Abstract: A system for ventilating a downstream cavity of an impellor of a centrifugal compressor in a turbomachine, this system including flow diversion system mounted fixedly in the downstream cavity of the impellor in order to divert the ventilation air taken from the outlet of the compressor and cause it to circulate radially from the inside to the outside along the downstream face of the impellor.

Abstract: A gas turbine engine assembly is provided. The gas turbine engine assembly includes a high-pressure compressor including a first rotor and a second compressor rotor disposed downstream from the first rotor, a high-pressure turbine coupled downstream to the compressor by a first shaft, and an air directing assembly coupled between the first and second compressor rotors for selectively channeling airflow discharged from the first compressor rotor through the first shaft. A method of assembling a gas turbine engine is also provided.

Abstract: A submersible pump, and method of making the submersible pump, is disclosed. The pump comprises a housing, a plurality of impeller stages serially disposed in the housing from a bottom impeller stage to a top impeller stage, an impeller bypass hole extending through one of the impeller stages and a housing bypass hole extending through the housing radially outwardly from one of the impeller stages.

Abstract: Apparatus and methods are presented for mixing a high temperature steam, perhaps leaked from an upstream turbine, with the cooler steam from a lower temperature, downstream turbine and introducing the mixture into the downstream turbine.

Abstract: Devices for intaking gases from the boundary layer through ducts hollowed out in blades. These devices are suitable for variable setting blades, installed on the stator using pivots. The seal is maintained despite the variation in the relative position between the moving pivots through which ducts pass, and the fixed intake header pipe.

Abstract: A turbine intake pressure release structure to control pressure release between a throttle and a first turbine boosted pressure outlet includes a pressure release valve which has a first pressure orifice, a second pressure orifice and a housing chamber, at least one controller which has a pressure detection end and a driven portion and a switch duct which has a first end opening, a second end opening and a third end opening. The first end opening is connected to a third turbine boosted pressure outlet. The second end opening leads to the atmosphere. The third end opening is connected to the second pressure orifice. The driven portion runs through the switch duct to close the second end opening through the driven portion drive a membrane to a first position or closes the first end opening through the driven portion to drive the membrane to a second position.

Abstract: A system for controlling the operating lines of a gas turbine engine comprising a compression system which compresses an incoming flow of a gas, a bleed system which extracts gas from a bleed location in the compression system prior to the gas entering a throttling orifice, a recirculation system which reintroduces at least a portion of the gas extracted by the bleed system into a feed location in the compression system or upstream from it, a control system which controls the recirculated gas such that the operating lines of the compression system are changed such that the stall margin of the compression system is increased.

Abstract: A core case section for a gas turbine engine a multitude of discreet radial extending 2.5 bleed ducts defined in part by a structural wall.

Abstract: A turbine power generation system with enhanced cooling provided by a stream of carbon dioxide from a carbon dioxide source and a method of using a stream of carbon dioxide to cool hot gas path components. The turbine power generating system includes a compressor, a combustor, a turbine, a generator, and at least one shaft linking the compressor and turbine and generator together such that mechanical energy produced from the turbine is used to drive the compressor and the generator. Carbon dioxide that is sequestered from the exhaust of the turbine may be stored and injected back into the turbine to cool hot gas path components of the turbine.

Abstract: A method and device for reducing noise and vibrations in a suction pipe (1) in a reaction-type hydropower turbine. The suction pipe (1) comprises one or more nozzles (2) for injection of a working medium through the nozzles (2) into the suction pipe (1). Each nozzle is arranged at an angle ? relative to a horizontal plane perpendicular to the longitudinal axis (4) of an inlet (3) of the suction pipe (1) and at an angle ? relative to a horizontally defined tangent (6) at the point of intersection between each nozzle (2) and the suction pipe (1).

Abstract: A bleed valve assembly for discharging bleed air into a gas turbine engine bypass plenum includes a bleed flow duct, a bleed valve, and a flow deflector. The bleed flow duct is contoured such that it delivers uniformly flowing bleed air to the flow deflector when the bleed valve is in the open position. The flow deflector has a plurality of openings formed therein. Each opening fluidly communicates the bleed air flow passage with the bypass plenum. A portion of the openings are oriented at a discharge angle such that bleed air is discharged from each opening in a direction that does not have a vector component in the direction in which air is flowing in the bypass plenum, and another portion of the openings are oriented to provide stress relief to the deflector.

