Abstract: A gas turbine sealing arrangement which includes a seal housing having at least one seal in close proximity to the turbine rotor. The seal housing is preheated prior to turbine start-up to thermally move the seal housing and its seal radially away from the rotor.

Abstract: A fan drive assembly including a cooling fan (11) and a fluid coupling device (13). The cooling fan includes a fan hub (17), a spider (15), and a plurality of fan blades (19). The coupling device has an output coupling assembly (21) including a body (23) and a cover (25). The body (23) includes preferably only three mounting portions (67), each being disposed immediately adjacent an outer periphery of the body. Each of the mounting portions (67) defines the necessary machining chucking surfaces (73), and a spider mounting surface (75) including a pilot surface (77) engaging the pilot diameter (79) of the spider (15). The body (23) includes cooling fins (61) covering substantially all of the rearward surface (59) of the body not covered by the mounting portions. The fan hub (17) also includes a rearwardly extending air dam portion (81), limiting localized radial air flow.

Abstract: A rotor blade (1) comprises a main blade (2) having a substantially fixed chord length (C), a front tip blade (3) having a chord length (C1) smaller than that of the main blade and connected to the main blade so that a front edge (3a) thereof is continuous with a front leading edge (2a) of the main blade, and a rear tip blade (4) having a chord length (C2) greater than that of the front tip blade and connected to the main blade so that a trailing edge thereof is continuous with a trailing edge of the main blade. The blade incidence angle (&thgr;1, &thgr;2), the washout angle (&dgr;1, &dgr;2) and so on of at least either the front tip blade or the rear tip blade, the respective lengths (R1, R2) of the front tip blade (3) and the rear tip blade (4), and the anhedral angle (&eegr;) of the rear tip blade (4) are determined so that tip vortices generated by the front tip blade (3) and the rear tip blade (4) cancel each other to suppress BVI noise.

Abstract: A lightweight high temperature multiproperty rotor disk and method of manufacture for use in a gas turbine engine. The rotor disk of a nickel super alloy and having a plurality of lightweight high temperature single crystal blade attachment lugs bonded thereto. The single crystal high temperature rotor blade attachment lugs being cast in a substantially rectangular shape and bonded to the circumference of the disk. A method of manufacturing the rotor includes positioning the plurality of single crystal attachment lugs on a positioning ring that has locating nests formed thereon. Subsequently, the rotor disk is placed within the bonding ring and a restraining ring is placed around the entire subassembly. Upon subjecting the assembly to high temperature the rotor disk, having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the restraining member, forces the components into a mating relationship.

Abstract: A flow metering turbine comprises a tubular body through which flows the fluid to be measured. The tubular body houses an upstream spider and a downstream spider each formed by a hub and fixed vanes, bearing the hub in the tubular body. The mutually facing ends of the hubs have a cavity on the axis of the tubular body for receiving a support bearing and thrust bearing. A screw member formed by a hub bearing vanes and a shaft is located between the spiders, the ends of the shaft being located in the support bearings of the spiders and against the thrust bearings. At least one fluid duct runs through each spider, opening into the cavity in line with the support bearing and thrust bearing.

Abstract: A lateral channel fuel pump with a stator having a pumping channel and a second channel each of which cooperates with vanes in a rotor driven to rotate by an electric motor to generate pressure within both the pumping channel and the second channel. The second channel and preferably cavities communicating with it are disposed so that the fuel pressure generated within the channel and any cavities produces forces which, when combined with the forces generated in the pumping channel, provide net forces which are substantially equal or uniform across the lower face of the rotor so that the forces produced by outlet fuel acting across the upper face of the rotor do not tend to cock or tilt the rotor relative to the stator. Further, the second channel and any cavities increase the total force acting upwardly on the lower face to reduce the magnitude of the net force on the rotor urging the rotor towards the stator and hence, to reduce the frictional forces between the rotor and stator.

Abstract: A pump impeller of a centrifugal or a half axial type meant to pump liquids, mainly sewage water. The pump impeller has a hub (4) provided with one or several vanes (5) the leading edges (6) of which being strongly swept backwards. The periphery (8) of the leading edge is displaced 125-195 degrees relative to its connection (7) to the hub (4).

Abstract: A centrifugal or mixed flow type turbomachine, of a diffuser type can operate stably at low flow rates below the design flow rate, by preventing the initiation of flow instability in the system. The turbomachine comprises a stabilization member disposed in a predetermined location of the diffuser section which prevents a generation of unstable flow in the diffuser section during a low flow rate operation.

Abstract: In a feed pump designed for feeding fuel in a motor vehicle and having two feed chambers (11, 12) located opposite one another, of which one is connected to an inlet port (18) and the other to an outlet port (19), the feed chamber (11) connected to the inlet port (18) has a calming region (21) which a compression region (22) adjoins. Fuel entering the feed pump is thereby first calmed. Subsequently, in particular, gas bubbles present in hot fuel are dissolved due to the vapour pressure in the fuel being exceeded.

