Having Diffuser For Air Inlet Patents (Class 60/751)
  • Patent number: 11125247
    Abstract: There is disclosed a centrifugal compressor including an impeller rotatable about an axis and a diffuser downstream of the impeller. The diffuser has walls delimiting flow passages. Plasma actuators are positioned adjacent the walls and are operatively connectable to a source of electricity. The plasma actuators have a first electrode, a second electrode, and a dielectric layer therebetween. The first electrode is upstream of the second electrode. The first electrode is exposed to the flow passage. The second electrode is shielded from the flow passage by the dielectric layer. The plasma actuators are operable to generate an electric field through the dielectric layer. The plasma actuators are located closer to inlets of the flow passage than to outlets of the flow passages. A method of operating the compressor is disclosed.
    Type: Grant
    Filed: November 16, 2018
    Date of Patent: September 21, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Martin Drolet
  • Patent number: 11060726
    Abstract: A compressor diffuser is disposed between cylindrical combustion chambers that are disposed around a rotational shaft to supply combustion gas to a turbine and a compressor that is rotatable about the rotational shaft to generate compressed air. The compressor diffuser includes one end connected to an outlet of the compressor; and another end connected to an air inlet of one of the combustion chambers. The one end defines an opening and has double arc portions curving about the rotational shaft, and the other end defines an opening shaped in conformance with the cylindrical shape of the one of the combustion chambers. The compressor diffuser is disposed continuously along an extending direction of the rotational shaft from the one end to the other end.
    Type: Grant
    Filed: April 17, 2017
    Date of Patent: July 13, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Kuniaki Aoyama, Hiroyuki Yamamoto
  • Patent number: 11047576
    Abstract: An assembly for a turbomachine can include a fuel nozzle and a combustion liner. The fuel nozzle and the combustion liner can be attached to each using a plurality of clip joints such that the combustion liner is longitudinally fixed relative to the fuel nozzle but such that the combustion liner can radially move relative to the fuel nozzle.
    Type: Grant
    Filed: March 29, 2017
    Date of Patent: June 29, 2021
    Assignee: Delavan, Inc.
    Inventors: Jacob Greenfield, Thomas J. Ocken, Jason A. Ryon
  • Patent number: 11021977
    Abstract: A guide vane for use in a compressor discharge plenum of a gas turbine engine is disclosed. The guide vane comprises a guide support system, a first side panel, a second side panel, and a deflector panel secured to the mounting system and extending between the first side panel and the second side panel. The deflector panel has a curved profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1 where the X, Y, and Z values are in inches from a center point of a bottom surface of the deflector panel. The coordinate values are connected by smooth continuing arcs to form profile sections and the profile sections are joined together smoothly to form the curved profile of the guide vane.
    Type: Grant
    Filed: November 2, 2018
    Date of Patent: June 1, 2021
    Assignee: Chromalloy Gas Turbine LLC
    Inventors: Daniel L. Folkers, Zhenhua Xiao, Vincent C. Martling, Mariano Medrano
  • Patent number: 11022144
    Abstract: A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.
    Type: Grant
    Filed: March 22, 2019
    Date of Patent: June 1, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Matthew Andrew Hough, John S. Tu, Stephen C. Harmon, Paul F. Croteau, Russell B. Hanson, Joshua C. Rathgeb
  • Patent number: 11009041
    Abstract: A gas turbine engine, in which a compressed gas from a compressor is burned in a combustor and obtained combustion gas drives a turbine, includes: a compressed gas supply portion configured to supply the compressed gas obtained from the compressor to the combustor; an annular dividing guide body disposed in a diffuser that forms an upstream-side portion of the compressed gas supply portion, the dividing guide body being configured to divide the compressed gas in a radial direction; and a guide support body that supports the dividing guide body on an inner diameter side wall of the compressed gas supply portion.
