Abstract: An adjustable bleed apparatus and method for bleeding air to or from the impeller inlet region of a centrifugal compressor through a segmented annular bleed slot. An annular support member, connected to the fixed intake casing, supports a downstream annular shroud segment and an upstream annular shroud segment such that the downstream end of the downstream shroud segment is unconstrained. The spaced-apart distance between the shroud segments defines an annular bleed slot, which is segmented by bridge members. The connections between the shroud segments and the annular support member are configured such that the spaced apart distance of the annular bleed slot is adjustable. The connections between the annular support member and the fixed intake casing are configured such that the running clearance between the downstream shroud segment and the impeller is adjustable independently from the width of bleed slot.

Abstract: A device is provided for pivoting at least one pivotable element in a gas turbine engine between a first and a second position in order to influence a gas flow in an annular gas duct in at least one of the positions. The device includes a moveable annular member which is arranged externally around the gas duct and is connected to the pivotable element in order to effect the pivoting of the pivotable element. The annular member is more specifically arranged to be displaced in a substantially axial direction and arranged to pivot the pivotable element when it is displaced axially.

Abstract: Provision of flow control arrangements which can be switched from high flow restriction to low flow restriction or vice versa are desirable. It is known to use switched vortex valves comprising a vortex chamber having a diverter portion which jets a through flow into either radial presentation to an outlet or tangential presentation with differential flow restrictions. Typically deflection is through cross flows presented from control ports as determined by mechanically actuated and controlled valves. Sensors are required to determine pressure differentials in order to actuate these moving part valves. By providing association between the control ports and an outlet path along with appropriate configuration and sizing of the flow regulators switching states can be provided through the cross flows presented via the flow regulators between the high and low through flow restriction. The flow regulators generally comprise orifice restrictors, diffusers/venturi arrangements or vortex throttles.

Abstract: To provide a turbofan jet engine which is capable of increasing the bypass ratio without increasing the fan diameter, and of reducing air resistance acting on the engine, a front fan duct that discharges air compressed by a front fan to the atmosphere and an aft fan duct that introduces air into an aft fan are disposed such as to change cross-sectional shapes thereof by rotating around a core engine in a counterclockwise direction, so that the cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately posterior to the front fan and a cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately anterior to the aft fan are inverted.

Abstract: A turbofan engine includes a variable area fan nozzle which effectively changes the physical area and geometry within a fan bypass flow path to manipulate the pressure ratio of the bypass flow with a multitude of bladders circumferentially located about a core cowl.

Abstract: A supersonic gas compressor. The compressor includes aerodynamic duct(s) situated on a rotor journaled in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. The convergent inlet is adjacent to a bleed air collector, and during acceleration of the rotor, bypass gas is removed from the convergent inlet via a collector to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is eliminated.

Abstract: The present invention relates to an adjustment device (1) for adjusting a valve or a flap, in particular a pressure nozzle for actuating a bypass valve when a limit charge pressure on an exhaust-driven turbocharger is exceeded, which comprises a single- or multi-part housing (2), in particular a housing (2) having a housing lower part (3) and a housing lid. Essential to the invention is that a clip device (4) is provided, by means of which the adjustment device (1) is fastened to a part (6).

Abstract: There is described a variable geometry turbine having a sliding element (5) for the control of the section throat of the turbine (1) by sliding movement along an axial direction of a turbine wheel (71). The turbine wheel operates to convert a flow of working fluid into mechanical energy. At least one bypass channel (51) is defined in the sliding element (5). The bypass channel is further connected to a turbine wheel outlet area (79) downstream of the turbine wheel for selectively guiding an excess flow of working fluid past the turbine wheel (71), so as to control the operation of the turbine. A use of the variable geometry turbine with a turbocharger for an engine and a method for controlling such turbine is also described.

