Selectively Adjustable Vane Or Working Fluid Control Means Patents (Class 415/148)
  • Patent number: 8919119
    Abstract: Various systems and methods are described for a variable geometry turbine. In one example, a turbine nozzle comprises a central axis and a nozzle vane. The nozzle vane includes a stationary vane and a sliding vane. The sliding vane is positioned to slide in a direction substantially tangent to an inner circumference of the turbine nozzle and in contact with the stationary vane.
    Type: Grant
    Filed: August 16, 2011
    Date of Patent: December 30, 2014
    Assignee: Ford Global Technologies, LLC
    Inventors: Harold Huimin Sun, Jizhong Zhang, Liangjun Hu, Dave R. Hanna
  • Publication number: 20140377056
    Abstract: An air shield apparatus includes a bracket, a number of baffles, and a connecting member. The bracket includes two opposite side plates. Each baffle includes a blocking piece placed between the side plates of the bracket, and a shaft located at a first side of the blocking piece. The shafts are rotatably connected to the side plates of the bracket. The connecting member includes a connecting pole and a number of pivot portions pivotably connected to the baffles.
    Type: Application
    Filed: March 21, 2014
    Publication date: December 25, 2014
    Inventors: XIAO-FENG MA, CHAO ZHAO
  • Publication number: 20140369806
    Abstract: An engine system having a compressor coupled to an engine and supplying air to an intake manifold, a throttle controlling the supply of air from the compressor to the intake manifold, a compressor recirculation valve (CRV) having a pneumatic control chamber, and a throttle aspirator having its motive section in fluid communication with an inlet of the throttle and its discharge section in fluid communication with an outlet of the throttle and its suction port in fluid communication with the pneumatic control chamber of the CRV. Such an engine system automatically minimizes surge during boost without a control system activating the CRV. Here, the CRV operates purely on the changes in pressure within the system forming a loop that resets itself. In another embodiment, a gate valve and a vacuum canister may be included rather than having the throttle aspirator directly connected to the CRV's pneumatic control chamber.
    Type: Application
    Filed: June 13, 2014
    Publication date: December 18, 2014
    Inventors: Dave Fletcher, Brian M. Graichen, Keith Hampton, Matt Gilmer, James H. Miller, Steve Long
  • Patent number: 8909454
    Abstract: A compression system includes a compressor with adjustable inlet guide vanes (IGVs) and variable stator vanes (VSVs) that are adjustable independently of each other. IGV and VSV control units produce respective IGV and VSV reference commands responsive to respective first and second inputs that may be responsive to measured properties of the compression system. The second input may be provided by a model of the compressor or of the compression system responsive to measured properties. The second input may particularly be an estimate of a property not directly observable, such as stall margin or efficiency.
    Type: Grant
    Filed: April 8, 2011
    Date of Patent: December 9, 2014
    Assignee: General Electric Company
    Inventor: Karl Dean Minto
  • Publication number: 20140356138
    Abstract: A refrigeration system includes a chiller having a refrigerant loop. A compressor is part of and in fluid communication with the refrigerant loop. The compressor has two stages, one with a variable geometry diffuser and one with a fixed geometry diffuser.
    Type: Application
    Filed: January 23, 2012
    Publication date: December 4, 2014
    Inventors: Lin Sun, Joost Brasz, Mogens Rasmussen
  • Publication number: 20140341716
    Abstract: A cryogenic liquid turbine is provided, wherein, an impeller end of the rotor and a nozzle assembly are received into a cavity of a volute (1), and a main part of the volute (1) is put into a perlite cold box (3); an insulation pad (2) is used between the volute (1) and a machine housing (9) to insulate heat; an impeller outlet is connected to a diffuser pipe (20). A nozzle assembly is connected to the machine housing (9) by a nozzle compression flange (27); a nozzle compression plate adjusts a compactness of nozzle vanes (18) by a disc spring (25); a nozzle turntable (14) is axially and rotatably connected on a nozzle chassis (17), and adjusts the nozzle vane stagger angle by a adjusting mechanism passing through the volute (1); impeller shroud side seal is axially fixed on the nozzle compression flange (27), and a shaft seal (5) is axially fixed on a seal gas part (4); the seal gas part (4) and an oil seal (6) are axially fixed on the machine housing (9) by a bolt (15).
