Abstract: The present embodiment relates to a catalytic combustor for reducing the pollutant emissions of combustion. The catalytic combustor described herein employs a novel heat exchange system for rapidly and economically bringing the combustor to a temperature wherein catalytic combustion may occur with minimal production of toxic products.

Abstract: A can combustor for an industrial turbine includes a transition piece transitioning directly from a combustor head-end to a turbine inlet using a single piece transition piece. In an exemplary embodiment, the transition piece is jointless.

Abstract: In a fuel lance by means of which fuels can be injected, via at least two separate passages, into a combustion chamber alternately or simultaneously at an injection location arranged substantially at the lance tip, reliable operation is achieved, without the risk of flashbacks and also without coking, by virtue of the fact that the fuel lance, in addition to fuel, also passes purge air to the injection location, and that the purge air, at the injection location, is routed between the two fuel systems, in such a manner that these systems are shielded from one another by the purge air.

Abstract: The invention pertains to a seal element for sealing a gap, in particular within a turbo-machinery, between a first component and a second components spaced apart from each other, said first component having a first surface and said second component having an opposing second surfaces. The seal element comprises a support structure and a sealing structure covering at least partially said support structure. The support structure comprises at least two contacting members, each contacting member serves for putting a portion of the sealing structure in contact with one of the surfaces and being capable of following a deformation of said surface. The invention further pertains to a combustion turbine, wherein a gap is formed between a first surface and a second surface, which gap is sealed off by said seal element.

Abstract: The invention is a turbojet propulsion system which includes a compressor section, a turbine section coupled by a shaft to the compressor section, a combustion section mounted between the compressor section and the turbine section, and an exhaust duct coupled to the aft end of said turbine section. A fuel delivery system is incorporated for supplying fuel to the combustion section. A laser assembly provides electromagnetic radiation to the combustion section. An electrical generator coupled to the turbine driven shaft powers the laser assembly.

Abstract: A gas diffusion arrangement (22) for a gas turbine engine (10) is disclosed. The gas diffusion arrangement (22) has an inlet (26) and an outlet (28) for the gas, and comprises diffusion means (32) having an upstream region (38) and a downstream region (40). Distribution means (41) is arranged between the downstream region (40) and the outlet (28) to distribute the gas into a desired flow pattern. The area ratio of the cross-sectional area of the downstream region (40) to the cross-sectional area of the upstream region (38) is greater than 1.5 to 1.

Abstract: A ventricular assistive device (VAD) based on a progressive cavity pump includes a pump housing having an inlet and an outlet, a pump stator contained within the pump housing, a pump rotor rotatably disposed within the pump stator, a motor including a motor rotor contained within the pump housing and a direct drive means connected between the motor rotor and an axial shaft of the pump rotor for rotating the pump rotor. The motor rotates the motor rotor, which in turn rotates the pump rotor through the direct drive means. The rotation of the pump rotor within the pump stator forms a plurality of cavities that carry blood forward through the pump housing from the inlet to the outlet as the motor drives the direct drive means.

Abstract: In a power generation unit, especially in a gasturbo group, a gaseous process fluid is guided in a closed cycle. The gaseous process fluid flows through a compression device (1), a heater (6) and an expansion device (2), especially a turbine. Downstream from the expansion device at least one heat sink (11, 13) is arranged in which the gaseous process fluid is cooled before it is returned to the compressor device (1). At least one heat sink includes a waste heat steam generator in which an overheated amount of steam (26) is generated that is added to the compressed gaseous process fluid. Together with the gaseous process fluid the steam flows through the heater (6) if necessary and is expanded together with it. The expanded steam condenses in the waste heat steam generator (11) and another heat sink (13); the condensate is processed in a filter (16) and is returned to the waste heat steam generator (11) under pressure via a feed pump (18).

Abstract: A multi-position pressurized fluid actuator is mounted for movement in a casing. The actuator includes at least one selectively openable opening at a location corresponding to an intermediate position through which pressurized fluid can be selectively bled from the actuator to permit the actuator to remain in the intermediate position.

Abstract: An inside-out ceiling fan motor has a stator mounted to a downrod with an annular array of stator coils positioned about a rotor axis of rotation. A rotor is rotatably mounted about the stator. The rotor has a plurality of vanes spaced along the rotor periphery and canted at an angle of attack to a plane of rotor vanes rotation oriented normally to the rotor axis of rotation to scoop ambient air into the rotor during fan operation through the stator coils to cool them.

Abstract: An inflator includes a hollow handgrip and an air cylinder having a shaft. One end of the shaft is connected with a piston in the cylinder and the other end of the shaft is provided with a stud extending out of the cylinder. A bottom wall and an opening are arranged respectively at opposite ends of the handgrip. A tapped hole is formed in the bottom wall for locking the stud. Through the opening, the cylinder may be stored in the handgrip to lessen the volume of the inflator. When using the inflator, a user draws the cylinder out of the handgrip and lock the stud to the tapped hole through the bottom end of the handgrip to thereby extend the shaft. Air is pumped out through an outlet of the cylinder by reciprocal axial motion of the shaft.

