Class / Patent application number | Description | Number of patent applications / Date published |
415145000 | Selectively adjustable vane or working fluid control for bypass | 85 |
20080199308 | AIR TAPPING CIRCUIT ARRANGEMENT, A COMPRESSOR STAGE COMPRISING SAME, THE COMPRESSOR COMPRISING SAME AND A TURBOJET COMPRISING SAME - In a compressor stage ( | 08-21-2008 |
20080253881 | Engine - 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. | 10-16-2008 |
20090016874 | METHOD AND APPARATUS FOR REGULATING FLUID FLOW THROUGH A TURBINE ENGINE - 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. | 01-15-2009 |
20090028694 | Structure of Exhaust Turbocharger Having Waste Gate Valve - 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. The turbocharger has a twin scroll type turbine housing having two exhaust gas entrance channels and two exhaust gas bypass passages for allowing exhaust gas entered the turbine housing to bypass the turbine rotor and being equipped with a waste gate valve for opening/closing the two exhaust gas bypass passages by allowing a plate-like valve body to seat against and depart from a seat face at an outlet end side of the two bypass passages, wherein a depression is formed to a seat-side face of the valve body or to the end face of the partition wall so that the seat-side face of the valve body does not contact the end face of the partition wall at least in the central region of the end face of the partition wall when the valve body seats against the seat face at the outlet end side of the bypass passages. | 01-29-2009 |
20090035127 | VALVE ASSEMBLY FOR A GAS TURBINE ENGINE - 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. | 02-05-2009 |
20090060719 | Dual volute turbocharger - A two-volute low pressure turbocharger is provided with a VGT mechanism in one turbine volute only. | 03-05-2009 |
20090067993 | COATED VARIABLE AREA FAN NOZZLE - 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. | 03-12-2009 |
20090074568 | VARIABLE FAN INLET GUIDE VANE ASSEMBLY, TURBINE ENGINE WITH SUCH AN ASSEMBLY AND CORRESPONDING CONTROLLING METHOD - 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. | 03-19-2009 |
20090092481 | ACTUATING ROD END CONNECTOR - 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. | 04-09-2009 |
20090097967 | GAS TURBINE ENGINE WITH VARIABLE GEOMETRY FAN EXIT GUIDE VANE SYSTEM - 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. | 04-16-2009 |
20090104020 | SYSTEM FOR DELIVERING AIR FROM A MULTI-STAGE COMPRESSOR TO A TURBINE PORTION OF A GAS TURBINE ENGINE - 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. | 04-23-2009 |
20090104021 | Turbine for power generation in a drill string - The invention is directed to a turbine ( | 04-23-2009 |
20090136337 | Method and Apparatus for Improved Reduced Load Operation of Steam Turbines - 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. | 05-28-2009 |
20090155057 | COMPRESSOR VARIABLE STAGE REMOTE ACTUATION FOR TURBINE ENGINE - A turbine engine locates an actuator ( | 06-18-2009 |
20090169366 | Variable Geometry Turbine For A Turbocharger And Method Of Controlling The Turbine - There is described a variable geometry turbine having a sliding element ( | 07-02-2009 |
20090191048 | ADJUSTMENT DEVICE - The present invention relates to an adjustment device ( | 07-30-2009 |
20090208328 | GAS TURBINE ENGINE WITH VARIABLE AREA FAN NOZZLE BLADDER SYSTEM - 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. | 08-20-2009 |
20090232642 | Adjustable compressor bleed system and method - 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. | 09-17-2009 |
20090252600 | ACTUATION OF A TURBOFAN ENGINE BIFURCATION TO CHANGE AN EFFECTIVE NOZZLE EXIT AREA - The invention relates to a turbine engine that includes a spool supporting at least one of a compressor and a turbine. A turbofan is coupled to the spool The spool is arranged in a core nacelle, and the turbofan is arranged upstream from the core nacelle. A fan nacelle surrounds the turbofan and the core nacelle and provides a bypass flow path. A structure extends radially between the core and fan nacelles to support the core nacelle relative to the fan nacelle. Surfaces are supported relative to the fixed structure and are moveable between closed and open positions to selectively obstruct bypass flow through the bypass flow path, thereby changing the effective area of the exit nozzle. A change in the effective area of the nozzle exit can be used to improve the efficiency and operation of the turbine engine. | 10-08-2009 |
20090297338 | VARIABLE AREA NOZZLE ASSISTED NOISE CONTROL OF A GAS TURBINE ENGINE - An example turbofan engine sound control system includes a core nacelle ( | 12-03-2009 |