    Type: Application
    Filed: December 30, 2011
    Publication date: November 20, 2014
    Inventors: Jinju Sun, Ke Wang, Peng Song
  • Publication number: 20140341761
    Abstract: A variable-nozzle turbocharger includes a turbine housing and a center housing, and a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. The vanes extend between the nozzle ring and an opposite wall of the nozzle. An axially floating vane sealing ring is disposed in an annular recess formed in the face of the nozzle ring adjacent proximal ends of the vanes. The vane sealing ring is urged by exhaust gas pressure differential toward the proximal ends of the vanes, and the vanes are thus urged toward the opposite nozzle wall so that distal ends of the vanes are close to or abutting the wall, resulting in a reduction or closing of the gaps at the proximal and distal ends of the vanes.
    Type: Application
    Filed: June 15, 2011
    Publication date: November 20, 2014
    Inventors: Emmanuel Severin, Pierre Barthelet
  • Publication number: 20140328667
    Abstract: An improved variable geometry diffuser (VGD) mechanism for use with a centrifugal compressor. This VGD mechanism extends substantially completely into the diffuser gap so that the VGD mechanism may be used more fully to control other operational functions. The VGD mechanism may be used to minimize compressor backspin and associated transient loads during compressor shut down by preventing a reverse flow of refrigerant gas through the diffuser gap during compressor shutdown, which is prevented because the diffuser gap is substantially blocked by the full extension of the diffuser ring. During start-up, transient surge and stall also can be effectively eliminated as gas flow through the diffuser gap can be impeded as load and impeller speed increase, thereby alleviating the problems caused by startup loads at low speeds. The VGD mechanism can be used for capacity control as well so as to achieve more effective turndown at low loads.
    Type: Application
    Filed: November 4, 2013
    Publication date: November 6, 2014
    Inventors: Steven T. Sommer, Jeb W. Schreiber, Justin P. Kauffman, Kurt F. Nenstiel (Deceased)
  • Publication number: 20140321987
    Abstract: A system for directing airflow, a gas turbine engine, and a method for directing airflow exiting a cascade of internal airfoils are provided. An exemplary system for directing airflow includes a cascade of internal structures spanning an airflow path. Each of the internal structures includes a rounded trailing edge. The system further includes at least one plasma generating device positioned on the rounded trailing edge of each internal structure. Also, the system includes a controller configured to selectively energize and de-energize each plasma generating device to selectively alter a direction of local airflow around each internal structure to produce a combined airflow exiting the cascade in a desired direction.
    Type: Application
    Filed: March 15, 2013
    Publication date: October 30, 2014
  • Publication number: 20140321990
    Abstract: A circular ring-shaped shroud plate is arranged between a scroll passage and a turbine chamber. The shroud plate has a through-hole that penetrates therethrough in a direction along an axis of a turbine shaft. A variable nozzle is supported in an openable/closable manner on the shroud plate by a shaft inserted through the through-hole. A gap between the shroud plate and a turbine housing in the direction along the axis is partitioned into a first space that communicates with an outlet of exhaust gas that faces the through-hole and is provided upstream of a turbine wheel with respect to the flow of exhaust gas, and a second space that communicates with the scroll passage, by a disc spring that is so arranged as to surround the turbine wheel.
    Type: Application
    Filed: November 13, 2012
    Publication date: October 30, 2014
    Inventors: Hiroaki Ikegami, Tsuyoshi Uesugi
  • Publication number: 20140321989
    Abstract: A wind turbine shaft includes tubes that are centered on a longitudinal axis, coupled to rotate together about the axis, and movable telescopically along the axis between a retracted condition and an extended condition. A mounting structure is configured to mount wind turbine vanes on the tubular structure when the tubes are in the extended condition. A generator has a pair of parts including a rotor and a stator, and is configured for coupling with the tubular structure for one of the parts to rotate about the axis with the tubular structure while the other part is stationary.
    Type: Application
    Filed: April 23, 2014
    Publication date: October 30, 2014
    Inventors: Justin R. Chambers, James E. Smith, Chad C. Panther, Andrew D. Lowery
  • Publication number: 20140321988
    Abstract: This disclosure describes improvements that can expand the operating envelope of a compressor device. These improvements implement devices that vary flow parameters of a working fluid at the exit of the compressor device. In one embodiment, the device utilizes a nozzle that installs into the discharge opening on a volute of a centrifugal compressor. Actuation of the nozzle modifies a flow area through which the working fluid exits the centrifugal compressor. The change in the flow area increases the velocity of the working fluid, without the need to change the operating speed and/or other operating parameters of the centrifugal compressor.
    Type: Application
    Filed: April 29, 2013
    Publication date: October 30, 2014
    Inventor: Dale Eugene Husted
  • Publication number: 20140314542
    Abstract: An exhaust diffuser for a gas turbine engine gas turbine engine includes a multiple of circumferentially spaced struts that extend between an inner gaspath wall and an outer gaspath wall, at least one of the multiple of circumferentially spaced struts movable about a strut axis.
