Selectively Adjustable Vane Or Working Fluid Control For Bypass Patents (Class 415/145)
  • Patent number: 10767508
    Abstract: A gas expander includes: a casing where a swirl chamber for a gas to be expanded is formed; a turbine wheel that is housed in the casing and rotationally driven by the expanded gas; a diffuser that is mounted to the casing in a direction of a rotating shaft of the turbine wheel and includes a flow path for the expanded gas to flow in the direction of the rotating shaft; a swirl stopper that is disposed in the diffuser, faces a downstream front end surface of a boss of the turbine wheel that faces the flow path, and includes a closed swirl stopping surface that is disposed to face the downstream front end surface of the boss with a gap between the closed swirl stopping surface and the downstream front end surface; and a swirl preventing plate that circumferentially partition the flow path in the diffuser.
    Type: Grant
    Filed: February 9, 2016
    Date of Patent: September 8, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Naoto Yonemura, Daisuke Hirata, Hirotaka Higashimori
  • Patent number: 10760437
    Abstract: A turbocharger includes a turbine housing that defines a flow passage for a fluid. The turbine housing includes a turbine shroud member. The turbocharger also includes a turbine wheel supported for rotation within the turbine housing relative to the turbine shroud member. The turbine wheel is configured to rotate as the fluid flows through the flow passage. Moreover, the turbocharger includes a port extending through the turbine shroud member. The port is configured to receive a portion of the fluid flowing through the flow passage.
    Type: Grant
    Filed: January 5, 2017
    Date of Patent: September 1, 2020
    Assignee: GARRETT TRANSPORTATION I INC.
    Inventors: William Joseph Smith, Ashraf Mohamed, Derek Cooper
  • Patent number: 10683808
    Abstract: A method of applying a wear-resistant coating to aluminum sliding contact wear surfaces is disclosed. The method includes providing a plurality of parts having sliding contact wear surfaces and thermal spray coating at least one of a composite aluminum oxide and PTFE or a blend of aluminum oxide and PTFE. The disclosed method may be used to repair aluminum parts subject to sliding contact wear as well as in the design of new aluminum parts subject to sliding contact wear. Improved compressor bleed valves for gas turbine engines and improved fan exit case assemblies are also disclosed.
    Type: Grant
    Filed: November 6, 2013
    Date of Patent: June 16, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: William Bogue, Timothy J. Tabor
  • Patent number: 10626801
    Abstract: An example method to extract bleed air from an aircraft engine includes extracting, via a plenum positioned in a compressor of the aircraft engine, bleed air from a first bleed port associated with a first stage of a compressor and a second bleed port associated with a second stage of the compressor. The plenum is configured to combine the extracted bleed air from the first and second bleed ports and fluidly couple the extracted bleed air to one or more systems of an aircraft. The method includes regulating a pressure of the extracted bleed air in the plenum by adjusting a flow of bleed air through the first bleed port via a first valve associated with the first bleed port and adjusting a flow of bleed air through the second port via a second valve associated with the second bleed port.
    Type: Grant
    Filed: April 17, 2017
    Date of Patent: April 21, 2020
    Assignee: The Boeing Company
    Inventors: Steve G. Mackin, Sean C. Thomas, Brian W. Debronsky
  • Patent number: 10570813
    Abstract: An exhaust manifold for an internal combustion piston engine having a first row of at least two cylinders inclined relative to a vertical plane and a second row of at least two cylinders inclined relative to the vertical plane, where the two rows of cylinders form a V configuration with the vertical plane being approximately equidistant between the two rows. The exhaust manifold in one aspect comprises plural exhaust stack assemblies for receiving exhaust gas from the first row of cylinders, an elongate manifold plenum having a terminal portion defining an exhaust gas passageway, and an exhaust gas routing circuit joined to the manifold plenum. The routing circuit comprises a turbocharger support column and a bypass pipe. The turbocharger support column is joined at a first junction with the manifold plenum, extends in a generally perpendicular direction from the elongate manifold plenum and terminates in a first exhaust gas outlet adapted for connection to a turbocharger.
    Type: Grant
    Filed: October 24, 2018
    Date of Patent: February 25, 2020
    Assignee: 500 Group, Inc.