    Type: Grant
    Filed: June 20, 2018
    Date of Patent: May 18, 2021
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Koji Terauchi, Daisuke Uemura, Hiroshi Kubo, Naoto Sakai, Toshimasa Miura, Yuki Ishitobi
  • Patent number: 10898627
    Abstract: A ventricular assist device for use in a human recipient includes a housing within which a series pair of turbine pump segments, each having a deswirler, are operative. The series pair of turbine pump segments provides a redundancy which in turn enhances the safety factor provided by the ventricular assist device.
    Type: Grant
    Filed: September 14, 2018
    Date of Patent: January 26, 2021
    Assignee: California Cardiac Solutions, Inc.
    Inventors: Peter DeSilva, Steve Smith
  • Patent number: 10816205
    Abstract: A pre-diffuser fairing for a gas turbine engine is disclosed. In various embodiments, the pre-diffuser fairing includes a first side wall, a first radially inward portion and a first radially outward portion and a second side wall, a second radially inward portion and a second radially outward portion. The first side wall and the second side wall are spaced apart to form a cavity configured to receive a strut.
    Type: Grant
    Filed: May 30, 2018
    Date of Patent: October 27, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Gary J Dillard, Russell B Hanson
  • Patent number: 10815891
    Abstract: An inner diffuser case for use in a combustor of a gas turbine engine includes a multiple of struts across an annular flow path between an outer shroud and an inner shroud, at least one of the multiple of struts is an open strut.
    Type: Grant
    Filed: September 27, 2013
    Date of Patent: October 27, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Chris J. Niggemeier, Karl D. Blume, John H. Mosley, Andreas Sadil
  • Patent number: 10655859
    Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.
    Type: Grant
    Filed: January 11, 2017
    Date of Patent: May 19, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, David K. Jan, Mark Matwey
  • Patent number: 10590787
    Abstract: A turboshaft engine has a principal rotational axis and comprises a power turbine, tail bearing housing, and exhaust collector arranged in axial flow series along the axis. The tail bearing housing has radially central region defining flow chamber for cooling air, and an annular duct defined around the central region and which forms at least part of exhaust flow passage for the flow of exhaust gases from the power turbine to the exhaust collector. The flow chamber is provided in fluid communication with the exhaust collector via at least one exhaust port formed in the tail bearing housing such that the flow of exhaust gases along the exhaust collector during operation of the engine educes flow of cooling air through the central flow chamber by drawing air through the or each exhaust port and into the exhaust collector.
    Type: Grant
    Filed: April 29, 2016
    Date of Patent: March 17, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Borja Navas, Peter Leyman, Lee Davitt
  • Patent number: 10519868
    Abstract: Systems and methods are provided for cleaning one or more cooling passages associated with a combustion chamber of a gas turbine engine. The gas turbine engine has a compressor section upstream from the combustion chamber. In one embodiment, a method includes: receiving a pressurized fluid from a source; directing the pressurized fluid through an inlet of a chamber such that a portion of a plurality of particles within the chamber is entrained within the pressurized fluid; and injecting the pressurized fluid with the entrained portion of the plurality of particles downstream from the compressor section through an end wall of a diffuser and deswirl system of the gas turbine engine or through a plenum upstream from the combustion chamber to clean the one or more cooling passages associated with the combustion chamber.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: December 31, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Harry Lester Kington, Nagaraja S Rudrapatna, Vladimir K Tolpygo
  • Patent number: 10337406
    Abstract: A gas turbine engine that includes a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and a bearing compartment.
    Type: Grant
    Filed: February 28, 2014
    Date of Patent: July 2, 2019
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, William K. Ackermann
  • Patent number: 10288289
    Abstract: An inner casing for a diffuser-combustor assembly of a gas turbine engine is disclosed. The inner casing may include an outer-ring, an inner-ring circumscribed by the outer-ring, and a strut having a body extending between the inner-ring and the outer-ring. In addition, the inner casing may include a reinforcing-pad.