Abstract: An exhaust turbo supercharger is provided that is able to effectively prevent exhaust gas that has flowed into between a turbine housing and a bearing housing from leaking to outside of the device, while allowing an excellent level of workability in assembly and disassembly. Included is a turbine housing, into which exhaust gas from an internal combustion engine is introduced; a turbine wheel which is provided within the turbine housing and which is rotation-driven by the exhaust gas; a turbine shaft, one end of which is inserted into the turbine housing, and to which the turbine wheel is attached; a bearing which supports the turbine shaft; and a bearing housing which is connected to the turbine housing and inside of which the bearing is housed.

Abstract: A submersible pump, and method of making the submersible pump, is disclosed. The pump comprises a housing, a plurality of impeller stages serially disposed in the housing from a bottom impeller stage to a top impeller stage, an impeller stage bypass hole extending through one of the diffusers and a housing bypass hole extending through the housing radially outwardly from one of the impeller stages.

Abstract: A turbofan engine is provided that includes a core nacelle at least partially surrounded by a fan nacelle. The core nacelle includes a reflex nozzle providing a core exit. The core nacelle includes a contour on its exterior surface upstream from the reflex nozzle. The contour is generally conical and tapers toward the core exit at a first slope. The reflex nozzle tapers toward the exit at a second slope that is less steep than the first slope. The reflex nozzle includes a generally linear portion. In one example, the reflex nozzle is provided by a generally cylindrical extension that sufficiently turns the bypass flow away from the core exit so that the core flow does not become choked.

Abstract: An axial compressor comprises a stator component and a rotor component, which cooperate to perform work on a fluid flow in a primary flow-passage defined by the stator and rotor components, the stator component and the rotor component further defining a secondary flow-passage which interconnects a higher pressure region and a lower pressure region of the primary flow-passage, the rotor component being provided with at least one secondary rotor element which, in normal operation of the machine, pumps a bypass flow of fluid through the secondary flow passage from the lower pressure region to the higher pressure region.

Abstract: Annular or ring-segment-shaped cavities (2, 7) which are formed in particular in multi-shell (11; 12, 13) casings of turbomachines are preferably provided with suitable means for compensating for forming temperature stratifications. According to the invention, an overflow passage (14) connects two points of the cavity to one another which are situated in different circumferential positions. Arranged in the overflow passage (14) is an ejector (17) which can be operated with a motive fluid and which serves to drive a flow through the overflow passage from an upstream end (15) to a downstream end (16).

Abstract: A vacuum pump (100) comprises a first set (106) of turbo-molecular stages, a molecular drag stage (112), a first inlet (120) through which fluid can pass through the first set (106) of stages and the molecular drag stage (112) towards a pump outlet (116), second and third sets (108, 110) of turbo-molecular stages located between the first set (106) and the molecular drag stage (112), a second inlet (122), the second and third sets (108, 110) being arranged such that fluid entering the pump through the second inlet (122) is separated into two streams each flowing through a respective one of the second and third sets (108, 110), and conduit means (126) for conveying fluid passing through the first set (106) and one of the second and third sets (108, 110) towards the outlet (116).

Abstract: The wind generating device employs modules each having two turbines. Each of the turbines employs two rotors, coaxially aligned and arranged one downstream from the other. The arrangement includes a proximal channel with a leading portion having decreasing radius toward the first rotor which acts as a collector and a following portion connecting fluidly the first and second rotor and a distal channel which is separate from the proximal channel and opens into the following portion thereby adding to the airflow to the second rotor. Downstream from the second rotor is a diffuser with radius increasing with distance from the rotor. The device includes mounting modules vertically stacked which allows for yaw responsive to wind. The device further includes mounting the modules on a tower.