20100047059 | BYPASS TURBOJET - The invention relates to a bypass turbojet engine comprising an outer fan duct and an inner fan duct (IFD), between which the secondary flow passes, and a high pressure compressor having an outer casing. In characteristic manner, the IFD is fastened on the outer casing. The invention is applicable to a turbojet engine having a high pressure compressor of the axial-centrifugal type. | 02-25-2010 |
20100061840 | COMPRESSOR WITH VARIABLE-GEOMETRY PORTED SHROUD - A compressor having a variable-geometry ported shroud includes a compressor housing defining an inlet duct, a shroud, and a bypass passage. A variable-geometry port extends through the shroud into the bypass passage, and includes an adjustable mechanism that is selectively configurable to adjust the meridional location of the port between at least first and second meridional locations. In one embodiment an opening extends through the shroud, and the adjustable mechanism includes a bypass control device that is disposed within the opening and is axially movable therein. The bypass control device has an axial length less than that of the opening such that there is always a portion of the opening that remains unblocked by the bypass control device and forms a port through the shroud. The bypass control device is axially movable between at least first and second positions to place the port at the first and second meridional locations. | 03-11-2010 |
20100068039 | TURBOFAN ENGINE WITH VARIABLE BYPASS NOZZLE EXIT AREA AND METHOD OF OPERATION - (A1)) A turbofan engine includes core and fan nacelles that provide a bypass flow path having a nozzle exit area. The bypass flow path carries a bypass flow to be expelled from the nozzle exit area. A turbofan is arranged within the fan nacelle and upstream from the core nacelle for generating the bypass flow. A flow control device includes a surface in the bypass flow path including an aperture. The flow device is adapted to introduce a fluid into the bypass flow path for altering a boundary layer of the bypass flow that effectively changes the nozzle exit area. In one example, bleed air is introduced through the aperture. In another example, pulses of fluid from a Helmholz resonator flow through the aperture. By decreasing the boundary layer, the nozzle exit area is effectively increased. By increasing the boundary layer, the nozzle exit area is effectively decreased. | 03-18-2010 |
20100215480 | SYSTEMS AND METHODS FOR ENGINE TURN DOWN BY CONTROLLING COMPRESSOR EXTRACTION AIR FLOWS - Systems and methods for controlling compressor extraction air flows from a compressor of a turbine system during engine turn down are provided. In one embodiment, a method for controlling compressor extraction air flows from a compressor of a turbine system during turn down includes a control unit monitoring one or more operating parameters of a turbine system associated with an exit temperature of a combustor of the turbine system. The method further includes the control unit detecting one or more operating parameters meeting or exceeding a threshold associated with a decrease in the exit temperature of the combustor. In response to detecting one or more operating parameter meeting or exceeding the threshold, a control signal is transmitted to at least one variable orifice located in the turbine system causing at least one variable orifice to alter at least one extraction air flow from the compressor. | 08-26-2010 |
20100215481 | RUNNING-GAP CONTROL SYSTEM OF AN AIRCRAFT GAS TURBINE - A running-gap control system of an aircraft gas turbine with a core engine including a turbine whose blade rows have a running gap | 08-26-2010 |
20110097196 | AIR DISCHARGE SYSTEM FOR AN AERONAUTICAL TURBINE ENGINE COMPRESSOR - The invention relates to an air discharge system for an aviation turbomachine compressor, the discharge system including at least one discharge valve ( | 04-28-2011 |
20110103936 | TURBOCHARGER WITH ANNULAR ROTARY BYPASS VALVE FOR THE TURBINE - A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines an annular bypass passage surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member. | 05-05-2011 |
20110123315 | MULTI-STAGE TURBOCHARGER SYSTEM - A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger and a second relatively large low pressure (LP) turbocharger. The turbine of the LP turbocharger is connected in series downstream of the turbine of the HP turbocharger. A first exhaust bypass flow passage provides a bypass flow path around the HP turbine. A second exhaust bypass flow passage provides a bypass flow path around the LP turbine. A rotary valve is located at a junction of the first and second bypass flow passages and a first exhaust gas flow passage. The rotary valve comprises a valve rotor which is rotatable selectively to permit or block flow to the LP turbine and to permit or block flow to the first and second bypass paths. | 05-26-2011 |