Abstract: A turbine engine locates an actuator (55) for the compressor variable guide vanes (54a, b, c) at a location remote from the variable guide vanes. The actuator is connected to the variable guide vanes through a torque rod (56) inside an inlet guide vane. The torque rod rotatably drives an activation ring (57) about the engine centerline. The activation ring is coupled to each of the variable compressor vanes via linkage, such that rotation of the activation ring about the engine centerline causes all of the variable compressor vanes to pivot. With this configuration, a tip turbine engine can be more easily provided with variable compressor vanes for the axial compressor.

Abstract: An apparatus and method for improving reduced-load operation of steam turbines. The apparatus may include a number of low pressure sections and a flow control system operable to limit the flow of steam to at least one of the number of low pressure sections. The method may include providing a number of low pressure sections, providing a flow control system operable to limit the flow of steam to at least one of the number of low pressure sections, and operating the flow control system to limit the flow of steam to the at least one of the number of low pressure sections when the load is below a predetermined value.

Abstract: The invention is directed to a turbine (3) for generating power in a drill string (2), including a turbine rotor (10) drivable by a fluid and a bypass device having a first bypass channel bypassing the turbine rotor (10). For varying the volumetric flow through the bypass channel, provision is made for a valve (28) and a control device driven by the fluid and having a drive element (24) by means of which the valve (28) is movable anywhere between a first and a second position. The drive element (24) produces a flow resistance in the fluid flow path downstream from the turbine rotor (10) and downstream from the valve (28) and in the flow direction takes support upon a spring (26).

Abstract: A system for providing air from a multi-stage to a turbine includes a turbine having a high pressure input port and a low pressure input port. The system also includes a compressor having at least one high pressure extraction air output and at least one low pressure extraction air output. A valve is fluidly connected to the at least one high pressure extraction air output, at least one low pressure extraction air output and low pressure input port of the turbine. The valve is selectively operated to fluidly connect the at least one low pressure extraction air output with the low pressure input port during normal operating conditions and fluidly connect the at least one high pressure extraction air output and the low pressure input port during a turn down condition or below design temperature operation to enhance turbine engine performance.

Abstract: A turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.

Abstract: An improved actuating rod end connector is connected with an actuating rod that extends from a turbocharger assembly actuator mechanism. The rod end connector has a body with an opening at one longitudinal end, and the actuator rod is disposed through the opening. An adjustment member is rotatably disposed within the body and has a threaded inside cavity in communication with the opening. The inside cavity is threadably engaged with a threaded outside surface of the actuator rod. The body includes an actuator rod opening disposed therethrough adjacent the adjustment member to receive a section of the actuator rod therein to facilitate contacting the actuator rod disposed within the body from outside of the rod end connector. An attachment opening is disposed through the body to facilitate attachment of the rod end connector with a linkage member, e.g., a linkage member connected with a movable member of the turbocharger.

Abstract: The invention relates to a turbocharger (1) comprising a turbine (2) and a compressor (3), connected to the turbine (2) so as to drive it and having a compressor housing (5) which has a by-pass channel (9) for connecting the compressor outlet with the compressor inlet and a diverter valve (10) which comprises a sealing element (11) having an obturator (12) and a valve face (13), the obturator (12) having a sealing lip (14).

Abstract: A sliding piston cartridge (50) for a turbocharger (20) that is insertable into a bore (44) in the turbine housing (38) as a unit and that includes all of the components of a sliding piston type variable nozzle. The sliding piston cartridge comprises a carrier (52) having a tubular portion that interfaces with the bore of the turbine housing. A sliding piston (62) is disposed within the carrier and makes sliding contact therewith. Vanes (58) are mounted on or formed as a part of the carrier at its upstream end, the vanes extending across a turbine nozzle. The piston slides between a closed position and an open position relative to the carrier. The tubular portion of the carrier can include openings (66) that are progressively uncovered by the piston as it moves toward the open position, to allow additional flow to enter the turbine wheel without passing through the vanes.

Abstract: A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.