Abstract: A vortex-flow blower device includes an impeller having a plurality of fins, a blower housing that has a vortex flow chamber for accommodating the impeller and extends from a start point on a side of a the fluid inlet port to an end point on a side of a fluid discharge port along the plurality of fins, a partitioning portion that blocks a communication between the end point and the start point in the vortex flow chamber, and a thermal fuse that is provided in the blower housing. The thermal fuse can be fused by a temperature rise so as to discharge the fluid on the side of the fluid discharge port to an outside, or communicate with the side of the fluid discharge port to the side of the fluid inlet port in the vortex flow chamber when the thermal fuse is fused.

Abstract: A steam turbine includes, in one exemplary embodiment, a rotor and a plurality of bucket stages coupled to the rotor with each bucket stage including a plurality of circumferentially spaced buckets coupled to the rotor. The steam turbine also includes a diaphragm assembly surrounding the rotor and the bucket stages, and an outer casing disposed about the rotor and diaphragm assembly. The diaphragm assembly includes a plurality of nozzle stages located between the bucket stages, a circumferentially extending groove, with the groove located upstream of one of the bucket stages and between that bucket stage and an adjacent nozzle stage, a circumferentially extending extraction chamber, and at least one first bore extending from the groove to the extraction chamber. The diaphragm assembly also includes at least one second bore extending from the extraction chamber through an outer surface of the diaphragm assembly.

Abstract: A centrifugal compressor is modified by forming a bypass between the leading edge of the compressor diffuser and a point downstream from the throat of the diffuser. The bypass may be unidirectional or bi-directional. In a bi-directional embodiment, an operable flow range of the compressor can be widened in both directions of a compressor map, i.e., extending both the surge and choke margins of a compressor at the expense of normal operating efficiencies. In a unidirectional bypass embodiment the flow range may be increased only in one direction, but there is no diminishment of efficiency of the compressor at normal operating conditions. The modification provides a simple expedient for increasing flow range without a need to redesign a compressor.

Abstract: Acoustic noise from relatively high pressure gas flows as a result of opening for example a bypass valve in a gas turbine engine can cause problems. By provision of an acoustic apparatus incorporating an inner chamber where there is a pressure reduction and then a chamber divider surface incorporating small apertures with a wide spacing distribution an upward shift in acoustic frequency of the gas flow is achieved beyond normal human comprehension. An outer chamber is provided to receive the fine gas flow jets from the apertures in the chamber divider surface for further pressure reduction and low pressure release through wider apertures in an exit surface.

Abstract: The invention relates to a mixer (100) for a separate-stream nozzle of a turbojet, the mixer being designed to mix a hot inner stream from the combustion chamber of the turbojet with a cold outer stream from the fan of the turbojet. The mixer comprises an inner shroud (120) defining a flow channel for said hot inner stream, an outer shroud (110) disposed around the inner shroud (120) and co-operating therewith to define a flow channel for said cold outer stream, and a lobed structure (130) having lobes (1321, 1322) extending longitudinally from the trailing edges (110a, 120a) of said shrouds. The lobed structure (130) is made of a ceramic matrix composite material and is attached to the outer shroud (110) by flexible fastener tabs (140).

Abstract: A method and system for assembling a turbine is provided, wherein an annular nozzle carrier is positioned radially inwardly from a casing such that a cavity is defined between the nozzle carrier and the casing. The method and system also includes a flange that is extended from at least one of a leading edge of the annular casing and a leading edge of the nozzle carrier, and a seal ring that is extended between the nozzle carrier and the casing such that the seal ring seals the cavity, wherein the seal ring is positioned between the flange and at least one of the nozzle carrier and the casing.

Abstract: A compressor assembly (304) includes a compressor housing (312) having a main air inlet (324) and an annular wall (328) defining an inducer bore (325). A secondary inlet passage (322) is disposed around the inducer bore (325). The secondary inlet passage (322) has an inlet slot (320) operatively intersecting the inducer bore (325) to permit the entry of a fluid thereinto through an inlet port (327). The inlet slot (320) advantageously defines an augmented inducer diameter region (331). Preferably the secondary inlet passage (322) may be selectively partially or completely isolated from the main air inlet (324). A compressor wheel (318) is located in the compressor housing (312) and has a stepped portion (330) formed by at least one plurality of vanes (238) operatively associated with the augmented inducer diameter region (331) adjacent to the inlet slot (320) of the housing (312) to receive fluid therefrom.