    Inventors: Paolo Tiramani, Kyle Denman
  • Patent number: 10519812
    Abstract: A turbine (3) includes: a turbine impeller chamber (43) having a tubular outflow portion (432), from which an exhaust gas flows out in an outflow direction (F) substantially parallel to an axis (C) of a turbine impeller (5); a bypass flow passage (491) bypassing the inside of the turbine impeller chamber; an outer duct (47) having an inner peripheral surface (475) that expands in diameter in the outflow direction from the outflow portion; and an inner duct (48) that extends in the outflow direction from the outflow portion. A diffuser flow passage (483) that expands in diameter in the outflow direction is disposed in the inner duct at least in a portion between the outflow portion and a distal end portion (481a). An outlet (492) of the bypass flow passage and a waste gate valve (493) that opens and closes the outlet are disposed on the inner peripheral surface.
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: December 31, 2019
    Assignee: Honda Motor Co., Ltd.
    Inventors: Naoki Itoh, Naoki Kuno, Takashi Sakakibara
  • Patent number: 10487751
    Abstract: A gas turbine engine includes a compressor section having multiple stages, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a bleed structure radially outward of the stages. The bleed structure includes a body structure having a first set of openings radially outward of a first stage and a second set of openings radially outward of a second stage. The bleed structure further includes a circumferential sleeve configured to cover the first set of openings in a first position and configured to cover the second set of openings in a second position. An actuator is coupled to the circumferential sleeve and is configured to articulate the sleeve between the first and second positions.
    Type: Grant
    Filed: October 2, 2017
    Date of Patent: November 26, 2019
    Assignee: United Technologies Corporation
    Inventor: Enzo DiBenedetto
  • Patent number: 10465685
    Abstract: The invention discloses a compressor. The compressor includes a first primary cylinder, a second primary cylinder and a secondary cylinder, which are stacked, a separator is provided between two adjacent cylinders. The first primary cylinder is provided with a first air entry, the second primary cylinder is provided with a second air entry, and the secondary cylinder is provided with an air outlet. The first primary cylinder and the second primary cylinder are connected in serial to the secondary cylinder after being connected in parallel. A refrigerant entering the first air entry and the second air entry is discharged from the air outlet after primary or/and secondary compression. The two separators are divided into a first separator and a second separator. Any one or two of the first separator, the second separator and a lower flange may be provided with a slide piece control device.
    Type: Grant
    Filed: April 30, 2015
    Date of Patent: November 5, 2019
    Assignee: GREEN REFRIGERATION EQUIPMENT ENGINEERING RESEARCH CENTER OF ZHUHAI GREE CO., LTD.
    Inventors: Hui Huang, Yusheng Hu, Huijun Wei, Liping Ren, Jia Xu, Jian Wu, Ouxiang Yang, Shebing Liang, Huifang Luo, Hongwei Zhu
  • Patent number: 10458206
    Abstract: A wellhead assembly for use with a well that includes a production tree, a production line for carrying produced fluid from the production tree, and a choke in the production line. The choke assembly includes a turbine member that rotates in response to fluid flowing through the production line. The kinetic energy of the rotating turbine is converted into electricity by a generator that is coupled with the turbine member. Selectively impeding turbine rotation with a brake system introduces a pressure drop in the production line fluid, and which regulates flow of the production line fluid. The turbine member can be disposed in a straight run of the production line, or adjacent a bend in the production line.
    Type: Grant
    Filed: October 6, 2016
    Date of Patent: October 29, 2019
    Assignee: Saudi Arabian Oil Company
    Inventors: Faisal M. Al-Dossary, Mohammed S. Al-Zahrani
  • Patent number: 10393128
    Abstract: A bleed of valve comprises a ring axially translatable between a retracted position in which the ring is configured to close an annular bleed off opening defined in a converging portion of a radially outer annular wall of a gas turbine engine gaspath and a deployed position in which the ring protrudes into the gaspath to mechanically scoop out incoming air and water/hail particles.
    Type: Grant
    Filed: May 26, 2015
    Date of Patent: August 27, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Tibor Urac, Karan Anand
  • Patent number: 10358974
    Abstract: A closed loop thermal cycle expander bypass flow control is described. An expander is positioned within and surrounded by a housing to receive a working fluid and rotate in response to expansion of the working fluid flowing through the expander. A bypass channel is positioned within and surrounded by the housing to define a fluid flow path that bypasses the expander. A fluid flow control sub-assembly is fluidically coupled to the expander and the bypass channel, and attached to the housing. The fluid flow control sub-assembly can receive the working fluid at a housing inlet and either flow the working fluid through the expander and block the working fluid from flowing through the bypass channel, or flow the working fluid through the housing bypassing the expander, flow the working fluid out via a housing outlet, and block the working fluid from flowing through the expander.