    Type: Application
    Filed: December 21, 2012
    Publication date: October 23, 2014
    Applicant: United Technologies Corporation
    Inventor: United Technologies Corporation
  • Publication number: 20140314549
    Abstract: A flow manipulating arrangement for a turbine exhaust diffuser includes a strut having a leading edge and a trailing edge, the strut disposed within the turbine exhaust diffuser. Also included is a plurality of rotatable guide vanes disposed in close proximity to the strut and configured to manipulate an exhaust flow, wherein the plurality of rotatable guide vanes is coaxially aligned and circumferentially arranged relative to each other. Further included is an actuator in operative communication with the plurality of rotatable guide vanes and configured to actuate an adjustment of the plurality of rotatable guide vanes. Yet further included is a circumferential ring operatively coupling the plurality of rotatable guide vanes, wherein the actuator is configured to directly actuate rotation of one of the rotatable guide vanes, and wherein the circumferential ring actuates rotation of the plurality of rotatable guide vanes upon rotational actuation by the actuator.
    Type: Application
    Filed: April 17, 2013
    Publication date: October 23, 2014
    Applicant: General Electric Company
    Inventors: Srinivas Rao Pakkala, Manjunath Bangalore Chengappa, Kamlesh Mundra, Antanu Sadhu, Kunal Upendra Sakekar, Moorthi Subramaniyan, Lisa Anne Wichmann
  • Publication number: 20140314550
    Abstract: The present invention relates to a stator stage (100) for a gas turbine and a method of adjusting a relative position between a vane segment (110) and a centre section (101) of the stator stage. A groove (102) is formed between a first rim (103) and a second rim (104) of a radially outer edge of the centre section, wherein the groove, the first rim and the second rim run along a circumferential direction (131). The vane segment comprises a radially inner shroud (111) from which a protrusion (112) protrudes radially inwards. The protrusion is inserted into the groove. An adjusting pin (120) comprises a first end section (121), a second end section (122) and an eccentric section (123) which runs between the first end section and the second end section.
    Type: Application
    Filed: October 23, 2012
    Publication date: October 23, 2014
    Inventors: Paul Jenkinson, Mike McKenna
  • Publication number: 20140314540
    Abstract: A synchronization ring for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a synchronization ring for a variable vane assembly. A plurality of rollers are attached to the synchronization ring for engaging a case on the gas turbine engine.
    Type: Application
    Filed: November 5, 2012
    Publication date: October 23, 2014
    Inventor: United Technologies Corporation
  • Patent number: 8863513
    Abstract: A compressor including a housing assembly that includes a bearing housing and a compressor housing, and a movable vane. In the housing assembly, a diffuser is formed by a first diffuser wall portion and a second diffuser wall portion. The movable vane includes a base portion and vane portions. The movable vane is movable between a projected position where a facing surface of the base portion contacts with a positioning surface provided in a storage chamber and a retracted position. The compressor housing includes an affixing portion projecting further than the second diffuser wall portion, and a fastening surface being, provided, to the affixing portion. The compressor housing is assembled with the bearing housing by attaching the fastening surface to a mounting surface of the bearing housing. The positioning surface is provided in the storage chamber so as to be flush with the fastening surface.
    Type: Grant
    Filed: March 18, 2010
    Date of Patent: October 21, 2014
    Assignee: Toyota Jidosha Kabushiki Kaisha
    Inventor: Masakazu Tabata
  • Publication number: 20140308115
    Abstract: A controllable coolant pump of a cooling circuit for an internal combustion engine, having a pump housing, in which a pump shaft with associated impeller is rotatably arranged. The impeller conveys a coolant as a volume flow via an intake connection in a pressure or spiral channel of the coolant pump. The volume flow can be influenced by a baffle plate which encloses the outside of the impeller, the push rod of the baffle plate being guided in the pump shaft. In connection with an actuator the baffle plate can be continuously adjusted between two limit positions against the force of a spring. A control element, which has an electro-hydraulic action and which is integrated into the pump shaft, serves as an actuator, wherein the pressurized coolant in the coolant pump is provided as a hydraulic fluid.
    Type: Application
    Filed: August 9, 2012
    Publication date: October 16, 2014
    Applicant: Schaeffler Technologies GmbH & Co. KG
    Inventors: Markus Popp, Eduard Golovatai-Schmidt
  • Publication number: 20140301831
    Abstract: A turbocharger system of an embodiment includes: a wastegate valve; an electrically-operated actuator configured to adjust a valve lift of the wastegate valve; a temperature acquisition unit configured to acquire a target temperature which is a temperature of the turbocharger body or a temperature correlating with the temperature of the turbocharger body; and an actuator controller configured to control the electrically-operated actuator on the basis of the target temperature. The temperature acquisition unit acquires the target temperature, and the actuator controller controls the electrically-operated actuator on the basis of the target temperature.