20110150634 | Integration of an Air-Liquid Heat Exchanger on an Engine - A bypass axial turbomachine includes a fan, a low pressure stator stage, a high pressure stator stage, the compressors being traversed by a flow referred to as primary flow of the turbomachine, at least one passage of discharge flow rate controlled from the primary flow in one of the stator stages toward the secondary flow, a heat exchanger of the surface air-oil (ACOC) type arranged flat on or in the wall surrounding the stator stages and defining the internal surface of the secondary flow, directly downstream of the junction of the passage of the discharge flow rate with said wall, so as to be run through by the secondary flow enriched with the discharge flow rate. | 06-23-2011 |
20110171007 | CONVERTIBLE FAN SYSTEM - A convertible fan system is disclosed having a fan rotor with a plurality of fan blades having an arcuate splitter that forms a portion of an inner flow passage and an outer flow passage wherein an inner portion of the fan blade pressurizes an inner flow in the inner flow passage and an outer portion of the fan blade pressurizes an outer flow in the outer flow passage and a vane system having an outer vane that is adapted to be able to vary the flow in the outer flow passage such that pressure ratio of the fan system can be varied. | 07-14-2011 |
20110206499 | DOUBLE CASING TYPE PUMP AND HEAD ADJUSTING METHOD THEREOF - Providing a double casing type pump and a head adjusting method thereof, wherein, the performance of the pump, especially, the head of the pump can be adjusted without large-scale work as well as without component disassembly. A double casing type pump, comprising: a plurality of impellers fixed to a rotation shaft, an inner casing that shrouding the impellers; an outer casing shrouding the inner casing and having a suction opening and a discharge opening; wherein, the pump further comprises: a space formed between the inner casing and the outer casing, the space communicating with the discharge opening; a bypass hole connecting the space to the working fluid passage in the inner casing, the pressure in the working fluid passage being lower than the stagnation fluid in the space; and, the bypass hole comprises a throat diameter adjusting member having a through-hole therein for determining the throat area of the bypass hole. Further, a plurality of throat diameter adjusting members is prepared in advance, each member having different throat area; a throat diameter adjusting member is selected out of the whole members so that the head of the pump remains within a predetermined range with the selected member. | 08-25-2011 |
20110268559 | Turbocharger With Turbine Nozzle Vanes and an Annular Rotary Bypass Valve - A turbocharger includes an annular bypass passage to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member. The turbine includes a nozzle having a vane assembly. In one embodiment the vane assembly has only fixed vanes. In another embodiment the vane assembly includes both fixed vanes and variable vanes, and the variable vanes are part of a rotor that rotates together with the rotary valve member. | 11-03-2011 |
20110268560 | GAS TURBINE ENGINE - A gas turbine engine has an annular bypass duct defined between a fan nacelle and a core fairing through which fan air is discharged. One or more bifurcator members are positioned inside the exit of the bypass duct to bifurcate the air flow in the bypass duct around the bifurcator members prior to exiting the bypass duct. The bifurcator members modify the flow field of the air in the bypass duct radially and/or tangentially with respect to the axis of the annular bypass duct. | 11-03-2011 |
20120020775 | FLOW SPLITTER ASSEMBLY FOR STEAM TURBOMACHINE AND METHOD - A turbomachine includes a first turbine portion and a second turbine portion. A flow splitter assembly is coupled between the first and second turbine portions. The flow splitter assembly includes a first end portion including a first mounting member and a second end portion including a second mounting member. A flow diverting member is positioned between the first and second end portions. The flow diverting member includes a first end section having a first mounting element coupled to the first mounting member and a second end section having a second mounting element coupled to the second mounting member. The flow diverting member includes a flow diverting surface. A first locking member engages the first mounting element and the first mounting member, and a second locking member engages the second mounting element and the second mounting member. | 01-26-2012 |