    Type: Grant
    Filed: October 25, 2017
    Date of Patent: July 23, 2019
    Assignee: Calnetix Technologies, LLC
    Inventors: Doug Ausdemore, Shamim Imani
  • Patent number: 10359054
    Abstract: The present application proposes an axial turbomachine compressor comprising a rotor with at least one annular row of rotor blades, a stator casing surrounding the row of rotor blades, the casing including a device for generating counter-vortexes. During operation of the compressor, the movement of the blades creates leakage vortexes at the blade tip. The generating device in turn injects counter-vortexes rotating in the opposite direction to the leakage vortexes in order to counter the leakage vortexes. This improves the surge margin of the compressor. The present application also provides a method for controlling the stability of a turbomachine compressor by counter-vortex injection.
    Type: Grant
    Filed: June 16, 2016
    Date of Patent: July 23, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Stéphane Hiernaux
  • Patent number: 10287992
    Abstract: A hybrid variable bleed valve includes a static bleed slot disposed in a transition duct defining a flow path for a core air flow, a variable bleed valve door disposed radially outwardly of the transition duct and the static bleed slot, a radially inward bleed cavity defined radially outwardly of the transition duct and radially inward of the variable bleed valve door for collection of a plurality of particulates and a pressure recovery return duct in fluid communication with the radially inward cavity and the transition duct. The hybrid variable bleed valve apparatus operable to open and close the variable bleed valve door to a booster bleed flow, flowing radially outwardly from the static bleed slot, for extraction of the particulates and provide a pressure recovery flow into the core air flow via the pressure recovery return duct. The hybrid variable bleed valve configured for use in a gas turbine engine.
    Type: Grant
    Filed: August 26, 2015
    Date of Patent: May 14, 2019
    Assignee: General Electric Company
    Inventors: Chiong Siew Tan, Hsiung-Wei Yeong
  • Patent number: 10180068
    Abstract: A gas turbine unit having a compressor section, a combustion chamber section containing at least one combustion chamber, and a turbine section, wherein, starting from a compressor inlet, a flow path extends. The gas turbine unit is equipped with at least one first and one second cooling air path. The first cooling air path draws off compressed air from the flow path upstream of the at least one combustion chamber. The first cooling air path has a higher pressure level than the second cooling air path and feeds the cooling air. The second cooling air path has a draw-off point in the compressor section, and extends from the compressor section to the turbine section, bypassing the at least one combustion chamber. After components have been cooled, the first cooling air path feeds the cooling air into the second cooling air path at an infeed point as additional cooling air.
    Type: Grant
    Filed: November 5, 2015
    Date of Patent: January 15, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventor: Lennard Helmers
  • Patent number: 10151302
    Abstract: Exemplary compact wind power generation systems are configured to be suitable for residential and other locations where concealed moving parts are desirable. The wind power generation systems utilize a propeller disposed behind a contracting inlet. The propeller blades may be oriented “into the wind” to develop consistent torque across a variety of wind speeds. The propeller may rim-drive power generation components, further reducing vibration, or may share a common rotational axis with the power generation components.
    Type: Grant
    Filed: February 15, 2016
    Date of Patent: December 11, 2018
    Assignee: Arizona Board of Regents on behalf of Arizona State University
    Inventors: Timothy T. Takahashi, Calahan B. Campton, Donald L. Wood
  • Patent number: 10125781
    Abstract: A compressor for a gas turbine engine includes a stator and a rotor. The stator includes first and second stator vanes attached to first and second vane platforms, respectively. The rotor includes a plurality of rotor blades that rotate with respect to the stator. An inner stator casing supports the first and second vane platforms and encloses the stator and the rotor. An outer stator casing encloses the inner stator casing, and a bleed cavity is disposed therebetween. At least one diffuser is disposed between the first vane platform and the second vane platform, and is configured to allow air communication between the inner stator casing and the bleed cavity. An exit opening of the diffuser is disposed within the bleed cavity at a location separate from the inner stator casing and the outer stator casing.
