B) and the peripheral surface (31). A sealing system (51) is provided in the gap (49) on the peripheral surface (31).

Abstract: A propeller fan adapted to prevent abnormal air flow to thereby increase discharge of air flow but to decrease noise, the fan including a plurality of vanes, each vane fixed at a hub secured at a rotary axle, having a predetermined length toward external radial direction thereof and circumferentially spaced out at a predetermined gap, wherein each van has a cross-sectional shape like a flat surface at an external side of a leading edge thereof while an external side of a trailing edge thereof is bent with a predetermined radius of curvature (Rc).

Abstract: A cooling fan (10) includes a plurality of blades (12) molded about a central hub plate (11) at an annular molded ring (13). A plurality of helical gussets (30) are formed on inlet side (25) of the molded ring (13) at the blade root (15) that are spaced apart to define flow gaps (32) therebetween, and are curved to substantially follow the airflow path through those gaps (32). A like plurality of radial ribs (40) may be formed at the outlet side (26) of the fan (10) that can include an indented stacking surface (41) that engages a contact surface (42) on the inlet side (25) to facilitate stacking of multiple fans. In another aspect, the fan blades (10) are configured to include elliptical or parabolic camber lines (C) that vary along the radial length of the blade so that the blade stacking, or the centers of gravity (CG) of radial blade segments, achieve a predetermined alignment under normal operating loads to minimize bending moments between blade sections.

Abstract: An adjustable and stable pre-loading device equipped fan includes a stator, a first rigid spacer, a first bearing, an elastic device, a second bearing, a second rigid spacer, a rotor and a shaft. Among these, the stator includes a receptacle. The first bearing is formed on the first rigid spacer in the receptacle. The elastic device is formed in the receptacle and further on the first bearing. The second rigid spacer is formed on the second bearing on the elastic device. The rotor is coupled to the stator and has a blade structure. The first rigid spacer compresses the elastic device by means of the first bearing. The second rigid spacer compresses the elastic device by means of the second bearing. The distance between the first rigid spacer and the second rigid spacer is adjustable, thereby altering pre-loading applied on the first bearing and the second bearing.

Abstract: Gas turbine steam passage seal structure between a blade ring and a stationary blade absorbs thermal deformation to prevent occurrence of minute gaps to thereby reduce leakage of steam as cooling medium. A blade ring steam passage hole, provided in the blade ring (10), has a stepped portion formed in a middle portion thereof. A stationary blade steam passage hole, provided in the stationary blade (50) so as to oppose the blade ring steam passage hole, has a stepped portion formed in an outer peripheral portion thereof. A cooling steam supply passage connection portion is constructed comprising a seal pipe (25) provided between the blade ring and stationary blade steam passage holes so as to communicate them with each other and a seal urging guide device (44, 47) provided at each of the stepped portions of the blade ring and stationary blade steam passage holes so as to effect a seal while fixedly supporting the seal pipe (25).

Abstract: A fan having stable pre-loading device includes a stator, at least one bearing, a rotor having a blade structure, a shaft and a rigid spacer. Among these, the bearing is formed in the space of the stator. One terminal of the shaft is coupled to the stator. The elastic device is formed on the bearing. The rigid spacer is formed on and thus compresses the elastic device. Another terminal of the shaft passing the rigid spacer as well as the elastic device is coupled to the inner ring of the bearing.

Abstract: An airfoil for a gas turbine engine, the airfoil having a core body with an airfoil body, an integral partial height squealer tip, and an integral tip cap between the airfoil body and the integral partial height squealer tip; and a squealer tip extension bonded to the partial height squealer tip. A method for manufacture and repair of an airfoil.

Abstract: A steam turbine has a rotor mounting axially spaced rotor wheels having male dovetails for mounting a plurality of axially spaced buckets having female dovetails. A plurality of arcuate bridging members extend axially between the axially adjacent bucket dovetails at locations spaced radially outwardly of the surface of the rotor shaft. A diaphragm in radial opposition to the bridging member mounts a brush seal having bristles engaging the bridging member. The bridging member carries backup labyrinth seal teeth for sealing with the diaphragm. The friction generated by contact between the brush seal bristles and bridging members lies radially outwardly of the rotor whereby non-uniform distribution of heat about the rotor surface due to frictional contact with the brush seal is avoided, with consequent avoidance of rotor bowing.

Abstract: A variable geometry turbocharger in which a bill-like projection portion is arranged in a part of an outer periphery of a flow passage spacer, and the projection portion is protruded to a turbine rotor side at a predetermined angle or the projection portion is movably provided. Alternatively, a rod-like member is arranged in a part of an outer periphery of a flow passage spacer and the rod-like member is arranged so as to be adjacent to the turbine rotor side at a predetermined angle. Alternatively, a guide vane in which a leading edge side of a rotational shaft is eliminated is arranged in a part of an outer periphery of a flow passage spacer and the rotational shaft is arranged so as to be adjacent to the turbine rotor side at a predetermined angle.

Abstract: In a fluid pump device, a filter is secured to a housing. A meshed portion of the filter substantially covers an inlet opening of the housing. Each engaging projection of the filter is engaged with a corresponding engaging recess of the housing in a direction perpendicular to an axial direction of an impeller. Arm portions of the filter substantially perpendicularly extend with respect to a meshed portion of the filter and are resiliently flexible in the direction perpendicular to the axial direction of the impeller. Each coupling projection of the filter is provided between adjacent two arm portions of the filter and is engaged with a corresponding coupling recess of the housing in the axial direction of the impeller.