With Attendant Coaxial Air Swirler Patents (Class 60/748)
  • Patent number: 10995716
    Abstract: A fuel supply system includes a fuel injector having an inlet conduit, a nozzle opening, and a valve needle which is moveable to selectively permit and prevent flow of fuel. The inlet conduit extends along an axis and includes an inlet conduit shoulder which is traverse to the axis. A fuel distribution conduit, which supplies fuel to the fuel injector, has external threads. A connection nut has internal threads which threadably engage the external threads of the fuel distribution conduit and also has an internal shoulder which is traverse to the axis. A first ring sector and a second ring sector each engage both the inlet conduit shoulder and the internal shoulder such that tightening of the connection nut causes the first ring sector and the second ring sector to be compressed between the inlet conduit shoulder and the internal shoulder.
    Type: Grant
    Filed: February 21, 2020
    Date of Patent: May 4, 2021
    Inventor: Ravish S. Masti
  • Patent number: 10941940
    Abstract: A burner for a gas turbine, having a combustion chamber, a first injector adapted to inject a first fuel into the combustion chamber and a second injector adapted to inject a second fuel being less reactive than the first fuel into the combustion chamber, wherein the burner is adapted to premix the fuels with an air flow before the fuel enter the reaction zone of the combustion chamber such that a first fuel flow of the first fuel has a first premixing stream line and a second fuel flow of the second fuel has a second premixing stream line, wherein each of the premixing stream lines begins with the beginning of the premixing with the air flow and ends at the location where the fuel enters the reaction zone and the length of the second premixing stream line is longer than the length of the first premixing stream line.
    Type: Grant
    Filed: July 4, 2016
    Date of Patent: March 9, 2021
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventors: Ghenadie Bulat, Jonathan May
  • Patent number: 10883718
    Abstract: An air intake swirler for a turbomachine injection system includes an upstream wall and a downstream wall, both of revolution about an axis of the air intake swirler, and fins distributed about the axis and connecting the upstream wall to the downstream wall so as to delimit, between the upstream wall and the downstream wall, air inlet channels each having an inlet and an outlet. The swirler includes two aerodynamic deflectors that respectively extend the downstream walls radially outward and that have a concavity oriented upstream. The aerodynamic deflectors extend radially facing the respective inlets of the air inlet channels and thus make it possible to limit the loss of pressure of the air supplied to the air inlet channels.
    Type: Grant
    Filed: April 28, 2017
    Date of Patent: January 5, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Romain Nicolas Lunel, Guillaume Aurelien Godel, Haris Musaefendic, Christophe Pieussergues, Francois Pierre Georges Maurice Ribassin
  • Patent number: 10823418
    Abstract: A combustor for a turbine engine includes an inner combustion liner and an outer combustion liner together defining at least in part an interior. The interior includes a combustion chamber and a main portion. The combustor also includes an inlet combustion liner at least partially defining the combustion chamber of the interior and including an inlet assembly. The inlet assembly includes at least two cavity air tubes arranged along the axial direction, each cavity air tube extending between an inlet and an outlet, the outlet of each cavity air tube in airflow communication with the combustion chamber for providing the combustion chamber with a flow of air.
    Type: Grant
    Filed: March 2, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Joseph Zelina, Sarah Marie Monahan, Michael Anthony Benjamin, Venkat Eswarlu Tangirala, Sibtosh Pal, William Thomas Ross
  • Patent number: 10823415
    Abstract: A deflector panel for a combustor of a gas turbine engine includes an outer radial edge, an inner radial edge, and two circumferential edges extending between the outer radial edge and the inner radial edge. Each circumferential edge including a panel scallop at least partially defining a deflector opening receptive of a fuel nozzle of the combustor. A combustor of a gas turbine engine includes a combustor shell at least partially defining a combustion zone therein, and a deflector assembly operably connected to the combustor shell. The deflector assembly includes a plurality of circumferentially abutted deflector panels. Each deflector panel includes an outer radial edge, an inner radial edge, and two circumferential edges extending between the outer radial edge and the inner radial edge. Each circumferential edge includes a panel scallop at least partially defining a deflector opening. A fuel nozzle extends through the deflector opening.