Abstract: In one embodiment a gas turbine engine is disclosed having a heat exchanger at least partially disposed in a bypass duct. In one form the gas turbine engine is a high bypass ratio engine. The heat exchanger may be coupled with a directed energy weapon to provide coolant flow and regulate the temperature of the directed energy weapon. Other devices may also be coupled with the heat exchanger, either as an alternative to in addition to the directed energy weapon.

Abstract: A radial fan (1) with a housing (2) and a fan impeller (3) disposed therein, an air inlet (4) and an air outlet (5) is provided, a pressure space (6) being formed between the latter, and in front of the air inlet (4) a laminar element (7) being disposed which, in a bypass (8) formed therein, has a sensor (9) for recording at least one parameter of the medium flowing through the air inlet (4).

Abstract: A by-pass turbofan gas turbine engine, comprises: a by-pass fan with a by-pass fan outlet; a generally annular core engine duct with a core engine duct inlet coupled to the by-pass fan outlet and a core engine duct outlet; a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct with a by-pass duct inlet coupled to the by-pass fan outlet and a by-pass duct outlet; an upstream axial compressor with an axial upstream compressor inlet coupled to the core engine duct outlet and an axial upstream compressor outlet; a downstream radial compressor with an axial downstream compressor inlet coupled to the upstream compressor outlet and a radial downstream compressor outlet; a generally annular recuperator with a cool side inlet coupled to the downstream compressor outlet, a cool side outlet, a warm side inlet and a warm side outlet; a generally annular combustor with a combustor inlet coupled to the recuperator cool side outlet and a combustor outlet; a radial turbine wit

Abstract: A transition duct for a gas turbine includes a tubular body having a forward end and an aft end, the aft end surrounded by a frame component; an interior closure band within the aft end, covering interior top, bottom and side wall surfaces of the frame; and a plurality of cooling channels between the frame and the closure band, each having an inlet and an outlet at the forward and aft ends, respectively.

Abstract: A fluid flow machine has a main flow path 2 which is confined by a hub 3 and a casing 1 and in which at least one row of blades 5 is arranged. A gap 11 is provided on at least one blade row 5 between a blade end and a main flow path confinement, with the blade end and the main flow path confinement performing a rotary movement relative to each other. At least one reversing duct 7 is provided in the area of the blade leading edge in the main flow path confinement at a discrete circumferential position. The reversing duct 7 connects two openings 12, 13 arranged on the main flow path confinement.

Abstract: A cooling system for a turbine exhaust assembly comprises an annular case, a flowpath ring and a splash plate. The flowpath ring is coaxially disposed within the annular case. The splash plate extends axially between the annular case and the flowpath ring. A plurality of cooling fluid apertures is formed in the annular case, in order to provide cooling fluid flow onto the splash plate. A plurality of impingement holes is formed in the splash plate, in order to provide impingement flow onto the flowpath ring.

Abstract: An apparatus for routing fluid in a steam turbine is provided. The steam turbine includes a stage comprising a plurality of buckets secured to a rotor. The rotor is configured to rotate in response to a first volume of fluid flowing from an inlet passageway past the plurality of buckets. The apparatus includes a member having a fluid passageway extending therethrough. The fluid passageway includes a first end in fluid communication with a discharge side of the stage of the steam turbine. A second volume of fluid comprising a portion of the first volume of fluid is received into the fluid passageway at the discharge side of the stage and is discharged out of an outlet of the fluid passageway. The outlet is in fluid communication with a region between an upstream side of the stage and a sealing member disposed against the rotor. The region receives a third volume of leakage fluid from the upstream side of the stage.

Abstract: A pump or turbine is disclosed which includes a housing provided with at least one chamber, a rotor, which is rotatably mounted on a shaft in the chamber, an inlet, which communicates with the chamber at least at the location of the shaft, and an outlet channel, which communicates with the chamber at least at the periphery of the rotor. The pump or turbine moreover comprises at least one bypass channel, a first end of which opens into the outlet channel of the pump and a second end of which forms an inlet. The bypass channel may be used for increasing the propelling force or for pumping slurries, for example.