20120045317 | FUEL ACTUATED BLEED AIR SYSTEM - A gas turbine engine bleed air system includes one or more fuel-actuated bleed air supply valves and, in some cases, a pneumatically actuated overpressure valve. Each fuel-actuated bleed air supply valve is mounted on a bleed air supply conduit and is coupled to a source of pressurized aircraft fuel. Each fuel-actuated bleed air supply valve is responsive to the pressurized aircraft fuel to move to a plurality of valve positions and to regulate compressed air pressure in the bleed air supply conduit, downstream of the fuel-actuated bleed air supply valve. The pneumatically actuated overpressure valve is mounted on the bleed air conduit downstream of each of the fuel-actuated bleed air valves and pneumatically regulates or shuts off pressure independent of fuel pressure or electrical signals. | 02-23-2012 |
20120070271 | GAS TURBINE ENGINE WITH BLEED DUCT FOR MINIMUM REDUCTION OF BLEED FLOW AND MINIMUM REJECTION OF HAIL DURING HAIL INGESTION EVENTS - A gas turbine engine includes a bleed structure which includes a forward wall and a rear structural wall to define a deposit space downstream of the bleed structure for a hail event of a predetermined duration. | 03-22-2012 |
20120087779 | SUPERSONIC COMPRESSOR STARTUP SUPPORT SYSTEM - A supersonic compressor includes a fluid inlet, a fluid outlet, a fluid conduit extending therebetween, and at least one supersonic compressor rotor disposed within the fluid conduit and including a fluid flow channel that includes a throat portion. The supersonic compressor also includes a fluid control device coupled in fluid communication with at least one fluid source and an inlet of the fluid flow channel. The fluid control device channels a first fluid to the fluid flow channel inlet. The first fluid has a first plurality of fluid properties that facilitate attainment of supersonic flow of the first fluid in the throat portion during a first operational mode. The fluid control device further channels a second fluid to the fluid flow channel inlet. The second fluid has a second plurality of fluid properties that permit maintenance of supersonic flow of the second fluid in the throat portion. | 04-12-2012 |
20120093631 | MULTI-STAGE TURBOCHARGER ARRANGEMENT - The present invention relates to a multi-stage turbocharger arrangement ( | 04-19-2012 |
20120099965 | TURBOCHARGER TURBINE - A turbocharger turbine which has a wastegate slide sleeve ( | 04-26-2012 |
20120128470 | SELF-ACTUATING BLEED VALVE FOR A GAS TURBINE ENGINE - A bleed valve for an air plenum includes a valve body which defines a valve seat. A poppet is movable relative to the valve seat between an open position and a closed position. A spring biases the poppet to the open position and toward the air plenum. | 05-24-2012 |
20120134782 | PURGE SYSTEMS FOR ROTARY MACHINES AND METHODS OF ASSEMBLING SAME - A method for assembling a rotary machine includes providing a first rotatable element. The method also includes coupling a second rotatable element to the first rotatable element. The first rotatable element and the second rotatable element at least partially define a cavity therein and at least one conduit extending substantially axially therebetween. Further, the method includes coupling a purge device including at least one radial channel defined therein and extending to the first rotatable element and to the second rotatable element such that the at least one radial channel is coupled in flow communication with the cavity and with the at least one axial conduit. | 05-31-2012 |
20120148386 | Turbocharger With Divided Turbine Housing and Annular Rotary Bypass Valve for the Turbine - A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a divided volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines a pair of concentric annular bypass passages surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel as two separate bypass streams. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member. | 06-14-2012 |
20120288359 | Gas-turbine engine with bleed-air tapping device - The present invention relates to a gas-turbine engine with at least one compressor and at least one bleed-air tapping device, which includes an annular duct in a radially outer wall of a flow duct, and with an annular closing element, which is arranged in the region of the annular duct and can be moved in a substantially axial direction from a closed position to an open position, with the closing element having an annular flow divider projection which in the open position projects in the flow duct. | 11-15-2012 |
