Abstract: A protector for protecting aircraft, particularly helicopter rotor blades, from absorbing the sun's infrared rays and the accompanying heat build-up in order to keep adhesive material between spar connections from debonding and to avoid delamination from the rotor blade's composite skin. The rotor blade protector includes a cover configured to encircle the length of the rotor blade and a guide form for installing and removing the cover. The inner surface of the cover is coated, by vacuum deposition technology, with aluminum, titanium, or other metals or alloys. The coating thickness will be in the order of 9-30 billionths of a meter thick. A stripper rod is attached to the guide so that aircraft personnel can install and remove the protector from the helicopter rotor blade while standing on the ground. Optionally, a series of ribs can be provided along the cover to provide increased air insulation around the rotor blade.

Abstract: A seal adapter for reducing the escape of exhaust gases between an outboard motor and a propeller includes a substantially hollow cylindrical connecting member (71) having a shoulder (84) for dividing the connecting member (70) into a plurality of sections. A seal ring (80) is associated with one of the sections for engaging with an annular recess (76) located within the propeller hub (74) to provide a substantially tight seal.

Abstract: An arrangement for a gas turbine engine comprises a compressor and its surrounding casing. The casing has a generally cylindrical inner surface, one cylindrical section of the inner casing being provided with a circumferential array of recesses. An axially adjacent cylindrical section of the inner casing surface is provided with an abradable lining. The tips of the rotor blades of the compressor are provided with a treated portion at least partly axially aligned with the recesses in the inner casing, the remaining untreated portion of the rotor blade tips being at least partly axially aligned with the lined section of the inner casing.

Abstract: A steam turbine includes a rotor supporting a plurality of turbine buckets. The rotor has shaped grooves for receiving a complementary-shaped bucket hook formed on an end of each of the turbine buckets. A rope seal is disposed in each interface between the bucket hooks and the shaped grooves, respectively. The rope seal serves to seal a leakage path that may exist over the bucket hooks between the buckets and respective rotor grooves.

Abstract: A device which can be utilized to temporarily seal substantially any opening on a turbine which is being assembled or repaired. The foreign material exclusion device includes a main body, preferably formed from a foamed polymer or rubber. The foreign material exclusion device is substantially elastic or resilient and can be compressed to fit into a desired opening and can be reexpanded to provide a snug fit about an opening. An extraction member is connected to the main body and is preferably utilized to remove the device from a portion of a cavity of a turbine.

Abstract: A turbo blood pump having a small size, that is, a small amount of blood to be filled and capable of adjusting and maintaining the slight amount of flow, and a turbo blood pump in which hemolysis is not likely to occur even if it is used at a practically high rotational speed necessary to obtain a predetermined discharging ability. The turbo blood pump to be used includes a housing having an inlet port and an outlet port; and an impeller disposed rotatably in the housing; wherein the impeller includes at least a rotation shaft and an annular connection portion to which the plural vanes are attached. The vane is manufactured so that an inlet side part is in the skew position with respect to an outlet side part.

Abstract: A low speed cooling fan that is designed to cool individuals located in large industrial buildings. A fan with a diameter between 15 to 40 feet consisting of a plurality of blades, with each in the shape of a tapered airfoil, is driven by an electric motor to produce a very large slowly moving column of air. The moving column of air creates a uniformly gentle circulatory airflow pattern throughout the interior of the building thus promoting the natural evaporative cooling process of the human body at all locations inside the building.

Abstract: An automotive engine-cooling fan assembly uses pairs of overlapping fans to improve flow uniformity through the heat exchanger cores and to maximize the amount of fan power that can be achieved with limited motor sizes. One fan of each pair has upstream supports and the other has downstream supports, and these supports are so configured to minimize the axial dimension of the assembly. The use of banded fans maximizes fan performance, and blade skew minimizes fan noise.

Abstract: The present invention employs improved fan blade shapes to improve fan blade performance in one or more manners (i.e., increased fan efficiency, lower fan noise, greater fluid moving capability, and the like). In some embodiments, the fan blade has a front side, a rear side, an inner attachment portion, an outer edge, a curved leading edge and a curved trailing edge. The outer edge can define an arc between a forward position and a rearward position of the fan blade. In some embodiments, the leading edge extends outward and intercepts the arc of the outer edge at the forward position, and the trailing edge extends outward to the rearward position. Various angles, lengths, and other dimensions of the blade can have selected values to produce superior fan performance.

Abstract: A turbine blade is disclosed having a tip shroud that includes internal passages through which cooling air is flowed to minimize creep. The cooling air is provided to the shroud through dedicated cooling passageways which include tube inserts that restrict the transfer of heat from the airfoil portion of the turbine blade to the cooling air within the tube as the cooling air passes through the airfoil portion.

Abstract: A set of split bodies for forming a synthetic-resin blower fan through a hollow-article injection molding process, wherein the blower fan integrally includes a circular base, a cover portion having an air inlet opening at the center thereof, and a plurality of blades. The set of split bodies comprise a first split body including the circular base and a plurality of blade members, and a second split body defining the inner surface of the cover portion and having an outer surface on the opposite side of the first split body. The outer surface of the second split body is formed with a plurality of reservoirs each extending radially in alignment with the corresponding blade member of the first split body to define spaces to be filled with molten synthetic resin in a state where the first and second split bodies are assembled together.

