Abstract: A portable air blower includes a blower fan, a drive unit for driving the blower fan, a casing for covering at least the blower fan and having a side wall with an air intake opening defined therein, and a covering unit for covering the air intake opening. The covering includes an air intake grille fitted to the casing and operable to permit an air to pass therethrough into the air intake opening, but to block foreign matters off therefrom, and a protective shroud held in overlapping relation with the air intake grille for covering the air intake grille on one side of the air intake grille opposite to the air intake opening. The air intake grille has an outermost area having a circumferential edge, which is positioned substantially radially inwardly of an outer peripheral edge of the protective shroud.

Abstract: A system for providing low cost fluid pressurization without consumption of limited natural resources, pollution, or greenhouse gas emission, and is independent of wind conditions. Additionally, the system of the present invention includes a venturi-like collar positioned at the top of one or more stacks increasing air flow.

Abstract: A compressor of a gas turbine engine comprises blades 2, 4 provided on blade platforms 8, 12 of a rotor. Stator vanes 20 lie between the blades 2, 4 and are connected to a vane support structure 22. Sealing rings 38 are secured to the vane support structure 22 to restrict air flow into stator wells 36 on each side of the vane support structure 22. The sealing rings 38 are made from a flexible material so that they deflect on installation of the vane support structure 22 in a direction radially inwards between the adjacent blade platforms 8, 12.

Abstract: A turbine rotor blade for a gas turbine engine that includes a five-pass spiral serpentine flow cooling circuit with a first channel extending along the pressure side of the blade, a second channel extending along the suction side of the blade and connected to the first channel at the airfoil tip, a third channel extending along the pressure side and connected to the second channel in the root portion, and fourth channel extending along the suction side and connected to the third channel at the blade tip, and a fifth channel extending along the trailing edge and discharging cooling air through exit holes. The first and second channels are opposite to each other and have the same chordwise length, and the third and fourth channels are opposite to each other and have the same chordwise length to form a spiral flow path between the second and third channels and between the fourth and fifth channels. All five channels are connected in series to form the serpentine flow path.

Abstract: A system and method is provided for detecting and controlling rotating stall in the diffuser region of a compressor. A pressure transducer is placed in the gas flow path downstream of the impeller, preferably in the compressor discharge passage or the diffuser, to measure the sound or acoustic pressure phenomenon. Next, the signal from the pressure transducer is processed either using analog or digital techniques to determine the presence of rotating stall. Rotating stall is detected by comparing the detected energy amount, which detected energy amount is based on the measured acoustic pressure, with a predetermined threshold amount corresponding to the presence of rotating stall. Finally, an appropriate corrective action is taken to change the operation of the compressor in response to the detection of rotating stall.

Abstract: A fan comprises an impeller and a motor. The impeller has a hub, a plurality of blades and a plurality of reinforced elements. The blades are disposed around the hub. At least one reinforced element is disposed on the active surfaces of two adjacent blades. The blades and the reinforced elements are integrally formed as a single piece. The motor connects to the impeller for driving it to rotate.

Abstract: A seal assembly (118) mounted within a nonrotatable static inner support structure (16) for engagement with an axial seal face surface (114) and a radial seal face surface (116). The radial seal (120) engages the axial seal face surface and the axial seal (122) engages the radial seal face surface. The seal assembly provides minimal leakage of core airflow to increase the tip turbine engine operating efficiency.

Abstract: The present invention broadly comprises a cone connection assembly for a torque converter, including: a first surface operatively arranged for connection to a crankshaft and a second surface on a cover of the torque converter. The first and second surfaces are arranged to be engaged and the first surface is arranged to transfer torque to the second surface via the engagement of the first and second surfaces. In some aspects, the crankshaft comprises a longitudinal axis, the first surface is disposed about the longitudinal axis, the cover comprises an outside surface, and the outside surface comprises the second surface. In some aspects, the first and second surfaces are arranged to be frictionally engaged or the first and second surfaces have complementary surface features and the first and second surface features are arranged to interlockingly engage.

Abstract: A housing is disclosed for a compressor having a duct defining a main gas flow axis and blades that draw a fluid through the duct. The blades impart to the fluid a momentum along a main gas flow direction and a swirl. The housing includes a volute configured to extend substantially circumferentially around and fluidly communicate with the duct (at a first location). The volute may be configured to direct a fluid portion flowing thereinto from the duct to have a velocity with a component in a first circumferential direction generally aligned with the swirl. The housing may also include at least one conduit, such as a pipe, in fluid communication with the first volute. The conduit may be configured to redirect the fluid portion to have a velocity with a first component along the main gas flow axis in a direction opposite the main gas flow direction and a second component in a second circumferential direction opposite to the first circumferential direction.

Abstract: A casing assembly for a compressor includes an internal compression assembly with a shaft and at least one impeller disposed on the shaft. The casing assembly includes an inlet body segment having a fluid inlet, an outlet body segment having a fluid outlet, and a number of intermediate body segments selected from a plurality of intermediate body segments, which are preferably preformed. The intermediate segments are disposed between the inlet and outlet segments to form the casing and each has an inner circumferential surface defining an interior chamber section, the chamber sections collectively defining at least a portion of a compressor chamber sized to receive the compression assembly. Preferably, the intermediate segment inner surfaces have equal inside diameters and are generally coaxially aligned. As such, the inner surfaces collectively define a portion of continuous compressor support surface of a desired axial length for supporting the compression assembly.

