Abstract: A latch assembly for securing a nacelle portion of a gas turbine engine includes first and second nacelle flow structures that define a portion of a bypass flowpath. A seal is engageable between the first and second nacelle flow structures. A latch is rotatable about a pivot between latched and unlatched positions. The latch maintains the seal in engagement with the first and second nacelle flow structures in the latched position. A method of opening a nacelle flow structure includes the steps of pivoting a latch from a latched position to an unlatched position, and unlatching a first nacelle flow structure relative to a second nacelle flow structure in response to the latch pivoting step.

Abstract: A method and associated system are provided for deicing turbine blades of a wind turbine, wherein rotational torque from a rotor hub on which the turbine blades are mounted is transmitted to a generator. The method and system include detecting conditions that are indicative of ice formation on a wind turbine blade. In response to detected icing conditions, generator torque is modulated so as to induce upstream vibrations in the turbine blades to shake loose ice that may have formed on the turbine blades.

Abstract: A stow abort mechanism for a ram air turbine (RAT) with a strut that rotates a turbine with associated blades from a stowed position to a deployment condition comprises a stow abort lock plate with an aperture that rotates with the strut and a stow abort lock pin that engages the aperture in the stow abort lock plate when the blades do not align properly for rotating the strut back into the stowed position.

Abstract: A piston pump (10) for a hydraulic consumer of an electronically controlled vehicle brake system, carries a stepped piston (50, 50?) and centers a sealing assembly (26, 26?) which is retained in an axial direction Ax by a step (52, 52?) on the stepped piston (50, 50?), on the one hand, and is retained by a spring cage (53, 53?), on the other hand. The stepped piston (50, 50?) includes a plane support (54, 54?) for plane support legs (55a,b,c; 55a,b,c?) of the spring cage (53, 53?) The stepped piston (50, 50?) includes radially inwards, with respect to the support (54, 54?), a stepped bore (56, 56?), with the bore (56, 56?) accommodating centering legs (57a,b,c; 57a,b,c?) of the spring cage (53, 53?). Coaxially as well as inside the stepped bore (56, 56?), a spring-loaded valve member (59, 59?) of a non-return valve is arranged.

Abstract: A pumping apparatus for pumping a liquid from a source to a target including a motor, a first pump driven by the motor, a second pump driven by the motor and a separator in fluid communication with the first and second pump for separating a liquid received from a source into a gaseous component and a liquid component. The separator further diverts the gaseous component to the first pump and the liquid component to the second pump, wherein the first pump pumps the gaseous component back to the source and the second pump pumps the liquid component to a target.

Abstract: The invention concerns a fluid pump with a cylinder, piston and check valve for compressing the fluid having a high-pressure seal for precluding leakage of pressurized fluid. Any leakage from the high-pressure seal feeds back into an inlet area of the pump and recycles through the pump instead of leaking externally.

Abstract: A side-blown fan is formed by a case and a blade member. The case includes a side-outlet, an axial inlet and a protrusion. The protrusion extends from an edge of the axial inlet toward the center of the axial inlet. The blade member is embedded in the inside of the case. In the radial direction, a high air pressure region exists between the blade member and the case. The protrusion covers the high air pressure region and a part of the blade member.

Abstract: A gas turbine component article has an airfoil section and is formed of a nickel-base superalloy. An unmasked region of the airfoil section has a platinum aluminide protective coating, and a masked region of the airfoil section has an aluminide coating. The platinum aluminide preferably is deposited at a trailing edge of the airfoil section that is susceptible to low-cycle fatigue damage when a platinum aluminide coating is present.

Abstract: A propeller assembly that includes a plastic bushing that is secured, e.g., bonded, to an inner hub and is configured to engage an outer hub of a propeller. More specifically, and in an exemplary embodiment, the bushing includes a cylindrical shaped body having a bore therethrough, and a plurality of grooves are in an outer diameter surface of the cylindrical shaped body. The inner hub includes a cylindrical shaped body sized to extend into the bushing bore. A flange is at one end of the inner hub body, and at least one limp home tab extends from the flange. The propeller includes an outer hub having a cylindrical shaped body, and a plurality of blades extend from an outer diameter surface of the outer hub body. An inner diameter surface of the outer hub body has a plurality of protrusions that extend radially inward. Each protrusion is positioned to extend within a respective one of the grooves in the outer diameter surface of the bushing body.

Abstract: A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The airfoil trailing edge is selectively thickened in the root portion so as to allow shortened trailing edge slots, thereby improving trailing edge cooling and reducing mechanical and thermal stresses.

Abstract: A cooling system for cooling a housing of a turbo-machine comprising a feeder air line connected to the feeder air connection of the housing, a waste air line connected to the waste air connection of the housing, a recirculating air line, a fan position in the feeder air line, and means for changing feeder air temperature including a controller to control the air flow in the air lines.