20120321448 | AIRCRAFT POWERPLANT - A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat areas for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle. | 12-20-2012 |
20130011244 | RECONFIGURABLE HEAT TRANSFER SYSTEM FOR GAS TURBINE INLET - A reconfigurable heat transfer system for a turbine inlet for a gas turbine engine is disclosed. The reconfigurable heat transfer system includes reconfigurable heat transfer components may be moved between a first position and a second position, wherein the second position allows a portion of or all of the air in the inlet to bypass the heat transfer components. | 01-10-2013 |
20130115055 | SYSTEM FOR CONTROLLING A PNEUMATIC VALVE OF A TURBINE ENGINE | 05-09-2013 |
20130129486 | Turbocharger With Annular Rotary Bypass Valve For the Turbine - A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines an annular bypass passage surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member. | 05-23-2013 |
20130149114 | HOUSING FOR A BLADE WHEEL - The present invention relates to a housing for a blade wheel of a turbo machine including a flow channel which is enclosed by a housing wall; a valve flap for selectively sealing or releasing a flow opening in the housing wall; and a shaft which is connected with the valve flap. The shaft is guided through an opening in the housing wall to the outside of the flow channel. The opening has an opening width which is larger than the largest diameter of the smallest projected area of the valve flap and of the part of the shaft protruding into the flow channel in the mounted state, and the opening is sealed in the mounted state by a cover through which the shaft extends. | 06-13-2013 |
20130223995 | Turbocharger With Annular Rotary Bypass Valve for the Turbine - A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines an annular bypass passage surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve includes a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member. | 08-29-2013 |
20140056696 | PUMP DEVICE AND PUMP SYSTEM - A pump device ( | 02-27-2014 |
20140127002 | MULTI-STAGE TURBOCHARGER ARRANGEMENT - A multi-stage turbocharger arrangement (TLA), having a high-pressure stage, the high-pressure turbine of which has an associated first bypass valve; and having a low-pressure stage which is arranged downstream as viewed in the flow direction of the exhaust gases and which has a low-pressure turbine and a second bypass valve, wherein at least one of the bypass valves is arranged in an associated, cooled housing module. | 05-08-2014 |
20140140821 | VACUUM-ACTUATED WASTEGATE - Embodiments for vacuum generation are provided. In one example, a method for an engine including a turbocharger having a compressor driven by a turbine comprises generating vacuum via compressor bypass flow through an ejector, and applying vacuum from the ejector to a wastegate actuator. In this way, vacuum produced via boosted engine operation may be used to actuate the wastegate valve. | 05-22-2014 |
20140234081 | TRANSLATING VARIABLE AREA FAN NOZZLE PROVIDING AN UPSTREAM BYPASS FLOW EXIT - A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end. | 08-21-2014 |
20140241863 | EXHAUST SECTION FOR BYPASS GAS TURBINE ENGINES - A turbine exhaust section comprises a turbine exhaust case having radially outer and inner ducts defining therebetween an annular exhaust portion for the hot exhaust gases, and an exhaust mixer projecting axially rearwardly from the turbine exhaust case for mixing the hot exhaust gases with a cooler bypass duct flow. The upstream end of the exhaust mixer surrounds a downstream end of the outer duct and defines therewith an axially extending overlap joint with a radial play between the outer duct and the exhaust mixer. A sliding attachment in the radial direction is provided between the outer duct and the exhaust mixer for accommodating differences in thermal growth during engine operation. The sliding attachment includes a circumferential array of sliding guides extending radially through the axially extending overlap joint. A resilient sealing ring seals the radial play between the outer duct and the exhaust mixer at the overlap joint. | 08-28-2014 |
20140248132 | ACTIVE BYPASS FLOW CONTROL FOR A SEAL IN A GAS TURBINE ENGINE CROSS-REFERENCE TO RELATED APPLICATION - An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed. The active bypass flow control system is an adjustable system in which one or more metering devices may be used to control the flow of bypass compressed air as the flow of compressed air past the outer balance seal changes over time as the outer balance seal between the rim cavity and the cooling cavity wears. In at least one embodiment, the metering device may include a valve formed from one or more pins movable between open and closed positions in which the one pin at least partially bisects the bypass channel to regulate flow. | 09-04-2014 |
