Abstract: A seal assembly for a gas turbine engine includes a first seal member having a first surface, a second seal member having a second surface, with the second surface configured to generally abut at least a part of the first surface. At least a portion of at least one of the first surface and the second surface includes a coating that includes about 30 to about 80 weight percent of a hard carbide material, and about 20 to about 70 weight percent of lubricating material incorporated with the hard carbide material. The coating defines overlapping lenticular particles.

Abstract: A method and a device for scheduling true CPU resources for a virtual machine system are disclosed. In one aspect a virtual machine monitor (VMM) acquires information about loads on virtual CPUs (VCPUs), and the VMM assigns the true CPU resources based on the information about the loads on the VCPUs in such a manner that more true CPU resources are assigned to a VCPU with a higher load. With the method and device according to certain embodiments, it is possible to assign the true CPU resources based on the information about the loads on the VCPUs in such a manner that more true CPU resources are assigned to a VCPU with a higher load. Further, certain embodiments are implemented directly by the VMM irrespective of types of upper-level GOSs, and thus is versatile.

Abstract: A protective coating for a surface exposed to hot gas flow comprises a thermal layer, a conducting layer and an abrasive layer. The thermal layer comprises stabilized zirconia, and overlies the surface. The conducting layer overlies the thermal layer. The abrasive layer comprises abrasive particles bonded in a metal matrix that is electroplated onto the conducting layer.

Abstract: A single point load structure transfers a first load from a first bearing cone and a second load from a second bearing cone of a gas turbine engine to a plurality of struts. The single point load structure includes a stem, a branch connected to the stem and a torque box connected to the plurality of struts for absorbing the first and second loads from the stem and the branch. The stem has a concave surface that opens in a radially outward direction with respect to a rotational axis of the gas turbine engine.

Abstract: An assembly for holding a fluid includes an auxiliary reservoir inside a main reservoir. The auxiliary reservoir includes an auxiliary reservoir shell with a fill passage at or near its bottom. The auxiliary reservoir shell also has a vent passage at or near its top. The fill passage and the vent passage fluidically connect the auxiliary reservoir to the main reservoir. A fluid inlet is located inside the main reservoir and outside of the auxiliary reservoir. A fluid outlet located inside the auxiliary reservoir between the fill passage and the vent passage.

Abstract: A method for comparing a plurality of geometrical data representations each representing a spatial boundary surface of a corresponding geometrical object which surface changes over a selected extent of the object bounded thereby through providing the plurality of geometrical data representations on a common format basis, including scaling so as to each to have a common selected extent, to thereby result in a plurality of standardized spatial boundary surface geometrical data representations and comparing them at a plurality of matching section locations along each of the common extents at each of which there is a section outline curve representations. Comparing selected features of the commonly scaled section outline curve representations for such representations at corresponding ones of the selected matched section locations provides a basis for determining similarity therebetween.

Abstract: A spinner mounting at least one propeller hub and having a blade platform for each hub formed on the spinner body formed from a thermal insulating material capable of withstanding exhaust gasses. The platform is formed in a shape that presents an aerodynamic surface in the direction of travel of the system, preferably at a predetermined effective blade angle so as to act in concert with the blade and the gas path to minimize drag or to optimize thrust. The system may include two sets of propeller blades, and each includes a spinner and blade platform.

Abstract: A method for producing nanoparticles of a selected size includes selecting an organic solvent based upon a molar volume of the organic solvent, the selected nanoparticle size, and a known relationship between the molar volume and the selected nanoparticle size, and producing nanoparticles having the selected size in a water-in-oil microemulsion comprising the selected organic solvent.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load shell structure and a plurality of struts. The single point load shell structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load shell structure to the mount.

Abstract: A cooled gas turbine engine component includes a cooling passage, one or more cooling inlet apertures in flow communication with a coolant supply and a first end of the cooling passage, and a coolant flow obstruction inside the cooling passage between the one or more cooling inlet apertures and a second end of the cooling passage and configured to direct a portion of coolant from the one or more cooling inlet apertures toward the first end of the cooling passage.