Abstract: A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is movable between a plurality of positions to change an effective area associated with a bypass airflow through a fan bypass passage of a gas turbine engine. A protective coating is disposed on the nozzle section and resists change in the effective area of the nozzle section caused by environmental conditions.

Abstract: A two-volute low pressure turbocharger is provided with a VGT mechanism in one turbine volute only.

Abstract: A method for channeling compressed air to a gas turbine engine augmentor is provided. The method includes coupling an annular slide valve to a gas turbine engine separation liner, coupling a valve seat to a gas turbine engine diffuser such that an airflow passage is defined between the annular slide valve and the valve seat, and channeling compressed air to the annular slide valve to facilitate regulating the quantity of fan bypass air channeled to the gas turbine engine augmentor.

Abstract: An exhaust turbocharger is provided which is enhanced in durability and reliability by making the valve body of the waste gate valve to contact uniformly the seat face of the turbine housing at the opening of two exhaust gas bypass passages without affected by the end face of the partition wall partitioning the two bypass passages, thereby preventing generation of vibration and vibration sound (chattering) of the valve body and occurrence of gas leakage due to defective seating of the valve body against the seat face of the turbine housing.

Abstract: A compression and vacuum-producing machine includes a housing, at least one rotating disk having a plurality of blades rotationally supported within the housing, and at least one stationary disk having a plurality of blades fixedly attached to the housing. A drive shaft includes a generally tapered surface and rotatably drives the rotating disks to increase the energy of a fluid stream disposed within the housing. The compression machine includes a transmission in mechanical communication with the drive shaft to convert a rotational input to a desired rotational speed and drive the shaft at the desired speed.

Abstract: In a compressor of a turbocharger of an internal combustion engine comprising a housing with an inflow channel; a compressor impeller arranged in the inflow channel; and a bypass channel which has a first flow opening upstream of the compressor impeller inlet, a second flow opening downstream of the compressor impeller inlet and an axial annular chamber which connects the first and the second flow openings. An axial vane structure is provided in the axial annular chamber of the bypass channel, which imparts a swirl direction corresponding to that of the air mass flow in the inflow channel to the air mass flowing through the bypass channel from the second to the first flow opening.

Abstract: A method for regulating fluid flow through a gas turbine engine is provided. The method includes coupling an outer fairing to a radially outer duct wall and coupling an inner fairing to a radially inner duct wall. An annular valve is coupled between the radially outer and the radially inner duct walls such that an outer bypass flow area is at least partially defined between the annular valve and the outer fairing, and such that an inner bypass flow area is at least partially defined between the annular valve and the inner fairing. The annular valve is selectively positioned between a first operational position and a second operational position, such that at least one of the outer bypass and the inner bypass flow areas is varied during a transition from a first turbine operation to a second turbine operation.

Abstract: A variable geometry turbine has an annular inlet passageway defined between a radial wall of a moveable wall member and a facing wall of the turbine housing. The moveable wall member is mounted within an annular cavity provided within the housing and having inner and outer annular surfaces. An annular seal is disposed between an annular flange of the moveable wall member and the adjacent inner or outer annular surface of the cavity. One or more inlet bypass passages are provided in the annular flange or said adjacent cavity surface, such that the annular seal and bypass passageways move axially relative to one another as the moveable wall member moves. The annular seal and the or each bypass passage are axially located such as the annular wall member approaches the facing wall of the housing the or each bypass passage permits the flow of exhaust gas through said cavity to the turbine wheel thereby bypassing the annular inlet passageway.

Abstract: Methods and apparatus for a balance weight access assembly are provided. The assembly includes an access cover, and an access tube including a first opening, a second opening, and a substantially hollow body extending therebetween. The first opening is positioned proximate to a balance weight retainer, the second opening is positioned proximate to the access cover, and the body is positioned in substantial alignment with an installation axis of the balance weight retainer.