20140248133 | ACTIVE BYPASS FLOW CONTROL FOR A SEAL IN A GAS TURBINE ENGINE - An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed. The active bypass flow control system is an adjustable system in which one or more metering devices may be used to control the flow of bypass compressed air as the flow of compressed air past the outer balance seal changes over time as the outer balance seal between the rim cavity and the cooling cavity wears In at least one embodiment, the metering device may include an annular ring having at least one metering orifice extending therethrough, whereby alignment of the metering orifice with the outlet may be adjustable to change a cross-sectional area of an opening of aligned portions of the outlet and the metering orifice | 09-04-2014 |
20140314548 | TURBINE ENGINE AND VANE SYSTEM - One embodiment of the present invention is a unique vane system. Another embodiment is a unique gas turbine engine. Another embodiment is a unique method for manufacturing a bypass vane stage. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for turbine engines and vane systems for turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 10-23-2014 |
20140321986 | TURBOCHARGER - A turbocharger includes: a turbine housing including a through-hole through which a turbine impeller is bypassed; and a wastegate valve configured to open and close the through-hole. A biasing portion biases the wastegate valve and a support plate in opposite directions, and restrains rotation of the wastegate valve relative to the support plate. | 10-30-2014 |
20140363277 | ASSEMBLY FOR A FLUID FLOW MACHINE - A structural assembly for a fluid-flow machine includes a main flow path boundary, a row of relatively rotating blades with a gap existing between the blade ends and the main flow path boundary. A secondary flow duct is connected to the main flow path via the two openings spaced apart in the flow direction. A structural assembly has at least one support component and at least one replaceable plug connected directly or indirectly to the support component. The replaceable plug includes a part-section of a secondary flow duct, where the part-section complements at least one further part-section of the secondary flow duct extending outside the plug in the structural assembly to form a secondary flow duct which is continuous between its openings. | 12-11-2014 |
20150010390 | TURBOCHARGER - A turbocharger includes: an inflow passage to guide a fluid to a housing space for a turbine wheel; an exhaust passage to discharge the fluid having rotated the turbine wheel from a turbocharger body; a bypass passage connecting the inflow passage and the exhaust passage; a valve unit having one valve for a communicating portion between the exhaust passage and the housing space, and another valve for the bypass passage; an actuator to turn the valve unit and a stem connected to the valve unit about an axis of the stem; and a controller to operate the actuator. The controller adjusts the opening of the bypass passage by turning the valve unit within a specific range about the axis of the stem when a specific condition is met, and closes the exhaust passage by turning the valve unit beyond the specific range when the specific condition is not met. | 01-08-2015 |
20150016963 | TURBINE - A turbine comprises a turbine housing defining a turbine inlet upstream of a turbine wheel and a turbine outlet downstream of the turbine wheel; a wastegate passage connecting the turbine inlet and the turbine outlet; and a wastegate valve comprising a movable valve member. The wastegate valve has an open state and a closed state. The valve member is mounted to an actuation member passing through an actuator conduit of the turbine housing, and movable so as to move the wastegate valve between the open and closed states. The turbine further comprises a sealing arrangement configured to provide a seal arranged to substantially prevent gas from passing from the turbine outlet into the actuator conduit. The sealing arrangement is configured such that when the valve member is urged into the closed state by the actuator member the sealing effectiveness of the sealing arrangement is increased. | 01-15-2015 |