    Type: Grant
    Filed: December 30, 2015
    Date of Patent: November 13, 2018
    Assignee: General Electric Company
    Inventors: Kevin Samuel Klasing, Robert Proctor, Jonathan Russell Ratzlaff, Thomas Matthew Doerflein
  • Patent number: 10094387
    Abstract: A turbocharger for an internal combustion engine has a housing (12) in which elements (18, 44) are arranged. An optical duct (24) is formed in the housing (12) and is assigned to at least one of the elements (18). The optical duct (24) is assigned an infrared detector (28) that is designed to detect infrared radiation (30) from the at least one element (18) through the optical duct (24) to determine a temperature (T) of the at least one element (18).
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: October 9, 2018
    Assignee: DR. ING. H.C.F. PORSCHE AKTIENGESELLSCHAFT
    Inventors: Johannes Wuest, Maximilian Fischer
  • Patent number: 10094385
    Abstract: A multistage centrifugal pump includes a foot part (1) and a head part (7), between which several pump stages are arranged. Each of the pump stages includes an impeller (4) and a housing (5) surrounding the impeller (4). The housings (5) are arranged over one another. The housings (5) together with an outer casing (9) form an annular channel (8). The housings (5) together with an outer casing (9) are clamped via clamping bolts (11) which are fastened on the head part (7) and the foot part (1). The clamping bolts (11) are arranged within the annular channel (8).
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: October 9, 2018
    Assignee: GRUNDFOS HOLDING A/S
    Inventors: Steen Mikkelsen, Carl-Christian Danielsen
  • Patent number: 10087840
    Abstract: A de-icing system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a forward assembly and a rear assembly adjacent to the forward assembly. One of the forward assembly and the rear assembly is rotatable relative to the other to generate an amount of air friction between said forward and rear assemblies.
    Type: Grant
    Filed: March 31, 2014
    Date of Patent: October 2, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas W. Ward, Scot A. Webb
  • Patent number: 10006347
    Abstract: A method for operating an engine system is provided. The method includes during a first condition, flowing exhaust gas from a first exhaust gas conduit to a first turbine inlet of a turbine and flowing exhaust gas from a second exhaust gas conduit to a turbine bypass conduit and during a second condition, flowing exhaust gas from the first exhaust gas conduit to the first turbine inlet and exhaust gas from the second exhaust gas conduit to a second turbine inlet.
    Type: Grant
    Filed: November 5, 2015
    Date of Patent: June 26, 2018
    Assignee: Ford Global Technologies, LLC
    Inventors: Paul Joseph Tennison, Daniel William Kantrow, Curtis Michael Bauer, Sr.
  • Patent number: 9856787
    Abstract: A valve device of a turbocharger includes: a valve seat disposed on an entrance of a fluid passage divided into at least two branches, and an opening/closing valve coupled to a rotary shaft rotatably disposed adjacent to the valve seat. The valve seat has a contact surface which is flat and a dividing section which extends across the entrance and divides the entrance into two entrance sections. The opening/closing valve closes the entrance of the fluid passage disposed in the valve seat. The bottom surface of the opening/closing valve is in surface contact with the contact surface of the valve seat. The central portion of the opening/closing valve corresponding to the dividing section is spaced apart from the dividing section at a predetermined distance.
    Type: Grant
    Filed: December 1, 2015
    Date of Patent: January 2, 2018
    Assignees: Hyundai Motor Company, Kia Motors Corporation, Keyyang Precision Co., Ltd.
    Inventors: Dong Ho Chu, Kyu Sik Cho
  • Patent number: 9816436
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft, a first bearing structure and a second bearing structure that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.
    Type: Grant
    Filed: May 21, 2014
    Date of Patent: November 14, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jorn A. Glahn, William K. Ackermann, Clifton J. Crawley, Philip S. Stripinis
  • Patent number: 9744660
    Abstract: A control line operating system includes a first piston having a first pressure face and a second pressure face, a first control line in operable communication with the first pressure face of the first piston, a second piston having a third pressure face and a fourth pressure face and a second control line in operable communication with the third pressure face of the second piston. Both the first piston and the second piston are in operable communication with a tool such that pressure increases in either the first control line or the second control line can cause actuation of the tool, the first control line is in operable communication with the fourth pressure face of the second piston and the second control line is in operable communication with the second pressure face of the first piston.
