Abstract: This invention relates to a cooling air ducting system in the high-pressure turbine section of a gas turbine engine, in which a portion of the air flow which exits from the compressor section of the engine and bypasses the combustion chamber of the gas turbine is ducted via a first pre-swirl system provided in a diaphragm into a pre-swirl chamber arranged upstream of the first stage turbine rotor disk and is fed from this pre-swirl chamber, in particular, to the air-cooled blades of this rotor disk for cooling purposes, and in which another portion of this air flow is applied to the face of the first stage turbine rotor disk via a second air transfer system which, when viewed in the radial direction, is arranged further inward than the first pre-swirl system. According to this invention, the second air transfer system is again provided as a pre-swirl system connecting to the pre-swirl chamber.

Abstract: A bracket includes a housing and a cover attached to the housing. The housing includes a base and first and second side walls extending from opposite sides of the base. The base forms a number of first sills to define a receiving space for engagingly receiving a fan therein. The first side wall forms a pair of first tabs. The second side wall forms a secure plate. The cover forms a pair of second tabs pivotablly attached to the first tabs of the first side wall. A latching plate extends from the cover opposite the second tabs for engaging with the secure plate of the second side wall.

Abstract: An article that is configured to be rotatably mounted includes an embedded hollow cavity into which at least one dampening member is inserted. The dampening member or members frictionally engage the hollow cavity such that relative movement between the dampening member or members and the hollow cavity operates to attenuate vibration that is generated when the article is rotated.

Abstract: A system for supporting bolted upper and lower diaphragms to one another in an outer housing of a turbine includes support screws threaded into bores adjacent opposite sides of the lower shell. The head of each support screw has a threaded bore receiving a set screw. The set screw has a length equal to the depth of the slot in which the head resides in the lower shell, minus a small clearance. With the diaphragms supported by the engagement of the set screw at the lower end with an abutment at the bottom of the slot, the clearance enables the diaphragms to move vertically upwardly, limited by the clearance distance.

Abstract: Blower designs for vented enclosures include an impeller having a plurality of blades. The impeller includes a plurality of blades pivotably coupled to an impeller body. The blades pivot to enable operation in one of a closed and an open state. Air flow between blades is substantially restricted when the blades are in the closed state. Air flow between the blades is permitted when the blades are in an open state. In one embodiment, the pivotable couplings are spring loaded to maintain the blades in the closed state when the impeller rotational speed is below a threshold range. The blades pivot to the open state when the rotational speed exceeds the threshold range.

Abstract: A turbine blade for a gas turbine engine comprises an aerofoil having a suction and pressure side. The pressure side is provided with a reflex curvature at the aerofoil trailing edge region so as to reduce the thickness of the aerofoil in that region.

Abstract: A nozzle lock for circumferentially securing a nozzle segment relative to the engine casing of a gas turbine engine. The nozzle lock includes a thickener pad joined to an outer surface of the engine casing and a locking member disposed in a notch located in the outer band of the nozzle segment. A pin formed on the locking member is press-fit into the casing and the thickener pad.

Abstract: A starter is provided including a housing defining a fluid passageway with an inlet and an outlet. A turbine rotor is supported in the housing and includes blades arranged in the passageway between the inlet and the outlet. The rotor is movable within the passageway at a speed with a fluid exiting the blade toward the outlet. A spoiler is arranged in the passageway between the rotor and the outlet. The spoiler deflects the fluid exiting the blade and reduces the rotor speed. Preferably, the present invention spoiler is utilized to reduce the maximum speed at the no-load condition. The angle, number, position, and other characteristics of the spoiler may be tailored for the particular turbine and a particular speed for which it is desirable to reduce.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a sheet metal seal supported by a bracket secured to the back side and radial inner surfaces of the inner rail. The sheet metal seal has a flexible margin which is preloaded and bears against the annular sealing surface of the nozzle support ring. The bracket is bolted or welded to the inner rail with the sheet metal seal therebetween inhibiting or precluding leakage past the back side of the supplemental seal.

Abstract: A double-seal/oil-reservoir system for motor/pump assembly includes first seal (S1) and a second seal (S2) of a carbon/ceramic ring type that are axially spaced from one another along a drive shaft (24). A containment volume “V” is defined between the first and second seals (S1 and S2) in which an oil or oil-like fluid is contained to prevent seepage or weepage of the fluid circulated by the pump.

Abstract: A multi-functional electric fan comprises a U-shaped brace pivotably mounted to motor, a support for supporting the brace, an arcuate guide mechanism hinged to the support, a transmission mechanism having a plurality of gears and an arm secured to a pin through an opening of the guide mechanism, a transverse post, and a vertical post. Thus fan can pivot transversely and longitudinally by the cooperation of posts, gears, pin, and opening at the same time to reciprocally induce air movement in a transverse, longitudinal, wavy, or fixed direction.