20150044033 | TURBOCHARGER - A turbocharger includes an open-and-close mechanism which opens and closes a circulation hole through which an exhaust gas flows into a turbine housing or the exhaust gas flows out of the turbine housing. The open-and-close mechanism includes: a valve; and an attachment plate one end of which is fixed to the valve, and the other end of which is provided with an insertion hole through which a stem turnably supported by the turbine housing is inserted, and an exposure hole which communicates with the insertion hole to expose part of an outer peripheral surface of the stem. The diameter of the insertion hole is gradually smaller in a direction of insertion of the stem. The stem includes a tapered portion whose diameter is gradually smaller toward its tip end in the direction of insertion into the insertion hole. | 02-12-2015 |
20150050128 | COMPACT MULTI-STAGE TURBO PUMP - A turbo pump has a common axis of rotation for a plurality of compressor and turbine wheels. One or more of the turbine and compressor wheels defines a gas passage axially therethrough, said gas passage being associated with another of the turbine and compressor wheels. The arrangement provides a compact multi-stage turbocharger. | 02-19-2015 |
20150098803 | EXHAUST-GAS TURBOCHARGER HAVING A WASTEGATE VALVE AND HAVING AN OVERRUN AIR RECIRCULATION VALVE - An exhaust turbocharger has a wastegate valve and a thrust circulation valve, which can be actuated by a single, common actuator. The actuation of the thrust circulation valve is dependent on the positioning velocity of the actuator. | 04-09-2015 |
20150118027 | ADJUSTMENT DEVICE FOR AN EXHAUST GAS TURBOCHARGER - In an adjusting device fir an exhaust gas turbocharger with a first adjusting member and a second adjusting member for operating a valve element for varying the flow cross-section of a bypass duct of a flow-through exhaust gas guide portion of a turbine of an exhaust gas turbocharger, the first adjusting member and the second adjusting member are connected so as to be pivotable relative to one another by a pin-shaped connecting element with a locking element establishing a pivot joint of the first adjusting member and the second adjusting member with a predetermined axial engagement force. | 04-30-2015 |
20150125272 | REGULATING FLAP ARRANGEMENT OF AN EXHAUST-GAS TURBOCHARGER - A regulating flap arrangement ( | 05-07-2015 |
20150125273 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 05-07-2015 |
20150147162 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 05-28-2015 |
20150292394 | CONTROL DEVICE FOR AN EXHAUST GAS GUIDE SECTION OF A TURBINE - In a control device for a flow-through exhaust gas guide section of a turbine for opening and dosing a bypass duct to permit exhaust gas to bypass a turbine wheel arranged in a turbine wheel housing of the exhaust gas guide section comprising with an actuating device and a cover element being provided for opening or dosing a flow cross-section of the bypass duct, the cover element is a hollow truncated cone with passages provided in the cone-shaped cover element which differ from one another so as to provide for a controllable efficient and quiet exhaust gas flow through the flow cross-section into the bypass duct. | 10-15-2015 |
20150300244 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 10-22-2015 |
20150330292 | CONTROL ARRANGEMENT OF AN EXHAUST-GAS TURBOCHARGER - A control arrangement ( | 11-19-2015 |
20160069253 | CONTROL ARRANGEMENT OF AN EXHAUST-GAS TURBOCHARGER - A control arrangement ( | 03-10-2016 |
20160076486 | ENGINE WITH A THRUST REVERSER LOCKOUT MECHANISM - A turbofan engine having a thrust reverser having at least one movable control surface, movable to and from a reversing position where at least a portion of the bypass air flow is at least partially reversed, a thrust reverser actuation system having multiple actuators and a lockout mechanism movable between an inhibit condition, wherein movement of the multiple actuators is prevented, and a permit condition, wherein movement of the multiple actuators is permitted. | 03-17-2016 |
20160084153 | TURBINE WASTEGATE - A turbine housing includes a bore, a wastegate seat and a wastegate passage; a bushing disposed at least in part in the bore; a rotatable wastegate shaft that includes a shoulder and a control end; a control arm operatively coupled to the wastegate shaft where the bushing is disposed between a surface of the control arm and the shoulder; a wastegate arm that extends from the wastegate shaft where the shoulder is disposed between the wastegate arm and the control end of the wastegate shaft; and a wastegate plug that extends from the wastegate arm where the wastegate plug includes a toroidal surface defined by a portion of a torus where, in a closed state, the toroidal surface contacts the conical surface of the wastegate seat to cover the wastegate passage. | 03-24-2016 |