    Type: Application
    Filed: June 19, 2014
    Publication date: October 9, 2014
    Applicant: IHI Corporation
    Inventors: Atsushi KOIKE, Tsuyoshi Nishiyama, Kazuhiko Shinagawa, Mitsushi Maeyama, Satoshi Kusano, Yuji Kobayashi, Masanori Okada
  • Publication number: 20140301830
    Abstract: A cabin air compressor drive ring includes an outer ring defining an axis, an inner ring co-axial with the outer ring, a plurality of webbings connecting the inner ring to the outer ring, and a plurality of vane engagement pins axially protruding from the outer ring. The vane engagement pins are spaced circumferentially about the outer ring, and the inner ring includes a drive ring bearing interface.
    Type: Application
    Filed: April 4, 2013
    Publication date: October 9, 2014
    Applicant: Hamilton Sundstrand Corporation
    Inventors: Craig M. Beers, Seth E. Rosen
  • Publication number: 20140286745
    Abstract: Actuation systems and methods for varying the angle of small turbine engine inlet guide vanes (IGV) and/or compressor stator vanes (CSV). Such systems and methods may employ a piezoelectric inchworm actuator (or a piezo stack actuator or magnetostrictive actuator, depending upon actuation requirements) to actively modify the angle of attack of a single or a cascade of inlet guide vanes or compressor stator vanes. The change in angle of attack is necessary due to large variations in engine operating envelope including but not limited to air density, velocity, temperature, and the like. The present invention is especially suitable to actuate small inlet guide vanes and compressor stator vanes found in small turbine jet engines including but not limited to those under ten (10) inches in diameter.
    Type: Application
    Filed: January 24, 2013
    Publication date: September 25, 2014
    Inventor: Razvan Rusovici
  • Publication number: 20140271113
    Abstract: A turbine engine includes a compressor, and high and low pressure turbines. The configuration includes a mid-compression station which can be, in the case of a single compressor in the middle of that compressor, or at the exit of the first compressor in the case of two compressors. Also, there is an exit pressure station at the exit of the compression system. A first gas flow line is interposed between the mid-compression station of the compressor and the low pressure turbine, and a second gas flow line is interposed between the exit pressure station of the compression system and the high pressure turbine. A first valve is coupled to the first gas flow line and modulates a low pressure flow rate of coolant in the first gas flow line, and a second valve is coupled to the second gas flow line and modulates a high pressure flow rate of coolant in the second coolant flow line.
    Type: Application
    Filed: September 27, 2013
    Publication date: September 18, 2014
    Applicant: Rolls-Royce Corporation
    Inventors: Syed Jalaluddin Khalid, Mark J. Gritton
  • Publication number: 20140271289
    Abstract: A reconfigurable grille for use in association with an axial fan, and a fan assembly including the reconfigurable grille. The reconfigurable grille includes a central hub, an outer rim, and a plurality of vanes each extending from the central hub to the outer rim. The plurality of vanes are configured to switch between at least a first configuration and a second configuration, for example, by a rotation of the central hub relative to the outer rim. The grille can further include a control element to switch the vanes between different configurations.
    Type: Application
    Filed: March 14, 2013
    Publication date: September 18, 2014
    Applicant: Kaz USA, Inc.
    Inventors: Rich Thrush, William Fiebel, Adam Sanchez, Christopher S. Kanel
  • Publication number: 20140250859
    Abstract: An axial-flow turbine according to an embodiment includes a plurality of nozzle structures and a plurality of blade structures. At least one nozzle structure includes an outer ring diaphragm and an inner ring diaphragm. The outer ring diaphragm and the inner ring diaphragm form an annular opening portion which extends in a circumferential direction therebetween. A nozzle is provided in a portion of a region of the annular opening portion in the circumferential direction, and a closing part is provided in another portion of the region of the annular opening portion in the circumferential direction. The closing part closes this other portion of the region to prevent a working fluid from flowing into this other portion of the region. A closing part medium passage is provided in the closing part and is configured to flow a cooling medium which cools the closing part.