Abstract: A vapor lock in a fuel pump can be prevented by reducing the formation of vapor within the fuel. A first group of concavities may be formed in an inner circumferential region of an intake side face of an impeller, and a second group of concavities may be formed concentrically in a region outside of the first group of concavities. A third group of concavities that communicates with the second group of concavities may be formed in a discharge side face of the impeller. The impeller is housed within a casing. A first groove that faces the first group of concavities and a second groove that faces the second group of concavities may be formed in the face of the casing that faces the intake side face of the impeller. A third groove that faces the third group of concavities may be formed in the face of the casing that faces the discharge side face of the impeller.

Abstract: The invention provides a rotary wing aircraft helicopter vehicle rod end and method of making a rod end. The rotary wing aircraft rod end includes a nonelastomeric inner member having an outer bonding surface segment and an axial bore with a center bore axis, a nonelastomeric outer member having an inner bonding surface segment and an axial bore center bore axis, and molded in place alternating elastomeric shims and nonelastomeric shims connecting the nonelastomeric inner member to the nonelastomeric outer member. The rod end includes a first inner elastomeric shim bonded to the nonelastomeric inner member outer bonding surface segment and to a first inner nonelastomeric shim and a second outer elastomeric shim bonded to the nonelastomeric outer member inner bonding surface segment and to a second outer nonelastomeric shim. The nonelastomeric inner member has a molded misalignment rotary wing aircraft rod end orientation with the outer nonelastomeric outer member.

Abstract: A turbine blade for use in a gas turbine engine, where the turbine blade is made from a spar and shell construction in which a thin walled shell is held in place between the blade tip and the platform by only a mechanical fastener without using any bonding, welding or brazing. The spar is connected to an attachment by a tie bolt, and a separate platform is secured, over the attachment t in which the shell is held against. This provides for a thermally free platform and shell connection. With this arrangement, the shell is held under compression within the 2% yield stress range such that the turbine blade shell can have an infinite life. Also, the turbine blade is much lighter than prior art blades. As a result, the spar and shell blade produces less stress on the rotor disk during engine operation.

Abstract: Apparatus for harnessing energy from wind comprises upper and lower continuous-loop trackways defining a continuous loop path and a series of connected, movable wind foils. Each wind foil has a leading edge mast engaging and guided by the upper and lower trackways. Each wind foil is movable between first and second orientations when moving along first and second portions of the path. A second example comprises a support structure having upper and lower closed loop trackways having inner and outer trackway rails and defining a closed loop path which guides a series of connected trolleys. Each trolley has a roller mounted to a roller support. The roller is guided by the rails of the upper and lower trackways. Sail assemblies each have a mast and a sail extending from the mast, with the upper and lower ends of the mast mounted to and supported by upper and lower trolleys.

Abstract: A bleed air cooler assembly of a gas turbine engine comprises a cooler body defining a fluid passage therein and a connector detachably affixed with the cooler body installed in an annular bypass air passage.

Abstract: A retention device for axially retaining a rotor disk flange, the device including a split annular retaining ring. The ring has an external face bearing against an internal face of the rim, thereby resulting in a first axial force, an internal face bearing against an external face of the root, thereby resulting in a second axial force, the axial forces being radially offset relative to each other, and an outer face bearing against an inner face of the base of the flange, thereby resulting in a radial force. The outer face of the ring presents an annular setback in such a manner that the radial force is situated in a plane that is offset axially relative to a radial plane passing through the center of gravity of the ring so as to obtain mechanical equilibrium between the forces acting on the ring.

Abstract: The present invention broadly comprises a blade for a torque converter stator including a body, a first end, and a second end; a stator blade assembly; and a stator for a torque converter including a plurality of blades, a housing, and a core ring. The first end is arranged to engage the housing and the second end is arranged to engage the core ring. In some aspects, the blade is stamped or the body is arcuate. The assembly includes a plurality of separate blades. In some aspects, each blade is stamped or bodies for adjacent blades at least partially overlap with respect to a radial plane through an axis for the stator. In some aspects, an axial opening between blades widens radially outward or inward.

Abstract: A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may be positioned in an endwall attached to the turbine airfoil. The endwall may include a submerged endwall cooling channel at the intersection between the generally elongated airfoil and the first endwall. The second endwall attached to the endwall on an end generally opposite to the first endwall may have a submerged endwall cooling channel as well. The submerged endwall cooling channels may include film cooling orifices to form vortices of cooling fluids to enhance cooling capacity of the cooling system of the turbine airfoil.

Abstract: An exhausting system and an exhausting pump connected to a processing chamber of a substrate processing apparatus are provided. The exhausting pump is provided with at least one rotary blade and a cylindrical intake part disposed at the processing chamber side from the rotary blade. The exhausting pump includes a reflecting device disposed inside the intake part and having at least one reflecting surface oriented to the rotary blade.

Abstract: A system and method for reducing vibration and wear to adjacent platform surfaces and mounting locations of a vane segment in a gas turbine engine is disclosed. The present invention seeks to improve the interaction between mating faces of adjacent gas turbine vane assemblies by increasing the surface area where contact between the adjacent vanes occurs, so as to increase the damping capability and reduce the wear to the mating surfaces.