Abstract: A compact, single shaft gas turbine gas generator uses a high pressure ratio dual-entry single stage centrifugal compressor, can combustors, and a radial inflow turbine with the compressor configured to achieve an overall pressure ratio of about 12:1 or greater and Mach Numbers less than or equal to about 1.4. The radial inflow turbine is configured to provide an expansion ratio of about 4:1 to about 5:1, to provide partially expanded combustion gases to a free-power turbine or an expansion nozzle, in a work-producing engine configuration. A ball bearing assembly in front of the compressor is used in conjunction with a thrust piston assembly to take up turbine thrust load, while a radial tilt pad bearing assembly is used in front of the turbine. A collector with scroll-shaped sector portions collects compressed air from an annular vaned diffuser, and respective crossover ducts channel the collected diffused compressed air from each sector portion to a plenum feeding can combustors.

Abstract: A turbofan engine control system and method includes a core nacelle housing (12), a compressor and a turbine. A turbofan is arranged upstream from the core nacelle and is surrounded by a fan nacelle (34). A bypass flow path (39) is arranged downstream from the turbofan between the core and fan nacelles. The bypass flow path includes a nozzle exit area (40). A controller (50) detects at least one of a take-off condition and a landing condition. The controller changes effectively the nozzle exit area to achieve a thrust vector in response to the take-off and landing conditions.

Abstract: A turbocompressor flow structure comprises a ring chamber which is arranged concentrically to an axis of a turbocompressor in an area of free blade/vane ends of a rotor blade ring/vane ring and is adjacent radially to a main flow channel. A ring chamber is provided which is bordered by a front upstream wall, a rear downstream wall and a wall that runs essentially axially. Baffle elements are arranged in the ring chamber and the ring chamber permits flow penetration in a circumferential direction in a front and/or rear area. At least one opening is provided in the area of the wall that runs essentially axially or in the area of the upstream wall and permits flow penetration out of the ring chamber, at least one compressor chamber being provided to accommodate this outgoing flow.

Abstract: A turbomachine with fluid removal, having at least one stator and at least one downstream rotor, with the stator being provided with stationary blades (1) and the rotor comprising several rotor blades attached to a rotating shaft, with a casing (2) confining the passage of fluid through the rotor and the stator in the outward direction, wherein, in an area of at least one blade (1) of the stator, a provision for fluid removal is provided adjacent to a suction side (3) of the blade (1).

Abstract: An air circulation method in a turbomachine compressor includes minimizing an inner flowpath between two adjacent blades by providing labyrinths on an inner casing between the two adjacent blades, and sucking in air from the minimized inner flowpath through a radially inner orifice of a vane faced by the labyrinths. The method further includes directing the sucked in air through the vane, bleeding the air from the vane through a radially outer opening of the vane and through an orifice of an outer casing. The air is collected from the vane into a manifold outside the compression stage. A compressor arrangement for circulating air includes a suction device for sucking in air present in the inner flowpath between labyrinths and the vane, and for sending the air into the vane of the stator. The arrangement also includes a device for bleeding air in the vane of the stator and for sending the air outside the compressor.

Abstract: A turbine bypass control method includes: a high-pressure side pressure controller configured to output a first operation amount signal corresponding to a valve opening; a low-pressure side pressure controller configured to output a second operation amount signal corresponding to a valve opening; a high value selector configured to output as a high value operation amount signal, one of the first operation amount signal and the second operation amount signal which indicates a larger opening; a first signal switching unit configured to receive the high value operation amount signal and the second operation amount signal and output a first bypass valve operation amount signal; a second signal switching unit configured to receive the high value operation amount signal and the first operation amount signal and output a second bypass valve operation amount signal; and a rapid opening controller.

Abstract: One form of the present invention contemplates an apparatus comprising a gas turbine engine core, a gearbox accessory mounted to the engine core and substantially enclosed by an inner fairing; a nacelle having a plurality of panels, wherein the nacelle panels substantially enclose and overlap at least a portion of the inner fairing; and a bypass duct defined between an exterior surface of the inner fairing and an interior surface of at least some of the nacelle panels.