    Type: Grant
    Filed: June 1, 2018
    Date of Patent: November 3, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Kristy Rose Riley, John R. Battye, Joanne V. Rampersad, San Quach
  • Patent number: 10823061
    Abstract: An annular air inlet duct circumscribing an axis of rotation of a rotatable member of a machine comprising a forward end and an aft end is described. The air inlet duct includes an unheated wall and a heated wall adjacent to a heat source. The heated wall includes a plurality of axially-spaced wall panels forming a cavity between each of a pair of adjacent wall panels of the plurality of axially-spaced wall panels.
    Type: Grant
    Filed: July 15, 2016
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventor: Mark Gregory Wotzak
  • Patent number: 10808935
    Abstract: A combustion chamber assembly group includes a nozzle providing a fuel-air mixture at a nozzle exit opening. An end of a fuel guiding channel is bordered at the nozzle exit opening by a flow-off edge located radially outside, and an air guiding element of an air guiding channel of the nozzle located radially outside projects with respect to this flow-off edge in the axial direction with respect to a nozzle longitudinal axis such that: a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and tangentially to the axially projecting air guiding element, and/or a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and a point of the air guiding element that projects maximally beyond the flow-off edge in the axial direction is ?50┬░.
    Type: Grant
    Filed: September 25, 2018
    Date of Patent: October 20, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Max Staufer, Miklos Gerendas, Ruud Eggels
  • Patent number: 10801726
    Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a deflector wall, an annular axial wall, and an annular shroud. The deflector wall is extended at least partially along a radial direction and a circumferential direction relative to an axial centerline and adjacent to a combustion chamber. A fuel nozzle opening is defined through the deflector wall, and a nozzle centerline is extended through the fuel nozzle opening along a lengthwise direction. The annular axial wall is coupled to the deflector wall and extended through the fuel nozzle opening. The axial wall is defined around the nozzle centerline. The annular shroud is defined around the nozzle centerline and extended co-directional to the axial wall. The axial wall and the annular shroud are each coupled to a radial wall defined upstream of the deflector wall. The annular shroud, the axial wall, and the radial wall together define a cooling plenum therebetween.
    Type: Grant
    Filed: September 21, 2017
    Date of Patent: October 13, 2020
    Assignee: General Electric Company
    Inventors: Eric John Stevens, Allen Michael Danis, Ravi Chandra, Jayanth Sekar, Perumallu Vukanti
  • Patent number: 10787927
    Abstract: A turbomachine, with a flow-conducting assembly, which on a first side serves for the flow-conduction of a first medium, which has a first temperature, and which on a second side is coolable with a second medium, which has a second temperature, that is lower than the first temperature, and with an impingement grille including openings which extend spaced from the flow-conducting assembly, wherein via the openings of the impingement grille the second medium is directable onto the second side of the flow-conducting assembly. In the region of at least some of the openings of the impingement grille, flow-conducting elements for the second medium are formed, which emanating from the impingement grille extend in the direction of the second side of the flow-conducting assembly to be cooled.
    Type: Grant
    Filed: September 20, 2018
    Date of Patent: September 29, 2020
    Assignee: MAN Energy Solutions SE
    Inventor: Robert Krewinkel
  • Patent number: 10767864
    Abstract: A gas turbine engine may include a combustor having an inner wall and an outer wall defining a combustion chamber there between. The inner wall and the outer wall may each have at least one opening into the combustion chamber. The gas turbine engine may also include at least one mobile conduit through which a cooling fluid may flow. The mobile conduit may pass through the combustion chamber from the at least one opening in the outer wall to the at least one opening in the inner wall. The gas turbine engine may further include a first joint and a second joint fluidly connecting the mobile conduit to the at least one opening in the inner wall and the at least one opening in the outer wall, respectively. The first joint and the second joint may enable multiple degrees of freedom of the mobile conduit within the combustion chamber.