    Type: Application
    Filed: February 19, 2014
    Publication date: September 11, 2014
    Inventors: Akihiro ONODA, Yuki Mimura, Shoko Ito
  • Patent number: 8826670
    Abstract: A method is provided for operating a gas turbine in a power station in which limits of the operating concept, which provide limits for optimization of the power station operation in respect of efficiency, service life consumption, emissions and power provision to the grid system, are adapted during operation. In particular, temperature limits and compressor inlet guide vane position limits are varied as a function of the optimization aims. A gas turbine power station is also provided for carrying out the method.
    Type: Grant
    Filed: September 3, 2010
    Date of Patent: September 9, 2014
    Assignee: Alstom Technology Ltd
    Inventors: J├╝rgen Hoffmann, Johann Josef Daxer, Bernhard Wippel, Klaus-Dieter Liedtke
  • Publication number: 20140237987
    Abstract: A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.
    Type: Application
    Filed: November 26, 2013
    Publication date: August 28, 2014
    Inventors: Matthew J. Bloxham, Craig E. Heathco, Adam D. Ford, Robert T. Duge, Thomas I. Gorman
  • Publication number: 20140234083
    Abstract: Actuator devices useable to change orientation of one or more vanes, including an actuator rod and an actuator device body configured to allow the actuator rod to move along the axis inside the actuator device body, and having an inlet flange configured to allow a third fluid to enter a space between the actuator device body and the actuator rod, and an outlet flange configured to allow the third fluid to exit the actuator device body. Besides providing a fluid seal between the first fluid and the second fluid, the third fluid may also heat the actuator rod thereby preventing ice formation.
    Type: Application
    Filed: September 6, 2012
    Publication date: August 21, 2014
    Applicant: Nuovo Pignone S.p.A.
    Inventors: Franco Sarri, Giuseppe Iurisci, Marco Pelella
  • Publication number: 20140234082
    Abstract: A synchronizing assembly for a gas turbine engine has a synchronizing ring. A bumper assembly has a cradle and a bumper held within the cradle. The cradle is secured to the synchronizing ring by at least one fastener without the fastener extending through the bumper. An engine is also disclosed.
    Type: Application
    Filed: February 12, 2014
    Publication date: August 21, 2014
    Inventors: Ryan Edward LeBlanc, Eugene C. Gasmen
  • Publication number: 20140227085
    Abstract: A fan control system includes an oscillating fan and a portable mobile device. The oscillating fan includes a housing member having a first driving motor arranged therein, and an oscillating mechanism mounted between the first driving motor and the housing member to electrically connect to the first driving motor and a receiving control unit. The portable mobile device has a touch panel forming an operation control interface, and is internally provided with a processor electrically connected to the touch panel and a transmission unit. The operation control interface produces an operation control signal when being touched, and the processor receives the operation control signal and correspondingly generates a control command to the transmission unit, from where the control command is wirelessly transmitted to the receiving control unit in the oscillating fan. The oscillating fan directly controllable via the portable mobile device has largely increased practicality and usability.
    Type: Application
    Filed: February 13, 2013
    Publication date: August 14, 2014
    Inventor: Steven Yu
  • Publication number: 20140219785
    Abstract: An exemplary variable vane actuation system for a gas turbine engine includes a vane arm attachable to a vane stem and configured to rotate the vane stem about a radially extending axis. The vane arm includes a claw feature to be press-fit onto the vane stem.
    Type: Application
    Filed: January 29, 2014
    Publication date: August 7, 2014
    Inventors: Eugene C. Gasmen, Bernard W. Pudvah, Stanley Wiecko
  • Publication number: 20140212261
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan.
    Type: Application
    Filed: December 19, 2012
    Publication date: July 31, 2014
  • Patent number: 8770925
    Abstract: A fan module includes a fan, and an air duct. The air duct includes a mounting bracket mounted to the fan, and a number of guiding plates pivotably mounted in the mounting bracket. Each guiding plate comprises a latching piece mounted to the guiding plate, The mounting bracket defines a number of groups of positioning holes, with each group of positioning holes corresponding to the latching piece of each guiding plate. The latching piece is selectively positioned by one of the corresponding group of positioning holes.
    Type: Grant
    Filed: May 27, 2011
    Date of Patent: July 8, 2014
    Assignees: Hong Fu Jin Precision Industry (ShenZhen) Co., Ltd., Hon Hai Precision Industry Co., Ltd.
    Inventor: Lei Liu
  • Publication number: 20140178181
    Abstract: It is provided with: a variable nozzle mechanism section 23; an opening degree regulating member 43 for regulating an angle of a nozzle vane 19a by bringing an outer peripheral surface 41 of an inner cylinder of a bearing housing 13 to which a nozzle mount is affixed and an inner peripheral surface of a lever plate 33 into contact; and a discharge recess 47 for discharging soot which accumulates in the gap between an inner peripheral end portion of the lever plate 33, the nozzle mount 21, and the bearing housing 13 to the inner peripheral end portion of the lever plate 33.