    Type: Grant
    Filed: November 3, 2015
    Date of Patent: May 14, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jonathan Jeffery Eastwood, Dave J. Hyland, Timothy Dale
  • Patent number: 10208664
    Abstract: Combustion equipment includes annular combustion chamber having an annular upstream wall structure. Annular outer casing surrounds and is spaced from annular combustion chamber and annular inner casing is within and spaced from annular combustion chamber. Ogee shaped annular cowl is positioned upstream of annular upstream wall structure and a stage of compressor outlet guide vanes is positioned upstream of annular cowl. Pre-diffuser extends in downstream direction from stage of compressor outlet guide vanes, pre-diffuser is positioned upstream of cowl. Stage of compressor outlet guide vanes is connected to outer and inner casing. Outer fairing extends radially inwardly from outer casing such that annular outer casing, outer fairing and pre-diffuser define annular outer cavity and outer fairing is spaced from cowl or inner fairing extends radially outwardly from inner casing such that annular inner casing, inner fairing and pre-diffuser define an annular inner cavity and inner fairing is spaced from cowl.
    Type: Grant
    Filed: March 4, 2016
    Date of Patent: February 19, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Christopher Armit, Emmanuel Aurifeille, Shahrokh Shahpar, Paul Denman, Christopher Ford
  • Patent number: 10197278
    Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.
    Type: Grant
    Filed: September 2, 2015
    Date of Patent: February 5, 2019
    Assignee: General Electric Company
    Inventors: Nicholas John Bloom, Daniel Kirtley, Michael Alan Stieg, Brian Christopher Towle, Chad Holden Sutton
  • Patent number: 10139109
    Abstract: Can-annular burners for gas turbine engines with flow conditioners having locally varying, asymmetrical patterns of circumferential perforations, to promote uniform fuel-air mixture among all premixers in the burner basket. Any one or more of the perforation pattern, pattern density, perforation profiles and perforation cross sectional area is locally varied to alter circumferential airflow into the burner basket, which in turn mitigates non-uniform thru-flow variations across the burner's air inlet plane. In some embodiments, the flow conditioner asymmetric perforation patterns are tailored for individual burner locations within the engine's combustor section annular ring, which mitigates non-uniform thru-flow variation among different respective burners in the combustor section annular ring. Thru-flow uniformity within each burner and among all the combustor section burners promotes uniform engine combustion.
    Type: Grant
    Filed: January 7, 2016
    Date of Patent: November 27, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Richard L. Thackway, Charalambos Polyzopoulos, James M. Hurney
  • Patent number: 10060631
    Abstract: A hybrid diffuser case for a gas turbine engine includes an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud. An inner diffuser case wall extends downstream from an annular inner pre-diffuser case shroud. A multiple of struts extend between the annular outer pre-diffuser case shroud and the annular inner pre-diffuser case shroud.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: August 28, 2018
    Assignee: United Technologies Corporation
    Inventors: Christopher B. Lyons, Alexander W. Williams, Alexander Broulidakis
  • Patent number: 9593851
    Abstract: A combustor (10) includes a combustion chamber (18), a liner (12) surrounding the combustion chamber, and a flow sleeve (52) surrounding the liner. An annular passage is between the liner and the flow sleeve, and a fuel injector (50) is located partially in the annular passage and extending through the liner into the combustion chamber. The fuel injector includes an outer tube, an inner tube, and a flow passage. A method of supplying a fuel to a combustor includes flowing a diluent inside an outer tube extending along a liner and flowing a liquid or gaseous fuel inside an inner tube extending inside a portion of the outer tube. The method further includes flowing the diluent and the liquid or gaseous fuel through the liner and into a combustion chamber surrounded by the liner.