Abstract: The invention provides a novel hardwall fan case for encasing the radial periphery of a forward fan in a gas turbine engine. The fan case includes a rigid annular fan case shell spaced a selected radial distance from the tips of the fan blades, thus defining an annular internal air path surface of the fan case. The shell has a rigid hardwall fore section generally parallel to the blade tips and coated with a fore layer of abradable material. The fore section serves as a hardwall to limit the radial movement of fan blades deflecting under bird strike conditions and thereby to control the erosion of fan case linings. Limiting the radial blade deflection thus maintains the resulting fan tip clearance within acceptable limits. Uncontrolled or excessive erosion of fan case linings during bird strike conditions has in the past led to potentially catastrophic engine surge conditions where highly aerodynamically loaded fans are used that are very sensitive to enlarged tip clearances.

Abstract: A gas turbine having cooling structure disposed on an outside peripheral side in a radial direction of a movable vane in which the cooling efficiency is further improved and sealing structure disposed on an inner peripheral side to suppress leakage of sealing air and prevent invasion of combustion gas into the turbine disc and enlargement of sealing air clearance is prevented. Outwardly in the radial direction, a gap between ring segment (90) and impingement cooling plate (92) disposed on the outer periphery thereof, is divided in the axial direction by a pressure partition plate (97) extending in a circumferential direction so as to provide plural cavities adjusted to different pressures, thereby forming a cooling structure in the ring segment (90). Inside in the radial direction, a static vane inside diameter side cavity (53) and downstream cavity (31) are formed by a box (57) for sealing the static vane inside diameter side cavity (53).

Abstract: A seal and a washer for a variable vane assembly in a turbine engine are described. The seal includes a first portion and a second portion that are substantially perpendicular. The seal is positioned between a variable vane and a casing. The washer is substantially flat and is located between the casing and a spacer.

Abstract: A fan assembly comprising a fan, a stationary airflow directing device and a support inner ring. The fan has a hub portion and a plurality of fan blades. Each of the fan blades has a root region and a tip region. The root regions of each fan blade are secured to the hub portion wherein the fan blades extend substantially radially of a fan rotational axis. The airflow directing device has a plurality of stator blades extending radially about the support inner ring. The stator blades receive air flow from the fan and divert the airflow. The surface area of the stator blades is substantially less than the surface area of the fan blades. Each stator blade has a planar surface and a curved surface opposing the planar surface. The planar surface is disposed such that rotational components of air flow from the fan are incident on the planar surface.

Abstract: A turbine wall includes an outer surface for facing combustion gases, and an opposite inner surface for being impingement air cooled. A plurality of adjoining ridges and grooves are disposed in the inner surface for enhancing heat transfer by the impingement cooling air.

Abstract: A bushing assembly as a means to enable guided movement of a shaft in an opening of a housing comprises a stationary bushing support carried by a housing internal wall. The bushing support has a support internal wall defining a bushing support opening through the bushing support to receive a movable shaft. Carried by the shaft is a removable wear sleeve having a wear sleeve outer wall in juxtaposition with and spaced apart from the support internal wall to permit relative axial movement of the wear sleeve with the shaft within the bushing support opening. Disposed between and for contact with the support internal wall and with the wear sleeve outer wall is an anti-friction layer.

Abstract: A flow machine with rotor and stator in axial structure in flow-oriented terms, at least in sections, having moving blades at the rotor and housing-fixed guide vanes, whereby the latter are arranged as at least one guide vane ring with an inner and an outer cover band. The at least one guide vane ring is implemented as self-bearing component part having a closed reinforcement at the inner cover band that reinforces the component part to resist jamming axial deformation, comprises a segmented outer cover band and is positioned in the housing over at least three cover band segments with bearing units that respectively allow radial relative movements. An air guide shell that guides a cooling air stream along the inside of the housing and is provided with openings for the housing-fixed bearing elements of the at least one guide vane ring is arranged between the housing and the outer cover band of the at least one guide vane ring.

Abstract: A turbine blade having an extensible tail is described. The extensible tail is selectively positionable during engine operation, enabling fine-tuning for maximum power and efficiency during engine operation. During periods of operation exhibiting low Reynolds number flows, the extensible tail is projected out from the trailing edge of the turbine blade, into the gas path. As Reynolds number flows increase, the extensible tail is retracted back into the turbine blade, maximizing turbine engine efficiency.

Abstract: A vacuum pump comprising at least a molecular drag section and a turbo-molecular section, a rotor common to both sections and a stator common to both sections. The turbo-molecular section is positioned wholly within an envelope defined by the molecular drag section.

Abstract: A blade assembly for use in a steam turbine having a housing, includes a plurality of circumferentially aligned and spaced-apart hollow blade members which have each a base and a head piece and are so arranged in the housing of the turbine as to form an inner ring and an outer ring. Each blade member is made of sheet metal and forms with the base and the head piece a uniform weldment, with the base of all blade members being suspended from stationary receptacles of the turbine housing.

Abstract: Turbine nozzles and turbine moving blades of an axial-flow turbine are provided which are capable of reducing a secondary flow loss with a simple structure. A nozzle blade passage formed by nozzle blades, an outer diaphragm ring and an inner diaphragm ring is structured in such a manner that the shapes of inner and outer walls of the nozzle blades are made to be irregular so that stepped portions (h1 at the root and h2 at the tip) each having curvature R are formed. The nozzle blades are formed in such a manner that ends (Zr, Zp and Zt) of a trailing edge of the nozzle blades are positioned at the most downstream position at the central portion of the nozzle blades. Moreover, relationships Zt<Zr<Zp are satisfied. Similarly to the nozzle blade passage, the moving blades are formed in such a manner that stepped portions h3 and h4 each having curvature R are formed in the moving blade passage.