Abstract: A turbomachine compressor comprises at least one plurality of moving blades and spaced apart therefrom in an axial direction relative to a central longitudinal axis of the turbomachine, a plurality of stationary vanes, and a stationary casing surrounding said plurality of moving blades and including a plurality of bleed holes centered in the range 5% to 50% of the blade chord length and having a diameter less than or equal to 30% of the blade chord length, each bleed hole sloping at two angles of inclination relative to the central longitudinal axis. Advantageously, each bleed hole has a first axis of inclination presenting an angle ? relative to the central longitudinal axis lying in the range 30° to 90°, and a second axis of inclination perpendicular to the first and presenting an angle ? relative to the central longitudinal axis lying in the range 30° to 90°.

Abstract: A turbomachine compressor, such as a high-pressure compressor, including air bleed means comprising a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor, a screen sheet of annular shape being mounted radially inside the casing facing a portion of the suction end of the duct so as to make the bleeding of air uniform over 360° around the axis of the compressor.

Abstract: A tip turbine engine (10) and a method of operating the engine provides increased efficiency while eliminating or educing the number of axial compressor (122) stages by moving the core airflow inlet (27) aft of the fan (24). As a result, the core airflow entering the core airflow inlet is the fan exhaust, which is already at an increased pressure. A portion of the fan exhaust is guided radially inward, then axially forward and then radially outward through compressor chambers (72) in the hollow fan blades (28) for further, centrifugal compression.

Abstract: The invention relates to a turbine engine (10), particularly for a helicopter, comprising a gas generator (12) and a free turbine (14) rotated by a gas flow (F) generated by the gas generator. The invention is characterized in that the turbine engine also comprises heating means (26) placed between the gas generator and the free turbine (14), the said heating means (26) being capable of increasing the temperature of the gas flow (f) generated by the gas generator (12) and driving the free turbine.

Abstract: A gas turbine engine system includes a nacelle assembly, a core engine and a mixer disposed between the nacelle assembly and the core engine. The core engine includes a core passage and a core auxiliary duct passage. The core auxiliary duct passage includes an inlet for receiving a portion of a core airflow form the core engine and an outlet for discharging a portion of the core airflow received from the core engine.

Abstract: A system for mixing flows from a compressor is provided. The system comprises an ejector that combines a first flow and a second flow, from the compressor, into a third flow. A bypass flow is connected between the first flow and the third flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the respective pressures and temperatures of the bypass flow and the third flow.

Abstract: A composite gas turbine engine duct receives a support ring that operates as an interface arrangement for attachment of engine system components. The support ring interfaces with the composite duct through a fastener shear load arrangement to provide a structurally sound interface which minimizes the risk of ply delamination.

Abstract: An engine system incorporating an air breathing, reciprocating internal combustion engine having an inlet for air and an exhaust for products of combustion. A centripetal turbine receives products of the combustion and has a housing in which a turbine wheel is rotatable. The housing has first and second passages leading from the inlet to discrete, approximately 180°, portions of the circumference of the turbine wheel. The passages have fixed vanes adjacent the periphery of the turbine wheel and the angle of the vanes in one of the passages is different than those in the other so as to accommodate different power levels providing optimum approach angles between the gases passing the vanes and the blades of the turbine wheel. Flow through the passages is controlled by a flapper valve to direct it to one or the other or both passages depending upon the load factor for the engine.

Abstract: A burn resistant composite article includes at least one composite layer having first fibers within a first organic resin matrix. At least one burn resistance layer is disposed adjacent the at least one composite layer. The burn resistance layer includes second fibers within a second organic resin matrix. The composite layer and the burn resistance layer each have an associated thermal resistance, and the thermal resistance of the burn resistance layer is greater than the thermal resistance of the composite layer.

Abstract: A turbocharger system having a compressor housing containing a rotating compressor wheel with a plurality of impellers that define an impeller passageway from an inducer to an exducer. The compressor housing includes an annular upstream housing-portion forming an upstream shroud-wall, and a downstream housing-portion forming a downstream shroud-wall. The a rib supports the upstream housing-portion with respect to the downstream housing-portion such that they are respectively disposed to form an annular bypass port into the impeller passageway between the upstream and downstream shroud-walls. The rib extends along a non-axial path within the bypass passageway.