Abstract: A reciprocating compressor, being small-sized and compact, for compressing hydrogen gas to be used in a fuel-cell car, has a crankshaft, to which an end of a connecting rod is connected. The other end of the connecting rod is connected to a crosshead. To the crosshead are connected a pair of shafts, each extending in directions opposing to each other. To each of the shafts is connected a plunger. The each plunger is received within a cylinder at the tip portion thereof. A pair of plungers moves reciprocally on an almost same axis, and the crosshead is formed in one body.

Abstract: Adaptive model-based control systems and methods are described so that performance and/or operability of a gas turbine in an aircraft engine, power plant, marine propulsion, or industrial application can be optimized under normal, deteriorated, faulted, failed and/or damaged operation. First, a model of each relevant system or component is created, and the model is adapted to the engine. Then, if/when deterioration, a fault, a failure or some kind of damage to an engine component or system is detected, that information is input to the model-based control as changes to the model, constraints, objective function, or other control parameters. With all the information about the engine condition, and state and directives on the control goals in terms of an objective function and constraints, the control then solves an optimization so the optimal control action can be determined and taken.

Abstract: A combustion case for a gas turbine engine. A typical combustion case is generally cylindrical or conical. Apertures penetrate the case, from the outer surface, through the case, to the inner surface. The apertures act as concentration points for stress. To dissipate the stress, bosses buttress the apertures, with each aperture having two bosses: one on the outer surface of the case, and another on the inner surface of the case. The invention eliminates the latter bosses. The invention dissipates stress by providing an array of T-slots on the inner surface.

Abstract: A fluid pump for pumping a volume of fluid under pressure from a fluid source to a fluid dispenser includes an electric motor. A pump drive assembly is operably coupled to the motor for reducing an output of the motor. A pump assembly is operably coupled to the pump drive assembly and is fluidly communicable with the source of fluid, the pump assembly being actuated by the pump drive assembly, the actuation causing the pump assembly to pump the fluid. A single main housing, the main housing in part the pump drive assembly and having a pump housing defined therein, the pump housing being integral, unitary therewith for housing the pump assembly. A method of making a fluid pump for pumping a volume of fluid under pressure from a fluid source to a fluid dispenser.

Abstract: A gas-turbine engine combustion system has a combustor with a burner head having both pilot gas and pilot liquid-fuel injection arrangements, the pilot gas arrangement comprising an annular gallery communicating with a downstream face of the head and a deflecting arrangement adjacent the gallery for directing the pilot gas-fuel towards a longitudinal axis of the combustor and over a central part of the downstream face. The combustion system is designed so that, during both gas- and liquid-fuel operations, the flame front face is located close to the burner head and, during liquid-fuel operation, air is forced across the downstream face to cool the head. Advantageously, the cooling air is made to replace the pilot gas-fuel in the annular gallery, so that it is deflected, like the gas-fuel, and contacts the central part of the downstream face. The burner head also features main gas and liquid-fuel injection arrangements, these communicating with one or more passageways in a radial swirler attached to the head.

Abstract: A combustor for a gas turbine engine having a longitudinal axis therethrough, including an outer liner having a forward end and an aft end, an inner liner having a forward end and an aft end, a first dome formed upstream of the outer liner forward end so as to define a first combustion zone radially oriented to the longitudinal axis, and a dome plate having an outer portion connected to an upstream end of the first dome and an inner portion connected to the inner liner forward end, wherein a second combustion zone is defined by the dome plate, the outer liner, and the inner liner substantially perpendicular to the first combustion zone.

Abstract: A fan in which, on one end of the motor shaft 6 a stepped portion 19 having a small diameter is formed, on which a central portion of the motor yoke 11 is press-fitted and fixed by caulking, thereby the motor yoke is mounted directly on the shaft 6. By such a structure, the conventional boss between the shaft 6 and the motor yoke 11 can be omitted and the structure can be simplified.

Abstract: A screw compressor having balanced axial thrust includes a housing having a fluid inlet and a fluid outlet; a rotor disposed in the housing for receiving low pressure fluid from the inlet and discharging increased pressure fluid from the outlet, the rotor having a discharge end and a motor end; a balance piston arranged to exert a balancing force on the motor end of the rotor; and a conduit for conveying a high pressure fluid to the balance piston so as to exert the balancing force.

Abstract: A combustor dome assembly includes a spectacle plate having an opening formed therein that defines an inner circumferential edge, at least one swirler assembly defining an inner cylindrical surface, and at least one deflector having an outer cylindrical surface. These components are arranged such that the outer cylindrical surface is joined to the inner circumferential edge and to the inner cylindrical surface. One preferred method of manufacturing the combustor dome assembly includes placing a first ring of joining material over the outer cylindrical surface. Then, the outer cylindrical surface is inserted into the spectacle plate opening so that the first ring is sandwiched between a first surface of the spectacle plate and a shoulder formed on the deflector. A second ring of joining material is next placed over the outer cylindrical surface, and a third ring of joining material is inserted into an annular groove formed in the inner cylindrical surface.