Abstract: In a gas turbine engine having a rim cavity formed between a rotor disk and a stator, and a brush seal or other seal member providing an airflow seal between the stator and a side plate of the rotor disk, a thermally responsive valve device is located in the bypass passage of the stator to form a parallel air flow path with the brush seal. As the brush seal wears and the leakage airflow around the worn brush seal increases, the air flow temperature in the rim cavity would decrease. The thermally responsive valve device would detect the decreasing airflow temperature, and reduce the airflow passing through the bypass passage in order to prevent the temperature of the rim cavity from decreasing. The temperature responsive valve device makes use of a bimetallic valve member that regulates airflow based upon temperature.

Abstract: In prop fan and contra fan gas turbine engines particularly utilised with regard to pusher configurations towards the aft of an aircraft, there is a significant problem with regard to debris and bird strikes resulting in particulate matter which may damage the engine thrust core. By providing an inlet rotor which fragments and creates a centrifugal aspect to the inlet flow, particulate matter can be directed to a bypass chute normally in the form of an annular section extending into a number of chute exits. In such circumstances, the particulate matter is removed continuously from the inlet flow and the chutes are normally angled to project any particulate matter towards propellers of the engine at robust positions.

Abstract: An assembly useful in reducing aircraft engine noise such as turbofan engine noise (730) comprises: (1) at least one tube “H-Q” having an inlet end (738), an outlet end (740) and a central tube portion therebetween; an (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube. The assembly of this invention may be used in a method for reducing noise, the method comprising: (a) providing means for generating non-uniform noise energy about an inner surface and within a disclosure having at least an inlet; (b) providing an assembly for reducing noise comprising; (i) at least one tube having an inlet end, an outlet end and a central tube portion therebetween, and (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube; and (c) directing at least a portion of the non-uniform noise into the assembly.

Abstract: In a compressor stage (7) comprising a movable bladed wheel (10) having movable blades (8) and a fixed bladed wheel (12) having fixed blades (9), the air tapping circuit arrangement comprises a movable wheel manifold (24) designed to collect an air flow aspirated from the movable blades (8) and a fixed wheel manifold (28) designed to collect an air flow aspirated from the fixed blades (9), and said movable wheel manifold (24) is placed on the periphery of said compressor stage (7) facing said movable wheel (10) and said fixed wheel manifold (28) is superposed on said movable wheel manifold (24). Application to a compressor stage (7) of a turbojet (1).

Abstract: The relief device is designed to divert a portion (94) of a main flow (90) toward a by-pass flow (92) in a turbojet that comprises a main flow stream (10), a by-pass flow stream (14) and an intermediate casing (20).

Abstract: A gas turbine engine includes a turbomachinery core operable to generate a flow of pressurized combustion gases at a variable flow rate, while maintaining a substantially constant core pressure ratio; a rotating fan disposed upstream of the core, the fan adapted to extract energy from the core and generate a first flow of air which is compressed at a first pressure ratio; and at least a first bypass duct surrounding the core downstream of the fan adapted to selectively receive at least a first selected portion of the first flow which is compressed at a second pressure ratio lower than the first pressure ratio, and to bypass the first selected portion around the core, thereby varying a bypass ratio of the engine. The fan is adapted to maintain a flow rate of the first flow substantially constant, independent of the bypass ratio.

Abstract: The bleed valve actuating system is for use in a gas turbine engine. The system comprises an actuator mounted adjacent the engine case and having a main actuation axis extending generally parallel to a surface of the engine case. A drive rod extends from the bleed valve to the actuator generally perpendicularly with reference to the main actuation axis of the actuator. The drive rod connected to the actuator via a linkage mechanically connects the actuator to the drive rod. The linkage is configured to convert axial motion of the actuator along the main actuation axis into generally perpendicular motion of the drive rod.

Abstract: A nacelle assembly for a gas turbine engine includes a fan cowl disposed about an axis, a core cowl within the fan cowl and a bleed passage having an inlet that receives a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The bleed airflow is selectively introduced near a boundary layer of an inlet lip section of the fan cowl.