Abstract: Elevator reassignment information is communicated to passengers in a group elevator system (10). The group elevator system (10) includes a group of elevators (14a, 14b, 14c) that is operable to transport each of the passengers to one of a plurality of floors (L, F2, F3, F4, F5). A destination entry input device (30, 35) at each floor permits each passenger to enter destination input information. A dispatch controller (20) assigns an elevator to each passenger based on the destination input information. When service of a dispatched elevator is terminated, a communication device (46, 50) communicates elevator reassignment instructions to passengers assigned to or located in the dispatched elevator.

Abstract: A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and cooling channels extending radially between the base and the tip of the airfoil between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply through the base of the airfoil. The cooling channels include a leading edge channel, a trailing edge channel, a serpentine cooling circuit, and a dedicated up-pass channel. The serpentine cooling circuit includes a first up-pass channel forward of the trailing edge channel and configured to be in flow communication with a supply channel through the base of the airfoil, a down-pass channel forward of and in flow communication with the first up-pass channel, and a second up-pass channel forward of and in flow communication with the down-pass channel.

Abstract: A destination entry input device (30, 35) is commissioned in a group elevator system (10). The destination entry input device (30, 35) is connected to a dispatch controller (20). A network address is input into the destination entry input device (30, 35) corresponding to an installation location of the destination entry input device (30, 35). When the network address is input, installation location information related to the installation location of the destination entry input device is downloaded to the destination entry input device (30, 35) and verified.

Abstract: A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and a forward-flow low pressure turbine disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine disposed aft of the low pressure turbine, a combustor disposed aft of the high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor.

Abstract: An epicyclic gear assembly includes a ring gear, a sun gear, at least one star gear enmeshed between the ring gear and sun gear, a carrier and a journal bearing. The carrier is disposed adjacent the rotatable sun gear and star gear. The journal bearing is disposed in the at least one star gear and connected to the carrier. The journal bearing has an outer radial surface with an amorphous surface finish of less than about 5 micro inches (127 micro mm) measured on an Ra scale and the outer surface of the journal bearing interfaces with an inner surface of the star gear.

Abstract: A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.

Abstract: A gas turbine engine includes a radial compressor having first and second blades. The first blade has a tuned leading edge that prevents either blade from exciting at a natural frequency at speeds within an expected operating speed range.

Abstract: A system for adjusting the pitch of a counter-rotating propeller has a propeller shaft, a forward propeller driven by the propeller shaft, and an aft propeller connected with the forward propeller. The forward propeller has a hub, blades mounted within the hub, and an actuator connected with an end of the blades. The aft propeller has a hub, blades mounted within the hub, and a cam assembly connected with an end of the blades. The actuator of the forward propeller has a forward end and an aft end, wherein the aft end is connected with the cam assembly of the aft propeller. Thus, when the actuator moves in an axial direction, the cam assembly moves relative to the actuator and the pitch of the forward propeller blades and the pitch of the aft propeller blades are simultaneously adjusted.

Abstract: A power system (10) operates a plurality of hoist motors (18a, 18b, 18c), each of which controls movement of one of a plurality of elevators (12a, 12b, 12c). The power system (10) includes a power bus (11) and a converter (22) connected across the power bus (11) for converting alternating current (AC) power from an AC power source (20) to direct current (DC) power and delivering the DC power to the power bus (11). The power system (10) also includes a plurality of inverters (26a, 26b, 26c) connected across the power bus (11). Each inverter (26a, 26b, 26c) is connected to a hoist motor (18a, 18b, 18c) and is operable to drive the hoist motor (18a, 18b, 18c) when the hoist motor (18a, 18b, 18c) is motoring by converting the DC power from the power bus (11) into AC power. Each inverter (26a, 26b, 26c) is further operable to convert AC power produced by the hoist motor (18a, 18b, 18c) when the motor is generating to DC power and to deliver the DC power to the power bus (11).

Abstract: A gas turbine engine includes a radial compressor with first and second blades. The first and second blades have tuned leading edges that prevent natural frequencies from exciting at speeds within an expected operating speed range.