20160084253 | MULTI-STAGE, SELF-PRIMING CENTRIFUGAL PUMP ASSEMBLY - A multi-stage, self-priming centrifugal pump assembly includes at least two pump stages ( | 03-24-2016 |
20160090917 | ENGINE BLEED AIR SYSTEM - An engine bleed air system having one or more taps in the compressor section of an aircraft engine, for example a low pressure tap and a high pressure tap. The low pressure tap is fluidly connected to the compressor of a turbo-compressor and the high pressure tap is fluidly connected to the turbine of the turbo-compressor. A bypass line connects the high pressure air to the outlet of the compressor, with a heat exchanger used to remove excess heat from the bypass line. An additional heat exchanger is used to remove any excess heat from the compressed air, dumping the heat to a fan stream or to the expanded air exiting the turbine. The system is controlled to minimize the amount of high pressure air extracted from the engine. | 03-31-2016 |
20160123222 | WASTEGATE ASSEMBLY IN A TURBINE - A wastegate assembly in a turbine of an internal combustion engine is provided. The wastegate assembly includes a wastegate conduit bypassing a turbine rotor, a valve sealing plate configured to seat and seal on a wastegate conduit outlet in a closed position, and a flow diverting tab coupled to the valve sealing plate, extending upstream of the wastegate conduit outlet, and separating a wastegate conduit outflow and a turbine rotor outflow. | 05-05-2016 |
20160130972 | BLEED VALVE - A bleed valve for a gas turbine engine, the bleed valve comprising: an inlet coupled to an air source; and an outlet coupled to an air sink. The bleed valve also comprises a first stage of flow area modulation between the inlet and the outlet. Also a second stage of flow area modulation between the first stage and the outlet. The pressure can be equalised between the first and second stages. There is also an arrangement comprising a plurality of bleed valves and a controller to control the flow areas of at least one of the first and second stages of each bleed valve. | 05-12-2016 |
20160146155 | GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME - A gas turbine engine having a centerline axis is provided. The gas turbine engine includes a fan and a fan cowl assembly surrounding the fan to define a bypass duct configured to channel airflow for the fan. The fan cowl assembly includes a stationary cowl and a transcowl. The gas turbine engine further includes a plurality of actuators configured for displacing the transcowl relative to the stationary cowl. Each of the actuators is skewed relative to the centerline axis of the engine. | 05-26-2016 |
20160146213 | TURBINE WASTEGATE PLUG - An assembly can include a turbine housing that defines a bore, a wastegate opening, a wastegate passage to one side of the wastegate opening and a chamber to another side of the wastegate opening and that includes a wastegate seat disposed about the wastegate opening; a rotatable wastegate shaft configured for receipt by the bore; a wastegate arm that extends from the wastegate shaft; and a wastegate plug that extends from the wastegate arm where the wastegate plug includes a seal surface that includes a toe end and a back end where the back end includes a radius of curvature that exceeds a radius of curvature of the toe end. | 05-26-2016 |
20160160684 | TURBINE ENGINE ASSEMBLY AND METHOD OF MANUFACTURING - A turbine engine assembly is provided. The assembly includes a booster compressor that discharges a flow of first compressed air at a first temperature, and a high-pressure compressor (HPC). The HPC receives a first portion of the flow of first compressed air and discharges the first portion at a second temperature higher than the first temperature such that a flow of second compressed air is formed. The assembly also includes a heat exchanger (HEX) that receives a second portion of the flow of first compressed air from the booster compressor and a first portion of the flow of second compressed air from the HPC such that heat is transferred therebetween. The HEX discharges the first portion of the flow of second compressed air at a third temperature lower than the second temperature and higher than the first temperature such that a flow of cooled bleed air is formed. | 06-09-2016 |
20160160756 | TURBOCHARGER COMBINING AXIAL FLOW TURBINE WITH A COMPRESSOR STAGE UTILIZING ACTIVE CASING TREATMENT - A turbocharger ( | 06-09-2016 |
20160201608 | SYSTEMS AND METHODS CONTROLLING FAN PRESSURE RATIOS | 07-14-2016 |
20180023459 | EXHAUST GAS TURBOCHARGER | 01-25-2018 |
20190145420 | GAS TURBINE ENGINE WITH MID-COMPRESSOR BLEED | 05-16-2019 |