Abstract: A gas turbine engine 10 comprises a fan 13, a bypass duct 22 having a nozzle 23, through which fluid B from the fan 13 flows, and a variable area nozzle device 34 located in the nozzle 23. The variable area nozzle device 34 comprises an arcuate fairing 36 having one end 44 in slidable cooperation with the bypass duct 22. In a deployed position the area of the nozzle is reduced from that when stowed thereby improving engine operability and efficiency.

Abstract: In the process of the present invention, a polyamide A1 and an organized clay B are mixed mainly by dispersive mixing, and after added with a polyamide A2, mixed mainly by distributive mixing in a corotating intermeshing twin-screw extruder so designed as to effect the dispersive mixing and the distributive mixing. The organized clay B is completely and finely dispersed and distributed throughout the resultant polyamide composite material. Shaped articles such as films and sheets made of the polyamide composite material exhibit excellent gas barrier properties and transparency with little malodor mainly attributable to the decomposed products of the organizing agent for preparing the organized clay B.

Abstract: A gas turbine engine compressor has a number of shroud rings, at least a bleed one of which defines a number of bleed ports. A structural hub is downstream of the shroud rings and secured relative to the shroud rings. A structural hub case extends from an aft joint with the structural hub to a fore joint with a joined one of the shroud rings and has a number of valve ports. At least a portion of the structural case extends structurally between the fore and aft joints. A valve element is shiftable between first and second conditions for respectively blocking and not blocking communication through the valve ports.

Abstract: A turbine housing assembly includes a tubular piston disposed in a bore of a turbine housing and axially slidable between a closed position and an open position for blocking a nozzle by an amount dependent on axial positioning of the piston. A bypass control member is disposed in the turbine housing and is slidable between a no-bypass position closing a bypass passage and a open bypass opening the bypass passage. The piston is structured and arranged to slide relative to the bypass control member for a part of a full stroke of the piston from the closed position toward the open position thereof, and then to engage the bypass control member and cause the bypass control member to slide together with the piston as the piston further slides toward the open position thereof such that the bypass control member is moved toward the bypass position.

Abstract: A wastegated turbocharger includes a turbine wheel mounted to a shaft for rotation within a turbine housing and a compressor wheel mounted to the shaft for rotation within a compressor housing. The compressor housing has mounted thereto a wastegate actuator command valve. A secondary boost air outlet passage is disposed in fluid flow communication with the wastegate actuator command valve and the compressor outlet volute. The secondary boost air outlet passage extends into the compressor outlet volute so that an inlet opening of the passage is spaced from the surface of the compressor outlet volute.

Abstract: In an exhaust gas turbocharger of an internal combustion engine including a compressor arranged in the intake duct and a turbine arranged in the exhaust duct of the engine, wherein the turbine includes in its housing an exhaust collection chamber from which the exhaust gas is directed via turbine inlet passage to the turbine wheel, the housing also includes a bypass arrangement for conducting part of the exhaust gas to the turbine exhaust structure in a turbine wheel bypass line which includes an ejector structure forming a gas pumping device.

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: The present invention is a system (20) for controlling various fluid flows, e.g., secondary fluid flows including cavitating fluid flows, typically developed along the shroud line and usually in or around a leading edge (21) within a flow channel (22) of a compressor or pump impeller (23) and inducer/impeller (24). System (20) includes a plurality of devices for controlling various flow conditions. In one embodiment, system (20) includes a diffuser device (27) for stabilizing cavitating flows, a bypass device (28) for re-injecting flow upstream, and a flow control device (30) for selectively directing secondary fluid flow to either the diffuser device or the bypass device. In addition, at very high flow rates, bypass device (28) may also serve as a high-flow, forward-bypass device. Devices (27) and (28) form a pathway for secondary fluid flows, including cavitating flows, around a first portion (31) of a housing (32).