    Type: Grant
    Filed: December 4, 2013
    Date of Patent: August 29, 2017
    Assignee: BAKER HUGHES INCORPORATED
    Inventors: Brett Cullen Jones, Samuel C. Kucera
  • Patent number: 9739282
    Abstract: A turbocharger system is disclosed, including a turbine and compressor and a rotary valve unit. The rotary valve unit comprises a fixed valve seat and a rotary 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 valve unit includes a valve housing that defines a first flow passage and a second flow passage, and the valve member and valve seat are disposed in the second flow passage. A turbocharger system is also disclosed, including a turbine and compressor and the rotary valve unit. The rotary valve unit is coupled with the turbine such that exhaust gas that has passed through the turbine wheel is fed into the first flow passage of the rotary valve unit, and exhaust gas that has bypassed the turbine wheel is fed into the second flow passage of the rotary valve unit.
    Type: Grant
    Filed: December 13, 2011
    Date of Patent: August 22, 2017
    Assignee: Honeywell International Inc.
    Inventors: Alain Lombard, Johann Kurtzmann, Nicholas Serres, Jean-Jacques Laissus
  • Patent number: 9657647
    Abstract: Methods and apparatus to adjust bleed ports on an aircraft engine are disclosed. An example apparatus for bleeding air from a multi-stage compressor of an aircraft engine includes a compressor case having a plurality of bleed ports. A first bleed port is associated with a first stage of a compressor, and a second bleed port is associated with a second stage of the compressor. The apparatus includes a plenum connected to the compressor case to define a plenum cavity. The plenum fluidly coupling the first and second bleed ports to a fluid conduit for providing bleed air to one or more systems of an aircraft. The apparatus also includes a bleed port selection mechanism located within the plenum cavity. The bleed port selection mechanism including a first portion proximate the first bleed port and operable to prevent fluid flow through the first bleed port.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: May 23, 2017
    Assignee: The Boeing Company
    Inventors: Steve G. Mackin, Sean C. Thomas, Brian W. Debronsky
  • Patent number: 9611627
    Abstract: A pressure supply system for a fresh water system is provided. The pressure supply system includes a water reservoir having a bleed air inlet and a water outlet. The pressure supply system also includes a water pump so as to load water, which is loaded with bleed air pressure, with a further pressure downstream until a predetermined nominal operating pressure range is achieved. As a result, the pressure supply system provides an increased redundancy by pressure generator assemblies which are based on different pressure generation principles.
    Type: Grant
    Filed: February 7, 2014
    Date of Patent: April 4, 2017
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Axel Schreiner, Paolo Cavarero, Ralf Menshausen, Markus Wirth, Michael Rempe, Carlos Rosero
  • Patent number: 9518513
    Abstract: A gas turbine engine variable bleed apparatus includes a variable bleed valve door disposed in a bleed inlet in a transition duct, rotatable about two or more separate pivot points, operable to open and close an aft bleed slot extending outwardly from transition duct, and operable to open and close a forward bleed slot extending inwardly into transition duct. Door is operable to transition between a first position with aft bleed slot open and forward bleed slot closed to a second position with aft bleed slot closed and forward bleed slot open without fully closing door. Door is rotatable about an axis translatable between the two or more separate pivot points. Transition duct having a transition duct conical angle at least about 10 degrees greater than a booster conical angle of a booster outer shroud upstream of transition duct.
    Type: Grant
    Filed: January 25, 2013
    Date of Patent: December 13, 2016
    Assignee: General Electric Company
    Inventors: Byron Andrew Pritchard, Jr., Paul Alfred Pezzi, George Gould Cunningham, III, Thomas Ory Moniz, Steven Alan Ross, Raymond Gust Holm
  • Patent number: 9458855
    Abstract: A unique compressor includes a rotating compressor blade having a blade tip; a compressor case having a blade track disposed opposite the blade tip; and a tip clearance control system including a fluid impingement structure. This structure has a plurality of openings to impinge a fluid received from a diffuser onto the compressor case. The tip clearance control system is configured to control a clearance between the blade tip and the blade track by impinging the fluid onto the compressor case and modulating the same with a valve in fluid communication with the diffuser. A further form includes a unique gas turbine engine having a compressor with a compressor blade tip, a compressor case disposed opposite the blade tip, and a fluid impingement structure having openings to impinge a fluid onto the case. Also included are other apparatuses, systems, devices, hardware, methods, and combinations for compressor blade tip clearance control.