Abstract: An axial/radial three-channel diffuser is provided with two guide vanes for dividing the diffuser into three partial diffusers that are distributed so that the distribution of the surface area over the three partial diffusers in the inlet surface area is uneven. The guide vanes are oriented in accordance with the total pressure field after the last rotating blade row and are arranged at a minimum distance from the trailing edge of the last rotating blade row. Because of its long extension in relation to the channel heights of the partial diffusers, the three-channel diffuser brings about a gentle deflection of the diffuser flow. The diffuser according to the invention results in an improved pressure recovery and increased turbine performance.

Abstract: A blade retaining system for securing rotor blades to a rotor disc used in gas turbine engines includes an inwardly radially extending annular groove defined in the periphery of the rotor disc, intersecting the “fir tree” mounting slots into which the rotor blades are mounted. A resilient split ring is received in both the annular groove of the rotor disc and a groove defined in the bottom end of the root portion of each blade, in order to restrain axial movement of the blade relative to the rotor disc. The resilient split ring under its radial expanding spring force, radially and outwardly abuts the rotor blades and is radially spaced apart to ensure the engagement in both the grooves of the rotor disc and each rotor blade, while permitting disengagement therefrom when required. The resilient split ring is disposed downstream of the cooling air inlets in the bottom end of each rotor blade to direct the cooling air into the inlets in order to facilitate the blade cooling air circulation.

Abstract: An inlet protector or guard that prevents jamming and clogging of a molten metal pump. The guard includes a flat surface having a central opening that accepts a shaft of the molten metal pump. A wall extends from the periphery of the flat surface along a longitudinal axis of the shaft. The wall is sized to fit within an inlet opening of the pump. The wall includes a plurality of openings, forming an inlet through which molten metal can enter a base of the pump. The plurality of openings are small enough to prevent solid particles that are larger than a distance between an impeller of the pump and a pump chamber from entering the pump and large enough to prevent the pump from clogging.

Abstract: One or more particle arrestor rings are mounted in a curved radial flow portion of a gas turbine annular flow passage. The arrestor rings block line of sight paths between the turbine wheel and the annular flow passage outlet. Thus, the arrestor rings substantially inhibit relatively high energy particles from exiting the gas turbine housing, thus substantially inhibiting collateral damage to surrounding equipment and structure.

Abstract: The invention relates to a cast turbine blading unit, in particular a gas turbine guide vane, having an airfoil and a platform region. The platform region is formed by a hot gas platform at the hot gas end and by a load-carrying platform opposite to it. The load-carrying platform accepts the forces so that the hot gas platform can be of thin configuration. There are particularly low thermal stresses.

Abstract: A fluid powered drilling motor adapted for drilling oil wells and other subterranean bore holes. The motor having a rotor and a stator wherein the iron content of the whole motor is less than 0.1% wt. In one embodiment the motor is made of an alloy having a base metal comprising one of copper, nickel, and aluminum plus about 0.05-10 wt % Beryllium. In another embodiment, the motor is made of either 15Ni-8SN—Cu or 9Ni-6Sn—Cu.

Abstract: A fuel pump for pumping fuel from an inlet port to an outlet port. In one embodiment, a housing made up of a body piece and a cover piece encloses an impeller. The impeller has a vaned periphery and an outer ring connected by spokes. An inlet hole is defined within the cover piece for fuel to enter the pump. An outlet hole is defined within the body piece for fuel to exit the pump into an internal chamber. A first main semicircular shaped channel is defined circumferentially into the cover piece and extends in an annular fashion around the cover piece. The body piece has a second main semicircular channel as well as at least one annular groove. In the preferred embodiment of the invention, there are two annular grooves, one connected directly to the second semicircular channel, and one around the peripheral edge of the body piece at the point where it contacts the cover piece.

Abstract: A turbine (4) suitable for use in down-hole drilling and the like, and comprising a tubular casing (11) enclosing a chamber (18) having rotatably mounted therein a rotor (19). The rotor (19) comprises at least one turbine wheel blade arrays (30a) with an annular array of angularly distributed blades (30), and a generally axially extending inner drive fluid passage (14) generally radially inwardly of said rotor (19). The casing (11) also has respective generally axially extending outer drive fluid passage (16) associated with said at least one turbine wheel blade array (30a), and one of the inner and the outer drive fluid passages (14, 16) constitute a drive fluid supply passage and is provided with outlet nozzles (17) formed and arranged for directing at least one jet of drive fluid onto the blade drive fluid receiving faces (31) for imparting rotary drive to said rotor (19).

Abstract: A gas turbine engine fan blade (26) comprises a root portion (36) and an aerofoil portion (32). The aerofoil portion (32) has a convex surface (44), a concave surface (42), a leading edge (38) and a trailing edge (40). The leading edge (38) of the aerofoil portion (32) is formed from a harder material than the regions of the concave surface (42) and convex surface (44) immediately adjacent the leading edge (38) such that the leading edge (38) of the aerofoil portion (32) remains pointed. This improves the efficiency of the fan blade (26) and hence the gas turbine engine (10) and reduces flutter of the fan blade (10).