Abstract: A bleed valve for use in a gas turbine engine is provided; the bleed valve may be used to relieve air pressure from a compressor stage of the engine. At normal pressure and when the engine is off, the bleed valve is in the open position. However once the engine starts, air pressure provided by the compressor closes the bleed valve. During engine operation, the bleed valve is opened to relieve air pressure by providing pressurized fluid, such as compressor air, to a valve chamber. The bleed valve is designed so that moveable parts of the valve, including contact seals and a sliding shaft, are protected by the valve structure from debris and contaminants carried in the engine's air stream.

Abstract: Disclosed is a system for operating gas turbine engine bleed valves in response to pressure values within the engine, wherein the engine pressure values are sensed electronically and routed to a programmable logic device, and wherein the programmable logic device control the opening and closing of the bleed valves in a manner that allows for reduced engine vibration with minimal loss of engine efficiency.

Abstract: A turbofan jet engine that includes a valve assembly mounted within the engine and in fluid communication with the engine bypass flow passage. The valve assembly includes a valve body that has a fluid inlet port in fluid communication with the bypass flow passage, and two or more fluid outlet ports in fluid communication with two different turbine case sections. The valve is disposed in the valve body and is selectively moveable between a closed position and an open position. In the close position only one fluid outlet port is in substantial fluid communication with the fluid inlet port, to thereby supply cooling air to one turbine case section. In the open position, all of the fluid outlet ports are in substantial fluid communication with the fluid inlet port, to thereby supply cooling air to all of the turbine case sections.

Abstract: The present invention relates to an axial flow rotary machine and to a maintainable compressor bleed system therefore. The axial flow rotary machine comprises a primary flow path for a working medium, a secondary flow path for the working medium, a bleed system for allowing a bleed portion of the working medium flowing in the primary flow path to be delivered to the secondary flow path, a support structure for the bleed system located radially inboard of the bleed system, and the panels for gaining access to the bleed system. The panels are located radially outboard of the bleed system. The panels form the inner flow wall for the primary flow path.

Abstract: A compressor assembly comprises a compressor having a rotor comprising a shaft with fan blades for compressing air. An air bearing serves to cool the shaft of the rotor. A compressor air inlet receives air for the fan blades, which is then exhausted from the fan blades out a compressor air outlet. An air flow path communicates air from the compressor air inlet to the air bearing. A valve controls the flow of air through the air flow path and has an open position permitting air through the air flow path in a closed position restricting air to the path.

Abstract: A method enables a gas turbine engine variable bypass valve system to be assembled. The method comprises positioning a unison ring circumferentially within the gas turbine engine such that the unison ring is radially outward from a structural frame, coupling at least one bellcrank to the unison ring, such that the unison ring is radially supported only by said at least one bellcrank, and coupling the at least one bellcrank to a bellcrank support that is coupled to the structural frame.

Abstract: The present invention relates to an axial flow rotary machine and to a maintainable compressor bleed system therefore. The axial flow rotary machine comprises a primary flow path for a working medium, a secondary flow path for the working medium, a bleed system for allowing a bleed portion of the working medium flowing in the primary flow path to be delivered to the secondary flow path, a support structure for the bleed system located radially inboard of the bleed system, and the panels for gaining access to the bleed system. The panels are located radially outboard of the bleed system. The panels form the inner flow wall for the primary flow path.

Abstract: Variable geometry turbochargers include a turbine housing having an exhaust gas inlet and outlet, a volute connected to the inlet, and typically a nozzle wall adjacent the volute. The turbine housing includes a bypass exhaust gas flow port disposed internally therein having an inlet opening positioned upstream from the turbine wheel, and a outlet opening positioned downstream from the turbine wheel. The inlet opening is exposed for facilitating bypass exhaust gas flow through the turbocharger when a respective vane is actuated or moved into an open position. The turbine housing may also include a specially configured nozzle wall terminal edge designed to work with vanes having a recessed underside surface to permit additional bypass exhaust gas flow within the turbocharger when the vanes are actuated in an open position.