    Type: Grant
    Filed: June 30, 2011
    Date of Patent: March 14, 2017
    Assignee: General Electric Company
    Inventors: Borys Borysovych Shershnyov, Geoffrey David Myers, Leonid Yulyevich Ginesin
  • Patent number: 9574575
    Abstract: A diffuser is disclosed that includes a splitter having a blunt forebody useful in re-starting a boundary layer. The blunt forebody can be used to create a static pressure bow wave and interaction with a passing fluid stream that reduces a thickness of boundary layer formed on an opposing wall. The re-start in boundary layer can be used in a way that allows an upstream portion of the diffuser to be sized approaching a separation limit and a downstream portion of the diffuser to also be sized approaching a separation limit. In some forms the passages split by the blunt forebody can be sized relative to each other to balance flow between the branches.
    Type: Grant
    Filed: December 13, 2013
    Date of Patent: February 21, 2017
    Assignee: Rolls-Royce Corporation
    Inventors: Charles B. Graves, Stuart M. Bloom, Donald M. Wicksall, Jacob E. Determan
  • Patent number: 9297532
    Abstract: A can annular combustion arrangement (12) for a gas turbine engine (10), including: a combustor can (14) having an inlet (46) at a head end (62); an annular chamber (30) surrounding the combustor can (14) for delivering a flow of compressed air from a plenum (18) to the inlet (46); a fuel injector (49) configured to inject a flow of fuel into the flow of compressed air; and a flow tripping device (60) surrounding the combustor can (14) and disposed in the annular chamber (30) downstream of the fuel injector (49).
    Type: Grant
    Filed: December 3, 2012
    Date of Patent: March 29, 2016
    Assignee: Siemens Aktiengesellschaft
    Inventors: Samer P. Wasif, Juergen Meisl, Bertram Janus, Andreas Koch
  • Patent number: 9151501
    Abstract: A gas-turbine combustion chamber arrangement includes at least one centrifugal compressor as well as one centripetal annular combustion chamber, with a stator vane arrangement being provided between the centrifugal compressor and the annular combustion chamber. The stator vane arrangement for diverting the air flowing out of the centrifugal compressor is designed at an angle ? of 20° to 30°, preferably 25°, relative to the engine axis, so the airflow is passed at essentially this angle ? to the combustion chamber. The inflow area into the combustion chamber for supplying air is designed at an angle of 20° to 30°, preferably 25°, relative to the meridional plane, and the center axes of the burners or of the injection nozzles of the combustion chamber are arranged inclined at an angle ? of 30° to 40°, preferably 35°, relative to a meridional plane passing through the engine axis.
    Type: Grant
    Filed: June 14, 2012
    Date of Patent: October 6, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Dimitrie Negulescu
  • Patent number: 9003805
    Abstract: A turbomachine including an annular combustion chamber; a centrifugal compressor; an annular diffuser with a radially oriented upstream portion presenting diffusion passages connected to the outlet of the compressor; a curved intermediate portion; and a downstream portion having a series of circularly spaced-apart deflector vanes. The turbomachine also includes an outer casing externally surrounding the combustion chamber and the downstream portion. The zone of the outer casing that is situated facing the deflector vanes is covered in a coating of abradable material, and the flow passage through the downstream portion is defined on the outside by the outer casing and by the coating.
    Type: Grant
    Filed: May 20, 2009
    Date of Patent: April 14, 2015
    Assignee: SNECMA
    Inventors: Didier Hippolyte Hernandez, Romain Nicolas Lunel
  • Publication number: 20150068211
    Abstract: A can-annular gas turbine engine combustion arrangement (10), including: a combustor can (12) comprising a combustor inlet (38) and a combustor outlet circumferentially and axially offset from the combustor inlet; an outer casing (24) defining a plenum (22) in which the combustor can is disposed; and baffles (70) configured to divide the plenum into radial sectors (72) and configured to inhibit circumferential motion of compressed air (16) within the plenum.