    Type: Grant
    Filed: December 22, 2011
    Date of Patent: October 4, 2016
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Douglas David Dierksmeier, Steven Lester Grant, James Christopher Muskat
  • Patent number: 9394792
    Abstract: A system for minimizing non-integral vibrations in rotor blades located in a compressor section of a gas turbine engine includes a casing having a plurality of bleed slots, at least one of the bleed slots being located in close proximity to a row of rotor blades, a plurality of structural ligaments, at least one of the structural ligaments extending between two adjacent ones of the bleed slots; and a channel for reducing the height of at least one of the structural ligaments so as to minimize the non-integral vibrations in the rotor blades in the row.
    Type: Grant
    Filed: October 1, 2012
    Date of Patent: July 19, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ryan Edward LeBlanc, Kevin J. Cummings, Amr Ali
  • Patent number: 9328735
    Abstract: A valve includes a body with bleed ports and a ring. The ring surrounds the body and includes two adjacent ring segments. The ring is movable between an open position and a closed position, the latter of which prevents flow through the ports.
    Type: Grant
    Filed: September 27, 2013
    Date of Patent: May 3, 2016
    Assignee: United Technologies Corporation
    Inventors: Ryan Edward LeBlanc, Kevin J. Cummings
  • Patent number: 9322371
    Abstract: A system and method for engaging a slide-in mountable fuel pump assembly with a fan cover of an internal combustion engine is disclosed. The fuel pump assembly includes a fuel pump configured to pump fuel from a fuel source to the engine and a mounting bracket affixed to or formed integrally with the fuel pump and configured to slidingly engage a fan cover of the engine so as to enable selective mounting and removal of the fuel pump assembly to and from the fan cover. The mounting bracket further includes a main plate affixed to or formed integrally with the fuel pump and a track formed on each of opposing sides of the main plate, with the track configured to slidingly engage a mating feature formed on the fan cover of the engine so as to selectively mount the fuel pump assembly to the fan cover.
    Type: Grant
    Filed: April 9, 2014
    Date of Patent: April 26, 2016
    Assignee: Champion Engine Technology, LLC
    Inventors: Mark J. Sarder, James J. Dehn
  • Patent number: 9309781
    Abstract: A splitter apparatus for a gas turbine engine includes: a splitter including: an annular outer wall which defines a convex-curved leading edge at a forward end thereof; an annular floorplate positioned radially inboard of the outer wall; and an annular first bulkhead spanning between the outer wall and the floorplate. The outer wall, the floorplate, and the bulkhead collectively define an annular splitter plenum positioned adjacent the leading edge of the outer wall. At least one exhaust passage formed in the outer wall extends past the floorplate and communicates with the exterior of the splitter. At least one jumper tube assembly passes through the first bulkhead, each configured to pass air flow from the exterior of the splitter into the plenum.
    Type: Grant
    Filed: March 18, 2011
    Date of Patent: April 12, 2016
    Assignee: General Electric Company
    Inventors: Benjamin Roby, Jarmo Monttinen
  • Patent number: 9279337
    Abstract: A splitter apparatus for a gas turbine engine includes: a splitter including: an annular outer wall which defines a convex-curved leading edge at a forward end thereof; an annular floorplate positioned radially inboard of the outer wall; and an annular first bulkhead spanning between the outer wall and the floorplate. The outer wall, the floorplate, and the bulkhead collectively define an annular splitter plenum positioned adjacent the leading edge of the outer wall. At least one exhaust passage formed in the outer wall extends past the floorplate and communicates with the exterior of the splitter. At least one jumper tube assembly passes through the first bulkhead, each configured to pass air flow from the exterior of the splitter into the plenum.
    Type: Grant
    Filed: March 18, 2011
    Date of Patent: March 8, 2016
    Assignee: General Electric Company
    Inventors: Benjamin Roby, Jarmo Monttinen
  • Patent number: 9188062
    Abstract: In a gas turbine of the invention, a first blade ring portion to which first vanes are attached and a second blade ring portion to which second vanes are attached are integrally formed to form an integrated blade ring. A second upstream pressing member is arranged on the upstream side of a second upstream isolation ring which attaches a first ring segment and a second vane stage which is arranged on the downstream side of the first ring segment to the integrated blade ring. By attaching the pressing member to the blade ring portion, the pressing member pushes and fixes the isolation ring to the downstream side, and the sealing performance of a packing is maintained.