Abstract: A ceiling fan comprising a plurality of fan blades connected to a rotatable motor by respective fan blade brackets with the fan blades being connected to the respective fan blade brackets by means of a boss that receives the fastener and a washer having a hole positioned around the boss between the fan blade bracket and the fan blade, whereby the washer may be affixed into position about the boss prior to installation of the fastener.

Abstract: A honeycomb structure is arranged on a stator of a gas turbine and is arranged opposite the moving blades of the gas turbine. The honeycomb structure is composed of metal sheets in such a way that webs having double the sheet thickness are obtained and connections of single thickness are obtained between the webs. The angle &agr; between the circumferential direction of the stator and the webs of double thickness is 5° to 175°. This serves to avoid undesirable efforts such as, for example, overheating during friction at the honeycomb structure of the moving blades of the gas turbine.

Abstract: A balancing arrangement which is used to relieve or take up axial thrust in a multistage centrifugal pump, having a balancing device with at least one axial gap (8) and at least one radial gap (6,7) and in which a balancing flow is conducted through the gaps, and having an axial bearing which receives remaining axial thrust. Associated with the axial bearing is a cardanic ring (10) which serves to offset alignment errors. Highly reliable operation with only low leakage losses is achieved by configuring the balancing device such that a residual thrust in the direction of the suction side of the pump exists in all operating conditons and the cardanic ring is designed such that it is elastically deformed by the residual thrust and has a spring constant such that the axial gap (s) will close from a maximum width position when the pump is at rest to a minimum width position during operation while still avoiding contact between the surfaces which define the axial gap.

Abstract: A gas turbine engine includes rotor blades including airfoils that facilitates reducing manufacturing losses due to airfoil trailing edge scarfing. Each airfoil includes a first and second sidewall connected at a leading edge and a trailing edge. The sidewalls define a cooling cavity that includes at least a leading edge chamber bounded by the sidewalls and the airfoil leading edge, and a trailing edge chamber bounded by sidewalls and the airfoil trailing edge. The cooling cavity trailing edge chamber includes a tip region, a throat, and a passageway region connected in flow communication such that the throat is between the tip region and the passageway region. Furthermore, the tip region is bounded by the airfoil tip and extends divergently from the throat, such that a width of the tip region is greater than a width of the throat.

Abstract: A turbo fan of a ceiling-embedded cassette type air conditioner. The turbo fan has a shroud for guiding a fluid introduced into the turbo fan, a hub having an outer diameter smaller than an inner diameter of the shroud, so as to facilitate an integral injection molding of the turbo fan, and blades extending between the shroud and the hub and being perpendicular to the shroud and the hub. Each of the blades has an inner diameter decreasingly inclined from the shroud to the hub, so that a quantity of sucked-air and a static pressure can be increased. The turbo fan not only can be integrally formed by injection molding but also can be manufactured at a reduced manufacturing cost.

Abstract: Fluid heating devices may be utilized, for example, to heat a vehicle coolant and may include a rotor body rotatably supported within a rotor housing. A plurality of blades may be disposed on a circumferential surface of the rotor body and a channel may be defined between each two adjacent blades. Each channel has a base portion, an inner circumferential end and an outer circumferential end. Preferably, the inner circumferential end is longer than the outer circumferential end as measured from the base portion. Further, the outer circumferential ends of the channels may define wall portions and the wall portions are preferably shorter than the inner circumferential ends as measured from the base portions of the channels. In view of this design, it is not necessary to provide shields toward the outer circumferential ends of the channels.

Abstract: A turbo-generator comprising a shaft, on which is positioned an axial ventilator, a cover that divides an inflow chamber for a cooling gas transported by the axial ventilator from an outflow chamber for this cooling gas, and a cylindrical channel segment that is positioned coaxially to the axial compressor and surrounds the axial compressor radially, whereby the inflow chamber comprises an asymmetrical cooling gas supply, and whereby in the inflow chamber means for homogenizing the cooling gas supply to the axial ventilator are provided. In order to improve the cooling, and therefore the efficiency of the machine, the inflow chamber forms a rotation-symmetrical annular chamber in the region of an inflow opening of the channel segment. A cylindrical annular collar is positioned coaxially to the axial ventilator within this annular chamber. The annular collar projects axially into the annular chamber and forms a completely surrounding, radial throttling gap at the inflow opening.

Abstract: An inner shroud assembly for a turbine comprising a plurality of part-annular segments combining to form an inner, annular shroud adapted to surround rotating components of a turbine, each segment having a pair of end faces that are juxtaposed similar end faces on adjacent segments with gaps therebetween; at least one convection cooling hole in the segment, opening along at least one of the pair of end faces. The cooling hole opens specifically into a diffuser recess formed in one of the pair of end faces for diffusing the flow of cooling air into the gap.

Abstract: A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The suction side wall has a selectively reduced thickness, which allows shortened trailing edge slots, improving trailing edge cooling.