Abstract: An axial flow gas turbine comprises a turbine and a turbine exhaust section. The turbine comprises a turbine nozzle containing a low pressure turbine stage having an annular row of stator vanes (V2) followed in axial succession by an annular row of rotor blades (B2). The low pressure turbine stage is characterized by the following parameters: the ratio of vane airfoil pitch to vane airfoil axial width (P/W) at the root end of the vane airfoil (V2) is in the region of 1.0 to 1.2, preferably about 1.12; the ratio of blade airfoil pitch to blade airfoil axial width (P/W)at the root end of the blade airfoil (B2) is in the region of 0.6; the ratio of blade diameter at the tip end of the blade airfoil to blade diameter at the root end of the blade airfoil (blade tip/hub diameter ratio) is in the region of 1.6-1.8, preferably about 1.72; and the ratio of the axial length of the exhaust section to the blade airfoil height (L/H) is no greater than a value in the region of 4:1, preferably 3:1.

Abstract: A shroud for the support of vane roots 1 of variable stator vanes 2 in the high-pressure compressor of a gas turbine includes a forward shroud segment 3 and a rearward shroud segment 4, each with an axially open annulus 5 forming an essentially U-shaped cross-section and with a plurality of axial assembly holes 6, wherein an annular cover 7 is arranged in the area of the opening of the annulus 5 which is provided with assembly openings 8 and tubular supports 9 are provided in the area between the assembly openings 8 of the cover 7 and the associated assembly hole 5 of the shroud segments 3, 4.

Abstract: A pump system, including an impeller and an impeller shaft, which has one end secured to the impeller and another end that may be coupled to a motor to drive the impeller. The pump system further includes a substantially liquid-proof barrier which has an opening through which the impeller shaft extends. The opening in the barrier is sealed with a shaft sealing system that includes a supply chamber fluidly coupled with a cavity. The cavity surrounds, and is at least partially bounded by, the impeller shaft. The shaft sealing system further includes a pressure mechanism that is configured to pressurize lubrication matter contained within the supply chamber and cavity, so as to inhibit liquid from passing along the impeller shaft through the cavity and thereby penetrating the liquid-proof barrier. The pressure mechanism is further configured to vary pressure of the lubrication matter based on atmospheric pressure surrounding the pump system.

Abstract: A permanent magnet alternator (PMA) includes a stator which rotates with a propeller shaft and a rotor which is mounted within the stator and rotates with a gas turbine engine output shaft. The rotor is driven at the relatively high speed of the turbine output shaft while the stator is driven at a relatively slow speed of the propeller shaft as reduced by an in-line gearbox. The great difference in speed between the propeller shaft and the turbine output shaft results in a compact PMA which provides significant electrical power output. As the stator of the PMA rotates with the propeller shaft, power is supplied directly to the rotating hub and blades without the heretofore necessary slip ring and associated electrical transmission components.

Abstract: A turbomachinery apparatus. A turbine is provided with a retainer having a bore step element for turbine wheel retention, and with an aperture manifesting a tailored diameter less than the trim diameter of the turbine, thereby to permit customization of the turbine efficiency characteristic. Various configurations of turbine retainers, with tailored diameter apertures, are disclosed.

Abstract: The inner barrel of a turbine has a plurality of holes for receiving compressor discharge air and flowing such air within the inner barrel. A plurality of replaceable nozzles having internal bores of different diameters are selectively screw threaded into the openings of the inner barrel body enabling, with different diameters, a variation in the flow of compressor discharge air entering the inner barrel.

Abstract: A turbine rotor can fix the heat resisting pipes provided in divided form per the disk member with simple structure for preventing wearing and damaging. The turbine rotor includes a coolant flow path formed through a plurality of disc shaped members respectively stacked across stacking planes in axial direction, a heat resisting pipe divided into a plurality of fractions adapted to be inserted into a portion of the coolant flow path defined in each disc shaped member, spot facing recesses each formed at opening portion of coolant flow path at the same side of the disc shaped member coaxially with the coolant flow path and having greater inner diameter than the opening portion, and ring shaped projecting portions formed at respective end portions of the fractions of the heat resisting pipe and engageable with respective spot facing recesses.

Abstract: A gas turbine blade includes an inlet edge region of a platform. Eroded into it is a slot which runs parallel to the flow-on edge and into which cooling air is introduced in an impact-cooled manner from the platform under side and is discharged in a film-cooling manner from the platform top side. This results in an efficient cooling system for the flow-on edge region of the platform. The method for producing a gas turbine blade includes producing ducts leading into the slot using laser drilling, the slot wall of the slot being protected by a Teflon strip.

Abstract: A cylindrical blade for a rotor of the purely radial type of a centrifugal compressor with a medium flow coefficient comprises a first surface (3) of the pressure side and a second surface (5) of the suction side of equal curvature, both having generatrices parallel to the axis (Z) of rotation of the rotor, in which the line (7) of curvature of the said surfaces (3, 5) is defined, in a Cartesian reference system, by the ratio between the coordinates of a discrete set of points (9) belonging to the line and the outer radius (R) of the rotor (10).