    Type: Grant
    Filed: December 26, 2012
    Date of Patent: November 17, 2015
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Eiichi Tsutsumi, Kenichi Arase, Hitoshi Morimoto, Taichi Ozaki
  • Patent number: 9109603
    Abstract: The invention relates to an improved multi-stage centrifugal compressor (10) comprising at least four centrifugal compression stages (11,12,13,14), each including an impeller. The impellers of one pair of the stages (12,13) are mounted on a first shaft (23) coupled to a first high speed direct drive motor (16), and the impellers of another pair of the stages (11,14) are mounted on a second shaft (24) coupled to a second high speed direct drive motor (15). The speed of the first and second motors is controlled by at least one drive (25) such that the impellers are all driven at the same speed.
    Type: Grant
    Filed: December 23, 2009
    Date of Patent: August 18, 2015
    Assignee: GARDNER DENVER DEUTSCHLAND GMBH
    Inventor: Jouko Tapani Peussa
  • Patent number: 9103283
    Abstract: A link includes a link body with two ends, a ring bore with a ring bore axis and a bearing, a mount bore with a mount bore axis and a bearing. The link also has an end curvature at the end having the ring bore wherein the curvature axis is substantially perpendicular to the ring bore axis.
    Type: Grant
    Filed: June 20, 2012
    Date of Patent: August 11, 2015
    Assignee: United Technologies Corporation
    Inventors: Ryan Edward LeBlanc, Kevin J. Cummings
  • Publication number: 20150147162
    Abstract: An exhaust-gas turbocharger (1), with: a turbine housing (2) which has a turbine housing inlet (8) and a turbine housing outlet (9) for exhaust gas, and which has a wastegate duct between the turbine housing inlet (8) and the turbine housing outlet (9), and a flap arrangement (10) comprising a pivotable flap lever (12), a flap plate (11), which is connected to the flap lever (12), for opening and closing the wastegate duct, and having a spring element (17) which is arranged between the flap lever (12) and a disc (18) fastened to the flap plate (11). The spring element (17) has an outer circumferential region (23) which is supported on a sliding contact surface (20), which is of curved form, of the flap lever (12).
    Type: Application
    Filed: July 3, 2013
    Publication date: May 28, 2015
    Applicant: BorgWarner Inc.
    Inventors: Michael Stilgenbauer, Matthias Ruh, Gerald Schall
  • Patent number: 9039353
    Abstract: A turbocharger turbine which has a wastegate slide sleeve (8), which is provided in a wastegate arrangement (5) and which closes off the wastegate duct, as a shut-off element. The wastegate arrangement (5) comprises a bypass duct (6) which runs in the turbine housing (2); a wastegate duct (7) which runs in the turbine housing (2) to the turbine housing outlet (4) and which is connected via the bypass duct (6) to the turbine housing inlet (3); and a shut-off element (8) which is arranged in the turbine housing (2). The shut-off element (8) is provided to open and close the wastegate duct (7) and can be moved by means of an actuating device (9) into an open position and closed position.
    Type: Grant
    Filed: June 29, 2010
    Date of Patent: May 26, 2015
    Assignee: BorgWarner Inc.
    Inventor: Thomas Ramb
  • Publication number: 20150139777
    Abstract: A turbocharger system and method for a vehicle, wherein the system comprises a high pressure turbocharger and a low pressure turbocharger. Both the high and low pressure turbochargers are driven by exhaust gas on an exhaust side of the turbochargers. The system further comprises a first bypass conduit that bypasses the low pressure turbocharger during set events.
    Type: Application
    Filed: November 7, 2014
    Publication date: May 21, 2015
    Inventors: Goran ALMKVIST, Jonas J. BJORKHOLTZ
  • Publication number: 20150132101
    Abstract: A cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade. The compressor bleed conduit may include an upstream section and a downstream section whereby the upstream section exhausts compressed bleed air through an outlet into the downstream section through which ambient air passes. The outlet of the upstream section may be generally aligned with a flow of ambient air flowing in the downstream section. As such, the compressed air increases the flow of ambient air to the turbine blade cooling fluid supply.
    Type: Application
    Filed: November 8, 2013
    Publication date: May 14, 2015
    Inventors: Jan H. Marsh, John J. Marra
  • Publication number: 20150125272
    Abstract: A regulating flap arrangement (1) of an exhaust-gas turbocharger (3) having a flap shaft (5), which is guided by means of a bushing (10) in the turbine housing (2). A shaped sealing ring (13), as viewed in cross section, has at least one cavity (14). The shaped sealing ring (13) bears simultaneously against the first sealing surface (11) and against the second sealing surface (12), and in order to impart its sealing action, is compressed and deformed in the axial direction (15) of the flap shaft (5).