    Type: Application
    Filed: September 12, 2013
    Publication date: March 12, 2015
    Inventor: Jose L. Rodriguez
  • Patent number: 8966877
    Abstract: An annular combustor and a method for operating a gas turbine engine over a power demand range facilitate combustion in a lean direct ignition (LDI) mode over an extended range of operating fuel air ratios. The flow primary combustion air admitted into the primary combustion zone is varied in response to power demand from a maximum air flow rate of high power demand to a minimum flow air rate of low power demand, while the flow of dilution air into a quench zone downstream of the primary combustion zone is increased from a minimum air flow rate at high power demand to a maximum air flow rate at low power demand.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventor: Randal G. McKinney
  • Patent number: 8950188
    Abstract: A fuel nozzle assembly for a gas turbine, the assembly including: a cylindrical center body; a cylindrical shroud coaxial with and extending around the center body, and a turning guide having an downstream edge extending in a passage between the center body and an inlet to the shroud, wherein the turning guide extends only partially around the center body.
    Type: Grant
    Filed: September 9, 2011
    Date of Patent: February 10, 2015
    Assignee: General Electric Company
    Inventor: Jason Thurman Stewart
  • Patent number: 8915085
    Abstract: A bleed assembly for a gas turbine engine is provided. The assembly includes: a duct having an inlet and an outlet; a bleed valve that controls the flow of bleed fluid into the inlet; and a dome-shaped diffuser screen which covers the outlet. The diffuser screen has a plurality of through-holes for passage of the bleed fluid. Each through-hole has one or more nearest-neighbour through-holes at a nearest-neighbour spacing. At the periphery of the diffuser screen, the average nearest-neighbour spacing of the through-holes at a given radial distance from the centre of the diffuser screen increases with increasing radial distance.
    Type: Grant
    Filed: December 15, 2010
    Date of Patent: December 23, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Quentin L. Balandier, John P. Vardy
  • Publication number: 20140352313
    Abstract: A diffuser strut fairing includes a top portion, a bottom portion, a pressure side portion, a suction side portion, an inner surface and an outer surface. The pressure side portion and the suction side portion extend between the top portion and the bottom portion. The exhaust diffuser strut faring further includes a flow manifold that is at least partially defined between the pressure side portion and the suction side portion. A plurality of openings is disposed along the suction side portion and are in fluid communication with the flow manifold.
    Type: Application
    Filed: May 31, 2013
    Publication date: December 4, 2014
    Applicant: General Electric Company
    Inventors: Carl Gerard Schott, Douglas Frank Beadie, Kenneth Damon Black, Khoa Dang Cao
  • Patent number: 8893511
    Abstract: A gas turbine system includes a compressor operative to output an airstream and a diffuser having an inlet to receive the airstream and an outlet to output the airstream. The outlet has an area larger than the inlet to diffuse the airstream. The gas turbine system also includes a fuel nozzle operative to receive fuel and emit the fuel in a combustor and at least one bleed duct having an inlet between the compressor and the outlet of the diffuser. The at least one bleed duct is operative to direct bleed air from downstream of the compressor to the fuel nozzle.
    Type: Grant
    Filed: June 4, 2013
    Date of Patent: November 25, 2014
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Geoffrey David Myers
  • Publication number: 20140331678
    Abstract: A system for distributing compressed air in a combustor of a gas turbine engine. The system may include a flow splitter, a center duct, an outer duct, and an inner duct configured to separate and receive compressed air from a prediffuser exit, and to route separate flows of the compressed air to separate downstream locations for the combustion reaction and for cooling. The system may include an axial mixer configured to axially receive a flow of the compressed air and to direct the flow to mix with fuel provided by an injector.