    Type: Application
    Filed: September 7, 2012
    Publication date: June 26, 2014
    Inventors: Naoto Tashiro, Yasuaki Jinnai, Hiroyuki Arimizu
  • Publication number: 20140169948
    Abstract: A gas turbine system includes a compressor. The compressor has a plurality of inlet guide vanes disposed at an inlet of the compressor. Furthermore, the compressor may have at least one unison ring coupled to a plurality of variable stator vanes disposed between the inlet and an outlet of the compressor. The gas turbine system includes a first actuator that may adjust a first pitch of the plurality of inlet guide vanes and a second actuator that may adjust a second pitch of the plurality of variable stator vanes. A first electric motor may drive the first actuator, while a second electric motor may drive the second actuator.
    Type: Application
    Filed: December 19, 2012
    Publication date: June 19, 2014
    Inventors: Cyron Frank Kay, John Carver Maters
  • Publication number: 20140169950
    Abstract: A variable vane includes a variable vane body that has an airfoil portion. The variable vane body is formed of a first material. A trunnion is attached at one end of the variable vane body. The trunnion includes a pivot formed of a second, different material.
    Type: Application
    Filed: December 18, 2012
    Publication date: June 19, 2014
    Inventors: David P. Dube, Steven J. Feigleson, Richard K. Hayford
  • Publication number: 20140169949
    Abstract: A stopper 30 is provided with: a nut-receiving part 44a provided on a heat insulation plate 44 that is attached to an actuator bracket 43; and a movable-side stopper part 33 provided on an actuator rod 26 that moves in relation to the heat insulation plate 44. An actuator 27 is provided with an actuator body 41 that generates driving force, and the actuator rod 26 which transmits the driving force from the actuator body 41. The movable-side stopper part 33 is provided on the actuator rod 26 that extends from the actuator body 41 to the nozzle vane side.
    Type: Application
    Filed: September 7, 2012
    Publication date: June 19, 2014
    Inventors: Naoto Tashiro, Yasuaki Jinnai, Hiroyuki Arimizu
  • Publication number: 20140154055
    Abstract: A turbocharger (1) with variable turbine geometry (VTG) having a guide grate (18) which surrounds a turbine wheel (4) radially at the outside, which has an adjusting ring (5) operatively connected to the guide blades (7) via associated blade levers (20) which are fastened to blade shafts (8) at one of the ends thereof. Each blade lever (20) has a lever head (23) which can be placed in engagement with an associated engagement recess (24), which has a base wall (26), of the adjusting ring (5), and which has a stop (25) at least for setting the minimum throughflow through the nozzle cross sections formed by the guide blades (7). The stop is a first support point (25) on the base wall (26), wherein, in the minimum throughflow position, the lever head (23) makes contact, via a wall surface (27) facing toward the base wall (26), with said first support point.
    Type: Application
    Filed: July 24, 2012
    Publication date: June 5, 2014
    Applicant: BORGWARNER INC.
    Inventors: Thomas Ramb, Dietmar Metz
  • Publication number: 20140154046
    Abstract: A gas turbine engine (100) variable nozzle (460) includes an outer shroud (461), an inner shroud (462), a variable nozzle airfoil (463), and a position selector (470). The inner shroud (462) is located radially inward from the outer shroud (461). The variable nozzle airfoil (463) extends radially between the outer shroud (461) and the inner shroud (462). The variable nozzle airfoil (463) includes a vane shaft (464) extending radially outward from the variable nozzle airfoil (463) through the outer shroud (461). The position selector (470) is coupled with the variable nozzle airfoil (463) to fixedly lock the variable nozzle airfoil (463) into one of a plurality of preselected positions.
    Type: Application
    Filed: October 25, 2012
    Publication date: June 5, 2014
    Applicant: Solar Turbines Incorporated
    Inventor: Solar Turbines Incorporated
  • Publication number: 20140154056
    Abstract: An exhaust-gas turbocharger (1) having a turbine (2) which is provided with a variable turbine geometry (18) and/or a wastegate; and having an actuator (11) which is connected to the variable turbine geometry (18) and/or the wastegate via a coupling rod (14; 14?; 14?). The coupling rod (14; 14?) is connected at its end regions (21, 22) at one side to the actuator (11) and at the other side to a pin (19) of an adjusting shaft arrangement (23; 26) of the variable turbine geometry (18) and/or of the wastegate. The pin (19) of the adjusting shaft arrangement (23; 26) is in the form of a bayonet pin, and that end region (22) of the coupling rod (14) which interacts with the pin (19) is in the form of a bayonet receptacle (24; 27) which is matched to the bayonet pin (19).