    Type: Application
    Filed: April 29, 2013
    Publication date: May 7, 2015
    Inventor: Sebastian Mack
  • Publication number: 20150125273
    Abstract: An exhaust-gas turbocharger (1) with a turbine housing (2) which has a turbine housing inlet (8) and a turbine housing outlet (9) for exhaust gas, and which has a wastegate duct (19) between the turbine housing inlet (8) and the turbine housing outlet (9), and a flap arrangement (10) having a pivotable flap plate for opening and closing the wastegate duct (19), wherein the flap plate is in the form of an elastic spring disk (11).
    Type: Application
    Filed: June 14, 2013
    Publication date: May 7, 2015
    Inventor: Juergen Tschirschke
  • Publication number: 20150118027
    Abstract: 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.
    Type: Application
    Filed: December 13, 2014
    Publication date: April 30, 2015
    Inventors: Nicolas ZIEBOLI, Hermann BURMESTER
  • Publication number: 20150104289
    Abstract: Methods and apparatus to adjust bleed ports on an aircraft engine are disclosed. An example apparatus for bleeding air from a multi-stage compressor of an aircraft engine includes a compressor case having a plurality of bleed ports. A first bleed port is associated with a first stage of a compressor, and a second bleed port is associated with a second stage of the compressor. The apparatus includes a plenum connected to the compressor case to define a plenum cavity. The plenum fluidly coupling the first and second bleed ports to a fluid conduit for providing bleed air to one or more systems of an aircraft. The apparatus also includes a bleed port selection mechanism located within the plenum cavity. The bleed port selection mechanism including a first portion proximate the first bleed port and operable to prevent fluid flow through the first bleed port.
    Type: Application
    Filed: February 25, 2014
    Publication date: April 16, 2015
    Inventors: Steve G. Mackin, Sean C. Thomas, Brian W. Debronsky
  • Publication number: 20150098803
    Abstract: 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.
    Type: Application
    Filed: March 7, 2013
    Publication date: April 9, 2015
    Inventors: Florian Kronschnabl, Roland Herfurth, Christoph Sparrer
  • Publication number: 20150071759
    Abstract: A method for controlling air flow through a compressor recirculation passage, comprising: during a first condition: reducing air flow through the compressor recirculation passage based on a margin, the margin based on a rate of air flow at a compressor inlet, a rate of air flow through the compressor recirculation passage, and a rate of EGR flow. In this way, the CRV recirculation flow may be controlled to be less than the amount that could potentially backflow into an air filter disposed in the air intake passage, thus preventing EGR contained in the CRV recirculation flow from fouling the air filter with soot, oil and water.
    Type: Application
    Filed: January 21, 2014
    Publication date: March 12, 2015
    Applicant: Ford Global Technologies, LLC
    Inventors: David Karl Bidner, Julia Helen Buckland
  • Patent number: 8961114
    Abstract: One or more heat exchangers mounted in a duct have heat transfer cooling passages therein and a variable geometry flow restrictor is integral with each of the heat exchangers. An annular slide valve axially translatable within the duct is operable to open and close or vary a variable area between the heat exchangers and one of inner and outer casings bounding the duct. The heat exchangers may be being circumferentially distributed around an annular duct and include radial or circumferentially curved heat transfer tubes or vanes.
    Type: Grant
    Filed: November 22, 2010
    Date of Patent: February 24, 2015
    Assignee: General Electric Company
    Inventor: Michael Anthony Ruthemeyer
  • Publication number: 20150050128
    Abstract: 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.
    Type: Application
    Filed: March 8, 2013
    Publication date: February 19, 2015
    Inventor: Olivier Roques
  • Publication number: 20150044033
    Abstract: 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.
    Type: Application
    Filed: October 27, 2014
    Publication date: February 12, 2015
    Applicant: IHI Corporation
    Inventor: Tomokazu MURAYAMA
  • Patent number: 8950069
    Abstract: A low leakage, integral fixed vane system for a gas turbine engine compression system which can accommodate the latest 3-D aerodynamic airfoil geometries and provide endwall ovalization control. A unitized construction wherein the vanes are integral with the case wall in the compression system.
    Type: Grant
    Filed: December 21, 2007
    Date of Patent: February 10, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Robert A. Ress, Jr.