    Type: Application
    Filed: May 8, 2013
    Publication date: November 13, 2014
    Applicant: Solar Turbines Incorporated
    Inventor: Paul Stuart Cramer
  • Patent number: 8876933
    Abstract: A breather assembly for use with a gas turbine engine includes a static housing for accepting a fluidic mixture of substances, a rotatable separator having one or more fluid inlets and arranged about an axis of rotation, an exhaust outlet defined in the housing and positioned coaxially with the rotatable separator to accept fluidic exhaust from the rotatable separator, and a static diffuser supported by the housing at or near the exhaust outlet downstream from the rotatable separator. A portion of the static diffuser extends within the rotatable separator. The static diffuser includes a flow-straightening structure configured to reduce vortex flows in fluid flows passing through the exhaust outlet.
    Type: Grant
    Filed: December 8, 2010
    Date of Patent: November 4, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Keith E. Short, Michael R. Blewett
  • Patent number: 8875517
    Abstract: A diffuser for a turbine engine that includes two annular webs extending inside one another and connected between them by substantially radial vanes, wherein the downstream peripheral edge of at least one of the webs includes indentions evenly distributed about the longitudinal axis of the diffuser.
    Type: Grant
    Filed: February 20, 2009
    Date of Patent: November 4, 2014
    Assignee: SNECMA
    Inventors: Patrice Andre Commaret, Didier Hippolyte Hernandez, Romain Nicolas Lunel
  • Patent number: 8839625
    Abstract: An exemplary diffuser includes a plurality of air flow channels defined by a corresponding plurality of vanes. The vanes extend from a first side of the diffuser and define a width of the air flow channel between the corresponding plurality of vanes. The first side has at least one tapered surface extending from an inner radial position to an outer radial position. The distance between a tapered surface and a top side of the plurality of the vanes defines a depth of the air flow channel. The width of the air flow channel varies relative to the depth of the air flow channel along the length of the air flow channel.
    Type: Grant
    Filed: June 8, 2010
    Date of Patent: September 23, 2014
    Assignee: Hamilton Sunstrand Corporation
    Inventors: James C. Napier, Anthony C. Jones
  • Publication number: 20140260289
    Abstract: A diffuser is disclosed that includes a splitter having a blunt forebody useful in re-starting a boundary layer. The blunt forebody can be used to create a static pressure bow wave and interaction with a passing fluid stream that reduces a thickness of boundary layer formed on an opposing wall. The re-start in boundary layer can be used in a way that allows an upstream portion of the diffuser to be sized approaching a separation limit and a downstream portion of the diffuser to also be sized approaching a separation limit. In some forms the passages split by the blunt forebody can be sized relative to each other to balance flow between the branches.
    Type: Application
    Filed: December 13, 2013
    Publication date: September 18, 2014
    Applicant: Rolls-Royce Corporation
    Inventors: Charles B. Graves, Stuart M. Bloom, Donald M. Wicksall, Jacob E. Determan
  • Patent number: 8833087
    Abstract: A splitter is disclosed that can be coupled with a splitter support and used within a diffuser of a gas turbine engine. The splitter includes apertures for receiving a portion of the splitter support. The splitter support includes support arms that are adapted to be slidingly received within the apertures of the splitter.
    Type: Grant
    Filed: October 29, 2008
    Date of Patent: September 16, 2014
    Assignee: Rolls Royce Corporation
    Inventors: Edward Claude Rice, Stuart Bloom, John R. Louie
  • Patent number: 8800291
    Abstract: A diffuser which straightens the flow of air issuing from a centrifugal compressor in a turbine engine is provided. The diffuser having a cylindrical shape and including a first part having the form of two substantially parallel discs extending substantially radially relative to the axis of symmetry of the diffuser, a second bent part, and a third part intended to open out into a downstream cavity, positioned downstream of the diffuser and fed with air issuing from the compressor. The first part is traversed by a plurality of channels distributed evenly over its circumference and opening out on its downstream face so as to bring the air contained in the downstream cavity into communication with a bleed cavity situated upstream of the diffuser.