    Type: Application
    Filed: August 2, 2012
    Publication date: June 5, 2014
    Applicant: BORGWARNER INC.
    Inventors: Thomas Ramb, Nico Kanoffsky
  • Patent number: 8740548
    Abstract: A compressor variable stator vane arrangement comprises at least one stage of variable stator vanes. A speed sensor measures the rotational speed of the compressor rotor. A pressure sensor measures the outlet pressure of the compressor. A second pressure sensor, a temperature sensor and a third pressure sensor measure the total inlet pressure, the temperature and the ambient pressure at the inlet of the gas turbine engine. A processor determines a target operating line as a function of ambient pressure and total inlet pressure. The target operating line is defined to ensure the gas turbine engine operates simultaneously at both the minimum required compressor speed and the minimum required compressor outlet pressure when commanded to idle to minimize idle thrust and fuel burn. The processor determines if the operating point of the compressor, defined in terms of corrected outlet pressure and corrected rotational speed of the compressor rotor is above or below the target operating line of the compressor.
    Type: Grant
    Filed: July 15, 2009
    Date of Patent: June 3, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Arthur L. Rowe, Marc Pons Perez, Cerith Davies
  • Publication number: 20140147255
    Abstract: A variable geometry turbine comprises: a turbine wheel in a housing assembly defining a radial gas flow inlet passage; an annular wall member which is displaceable to control gas flow through the inlet passage; and a linkage mechanism comprising at least one actuating member operably connected to the annular wall member to control displacement of the wall member. The actuating member has a terminal portion defining a radially extending flange and extends in a direction substantially parallel to the turbine axis through an aperture defined by a retaining member to locate the radially extending flange in between said retaining member and annular wall member. The terminal portion is contacted by the retaining member to connect the actuating member to the annular wall member. The aperture defines a clearance to accommodate displacement of the retaining member relative to the actuating member.
    Type: Application
    Filed: December 13, 2013
    Publication date: May 29, 2014
    Applicant: Cummins Turbo Technologies Limited
    Inventors: Stephen Garrett, John F. Parker
  • Publication number: 20140134015
    Abstract: A variable-vane assembly for a turbocharger includes an annular nozzle ring supporting an array of rotatable vanes, an insert having a tubular portion sealingly received into the bore of the turbine housing and having a nozzle portion extending radially out from one end of the tubular portion and being axially spaced from the nozzle ring with the vanes therebetween, and an annular retainer ring disposed radially outward of the nozzle ring and extending generally radially inwardly. The nozzle ring's face is stepped, and a radially inner edge of the retainer ring engages the face of the nozzle ring radially outward of the step, the radially inner edge of the retainer ring having an axial thickness that is less than the step height such that a remaining portion of the step is presented to the exhaust gas flowing through the nozzle.
    Type: Application
    Filed: November 12, 2012
    Publication date: May 15, 2014
    Inventors: Julien Mailfert, Nicolas Morand, Calogero Beltrami
  • Publication number: 20140133968
    Abstract: A variable vane assembly for use in a gas turbine engine includes a variable vane, an actuator, and a mechanical linkage. The mechanical linkage connects the variable vane to the actuator. The mechanical linkage includes a bellcrank rotatable about an axis, a first bellcrank arm having a first clevis at an inner end, and a first pin extending through the first clevis and a first flange of the bellcrank to fasten the first bellcrank arm to the bellcrank.
    Type: Application
    Filed: November 15, 2012
    Publication date: May 15, 2014
    Inventors: John Holchin, Mark Boyer, Tim Harding
  • Publication number: 20140127003
    Abstract: A stator vane adjusting device of a gas turbine has a plurality of stator vanes each rotatable about a radial axis 44 and arranged in at least two radial planes, as well as at least one stator vane adjusting ring connected to the respective stator vanes and rotatable in the circumferential direction by at least one actuating device. The actuating device includes a crankshaft element rotatable about a stationary pivot axis by an actuator. A first lever is articulated by a joint to the stator vane adjusting ring, with its free end being connected by a joint to a center area of a second lever, the second lever being mounted at its one end on a stationary pivot point and at its other end being linked by a joint to a third lever, which is mounted by a joint at its free end on the crankshaft element.