    Type: Grant
    Filed: June 21, 2011
    Date of Patent: August 12, 2014
    Assignee: SNECMA
    Inventors: Eric Stephan Bil, Jean-Francois Rios, Delphine Roussin-Leroux
  • Publication number: 20140144145
    Abstract: The present invention relates to a gas-turbine combustion chamber with an outer combustion chamber wall concentric to a gas-turbine center axis and with an inner combustion chamber wall, with several burners arranged spread over the circumference of the combustion chamber, and with air inlet recesses which in at least one radial plane are provided spread over the circumference on an outer combustion chamber wall and on an inner combustion chamber wall, where the burner is designed to form a flow provided with a swirl and where air inlet recesses assigned to a burner are dimensioned in differing size in order to generate airflows of differing size, characterized in that at least one of the respective air inlet recesses is designed for supplying air in the flow direction of the swirl of the combustion chamber flow and is provided with flow guidance walls.
    Type: Application
    Filed: February 22, 2012
    Publication date: May 29, 2014
    Applicants: Rolls-Royce PLC, Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Leif Rackwitz, Emmanuel Aurifeille
  • Publication number: 20140137559
    Abstract: A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber.
    Type: Application
    Filed: September 26, 2012
    Publication date: May 22, 2014
    Applicant: United Technologies Corporation
    Inventors: Frank J. Cunha, Nurhak Erbas-Sen
  • Publication number: 20140116056
    Abstract: A diffuser for use in a gas turbine engine, the diffuser having a first wall, a second wall, and a flow separator. The first and second wall define an annular cavity, with the annular cavity having an inlet. The first and second wall also forming a prediffuser that is proximate the inlet, and a dump region distal the inlet. The flow separator extends from the first wall into the annular cavity.
    Type: Application
    Filed: October 29, 2012
    Publication date: May 1, 2014
    Applicant: Solar Turbines Incorporated
    Inventors: Timothy James Caron, Peter J. Skyes, Christopher J. Meyer, Federico Liberatore
  • Publication number: 20140090400
    Abstract: The present invention discloses a novel apparatus and way for altering the airflow to a gas turbine combustion system. The apparatus comprises a flow divider mechanism which splits the airflow surrounding a combustion liner into two distinct portions, one directed towards a pilot and one directed towards a main stage combustion. The flow divider mechanism is interchangeable so as to provide a way of altering airflow splits between stages of the combustion system.
    Type: Application
    Filed: September 26, 2013
    Publication date: April 3, 2014
    Inventors: PETER JOHN STUTTAFORD, STEPHEN JORGENSEN, YAN CHEN
  • Patent number: 8572982
    Abstract: The invention relates to a gas turbine, for energy generation, with a compressor, arranged coaxially to a rotor, mounted such as to rotate, for the compression of an inlet gaseous fluid, at least partly serving for combustion of a fuel in a subsequent annular combustion chamber, with generation of a hot working medium, with an annular diffuser arranged coaxially to the rotor, between the compressor and the annular combustion chamber, for distribution and deflection of the fluid, whereby a part of the fluid is diverted as cooling fluid for the turbine stages after the combustion chamber, by means of a dividing element, arranged in the fluid flow.
    Type: Grant
    Filed: July 10, 2009
    Date of Patent: November 5, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventors: Peter Tiemann, Iris Oltmanns
  • Patent number: 8561410
    Abstract: An outlet guide vane structure for a gas turbine engine includes outlet guide vanes supported between inner and outer outlet guide walls. The guide walls form a diffuser aft of the guide vanes. The outer guide wall is secured directly to a compressor casing. A support structure, for example for supporting turbine nozzle guide vanes, is connected to an outer case of the engine at a flange. The support structure includes struts which pass through the outlet guide vane structure to provide a load path by which loads on the support structure are transferred to the outer case independent of the outlet guide vane structure.