    Type: Application
    Filed: November 6, 2013
    Publication date: May 8, 2014
    Applicant: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Thomas KLAUKE, Mats MOJEM, Nishanth RAJARATNAM
  • Publication number: 20140119894
    Abstract: A gas-turbine engine (100) variable nozzle (460) includes an outer shroud (461), an inner shroud (462), and a variable nozzle airfoil (463). The outer shroud (461) includes a first spherical surface (466), a radially inner surface of the outer shroud (461). The inner shroud (462) includes a second spherical surface (467), a radially outer surface of the inner shroud (462). The variable nozzle airfoil (463) includes an outer edge (468) adjacent to the first spherical surface (466) and an inner edge (469) adjacent to the second spherical surface (467). The outer edge (468) has a curve which matches the contour of the first spherical surface (466). The inner edge (469) has a curve which matches the contour of the second spherical surface (467).
    Type: Application
    Filed: October 25, 2012
    Publication date: May 1, 2014
    Inventors: John James Hensley, Ulrich Edmund Stang
  • Publication number: 20140119896
    Abstract: An exhaust gas turbocharger (1) having a compressor (2), a turbine (3) which has a turbine casing (4) in which a wastegate opening (5) is arranged and which has a charge pressure control flap arrangement (6) with a flap plate (7) which can be moved between a closed position and an open position. The flap plate (7) is provided with a guide lever (8) whose first end (9) is connected to a rear side (10) of the flap plate (7) and whose second free end (11) is guided in a curved track (12).
    Type: Application
    Filed: June 20, 2012
    Publication date: May 1, 2014
    Applicant: BORGWARNER INC.
    Inventor: Silvio Koch
  • Publication number: 20140119895
    Abstract: An inner bushing assembly (280) to provide a biasing force between a guide vane (260) and an inner ring half (261) of a gas turbine engine compressor (200) is disclosed. The inner bushing assembly (280) includes a first bushing (281), a second bushing (282), and a biasing element (283). The first bushing (281) is configured to be installed about an inner vane shaft (267) of the guide vane (260) adjacent to an airfoil (265) of the guide vane (260). The second bushing (282) is configured to be installed about the inner vane shaft (267) distal to the airfoil (265). The biasing element (283) is configured to be installed about the inner vane shaft (267) between the first bushing (281) and the second bushing (282).
    Type: Application
    Filed: November 1, 2012
    Publication date: May 1, 2014
    Inventor: John Frederick Lockyer
  • Publication number: 20140086733
    Abstract: According to an aspect of an exemplary embodiment, there is provided a compressing system including: a casing including an inlet and an outlet; a first compression unit configured to receive an inlet fluid from the inlet and compressing the inlet fluid into a first pressure fluid; a first pressure chamber configured to receive the first pressure fluid; at least one first intercooler unit configured to cool the first pressure fluid; a second compression unit configured to compress the first pressure fluid into a second pressure fluid; a second pressure chamber configured to receive the second pressure fluid; at least one second intercooler unit configured to cool the second pressure fluid; and a third compression unit configured to compress the second pressure fluid.
    Type: Application
    Filed: May 20, 2013
    Publication date: March 27, 2014
    Applicant: Samsung Techwin Co., Ltd.
    Inventor: Jae-ho CHOI
  • Patent number: 8672617
    Abstract: The invention relates to a hydraulic plant (I) that defines a path (4, 5, 6) for a forced water flow (E), and comprises at least one machine (1) of the turbine, pump or turbine-pump type, a member (8) provided with at least one deformable wall (81) and defining at least one closed volume (V8) with variable dimensions. The plant also includes means (9, 91) for supplying (Fg) the closed volume with a pressurized fluid. The member with a deformable wall (81) is mounted in a hydraulic duct (6) located downstream from a rotary portion (2) of the machine (1). The deformable wall defines, locally and downstream from the rotary portion (2), a modular section (S63) for the flow (E) passage in the hydraulic duct (6). According to the method of the invention, a pressurized fluid is injected (F9) into a closed volume having variable dimensions (V8) and defined by a member (8) provided in a hydraulic duct (6) located downstream from the rotary portion (2), in order to modulate the passage section (S63).
    Type: Grant
    Filed: November 14, 2008
    Date of Patent: March 18, 2014
    Assignee: Alstom Renewable Technologies
    Inventors: Michel Henri Couston, Michel Sabourin
  • Patent number: 8667773
    Abstract: A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor stages rotates in a first direction, and the second set rotates in a second direction. The first and second sets alternate in axial series along the flow duct, such that axially adjacent rotor stages rotate in different directions. The variable endwall segments are radially positionable, in order to regulate loading on the first and second sets of rotor stages by changing a cross-sectional flow area between the inner and outer endwalls.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: March 11, 2014
    Assignee: United Technologies Corporation
    Inventor: Peter D. Silkowski