    Type: Grant
    Filed: January 20, 2011
    Date of Patent: October 22, 2013
    Assignee: Rolls-Royce PLC
    Inventor: Thomas G. Mulcaire
  • Publication number: 20130255263
    Abstract: An air blocker ring assembly includes a proximal end and a distal end, a blocker ring, and a blocker ring support. The blocker ring support includes at least one flange radially overlapping a portion of the blocker.
    Type: Application
    Filed: March 30, 2012
    Publication date: October 3, 2013
    Inventors: Jonathan C. Wilson, Bruno E. Struck
  • Patent number: 8505305
    Abstract: A diffuser for a centrifugal compressor in a gas turbine engine, the diffuser including a diffuser ring having a series of bores defined therethrough to receive and direct air exiting the compressor, each bore being defined by a respective bore surface including a boride layer protecting the bore surface from erosion damage.
    Type: Grant
    Filed: April 20, 2007
    Date of Patent: August 13, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Reza Ziaei, Victor Salivon, Jaroslaw Wójcik
  • Patent number: 8499565
    Abstract: A turbine engine having a plenum for passing fluids from an outlet of a compressor to an inlet of a combustor that may increase the efficiency of the turbine engine. The turbine engine may include a combustor, a compressor positioned upstream of the combustor, a transition channel extending from the compressor to the combustor, and a shell extending between the compressor and a combustor portal and positioned around the at least one transition channel. The turbine engine may also include an axial diffusor in the shell near the at least one transition channel, wherein the axial diffusor may include a fluid flow recess in a trailing edge of the axial diffusor. The turbine engine may also include a wave protrusion extending from a surface positioned radially inward of the axial diffusor. The fluid flow recess and the wave protrusion may reduce fluid flow loss within the shell.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: August 6, 2013
    Assignee: Siemens Energy, Inc.
    Inventors: Robert Bland, John Battaglioli
  • Patent number: 8474266
    Abstract: A gas turbine system comprising, a diffuser operative to diffuse an airstream output from a compressor, a fuel nozzle operative to receive fuel and emit the fuel in a combustor, and at least one bleed duct operative to direct bleed air from down stream of the combustor to the fuel nozzle.
    Type: Grant
    Filed: July 24, 2009
    Date of Patent: July 2, 2013
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Geoffrey David Myers
  • Patent number: 8438855
    Abstract: A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream edge in an upstream direction.
    Type: Grant
    Filed: July 24, 2008
    Date of Patent: May 14, 2013
    Assignee: General Electric Company
    Inventor: Carl G. Schott
  • Patent number: 8438854
    Abstract: A diffuser system for a compressor for a gas turbine engine, the compressor having an impeller and the gas turbine engine having a combustor and a fuel injector proximate to the combustor, includes a first diffuser and a second diffuser. The first diffuser is configured to receive compressed air from the impeller. The second diffuser is coupled to receive the compressed air from the first diffuser. The second diffuser comprises a housing comprising a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The first wall or the second wall, or both, further form an opening through the first and second walls for the fuel injector to pass through when removed from the combustor.
    Type: Grant
    Filed: May 23, 2008
    Date of Patent: May 14, 2013
    Assignee: Honeywell International Inc.
    Inventor: Nick A. Nolcheff
  • Patent number: 8402769
    Abstract: A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.
    Type: Grant
    Filed: January 25, 2008
    Date of Patent: March 26, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventor: John David Maltson
  • Patent number: 8381532
    Abstract: The present subject matter provides a system for modifying static pressure recoveries and emissions formation within a gas turbine. The system includes a bled diffuser positioned downstream from a compressor section of the gas turbine and a bleed duct extending from the bled diffuser. The bleed duct may be configured to direct bleed air from the pressurized airflow exiting the compressor section to a secondary combustion system located downstream from the main combustion system in a combustor. The bleed air flowing into the secondary combustion system may be mixed with fuel to form an air/fuel mixture.
    Type: Grant
    Filed: January 27, 2010
    Date of Patent: February 26, 2013
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Michael John Hughes