    Type: Grant
    Filed: June 17, 2016
    Date of Patent: September 8, 2020
    Assignees: ROLLS-ROYCE PLC, ROLLS-ROYCE CORPORATION
    Inventors: Joseph Clegg, Robert A. Hicks
  • Patent number: 10760792
    Abstract: A combustor assembly for a gas turbine engine includes a dome and a deflector positioned adjacent to the dome. One or both of the dome and the deflector define an opening, a component axis extending through the opening, and a radial direction relative to the component axis. The combustor assembly also includes a retainer having an outer member contacting the dome, the deflector or both. The outer member of the retainer defines at least in part a retainer cavity inward of the outer member along the radial direction. The dome, the deflector, or both define a plurality of cooling holes for providing a cooling airflow from the retainer cavity to the opening.
    Type: Grant
    Filed: February 2, 2017
    Date of Patent: September 1, 2020
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, James Russo, Duane Douglas Thomsen, Daniel Kirtley
  • Patent number: 10731860
    Abstract: An air shroud for a nozzle includes an air shroud body defining an inlet and an outlet in fluid communication with one another to allow an outer airflow to issue therefrom. The air shroud also includes an air wipe disposed outboard of the air shroud body including a web defining a plurality of air wipe outlets in fluid communication with a downstream surface of the air shroud body such that air can flow through the air wipe outlets and wipe the downstream surface of the air shroud body. The air wipe can be integral with the air shroud body.
    Type: Grant
    Filed: February 5, 2015
    Date of Patent: August 4, 2020
    Assignee: DELAVAN, INC.
    Inventors: Matthew R. Donovan, David H. Bretz, Philip E. Buelow
  • Patent number: 10724739
    Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an annular bulkhead adjacent to a diffuser cavity; a deflector downstream of the bulkhead and adjacent to a combustion chamber; a bulkhead support coupled to an upstream side of the deflector; a first walled enclosure coupled to the bulkhead support; and a second walled enclosure coupled to the first walled enclosure. The deflector and the bulkhead support together define a bulkhead conduit therethrough to the combustion chamber. The first walled enclosure defines a first cavity and a hot side orifice. The hot side orifice is adjacent to and in fluid communication with the bulkhead conduit. The second walled enclosure defines a second cavity and a second opening adjacent to a diffuser cavity.
    Type: Grant
    Filed: March 24, 2017
    Date of Patent: July 28, 2020
    Assignee: General Electric Company
    Inventors: Kwanwoo Kim, Owen Graham, Clayton Stuart Cooper
  • Patent number: 10690347
    Abstract: Combustor dome assemblies having combustor deflectors are provided. For example, a combustor dome assembly comprises a combustor dome defining an opening; a ceramic matrix composite (CMC) deflector positioned adjacent the combustor dome on an aft side of the assembly; a fuel-air mixer defining a groove about an outer perimeter thereof; and a seal plate including a key. The CMC deflector includes a cup extending forward through the opening in the combustor dome that defines one or more bayonets and a slot. The bayonets are received in the fuel-air mixer groove, and the seal plate key is received in the CMC deflector slot. In another embodiment, where the seal plate may be omitted, a spring is positioned between the fuel-air mixer and the CMC deflector to hold the CMC deflector in place with respect to the combustor dome. Methods of assembling combustor dome assemblies having CMC deflectors also are provided.
    Type: Grant
    Filed: February 1, 2017
    Date of Patent: June 23, 2020
    Assignee: General Electric Company
    Inventors: Brandon ALlanson Reynolds, Matthew Mark Weaver, Daniel Patrick Kerns
  • Patent number: 10632430
    Abstract: A vane swirl mixer for exhaust aftertreatment includes: a vane swirl mixer inlet; a vane swirl mixer outlet; a first flow device including: a Venturi body; a plurality of upstream vanes positioned within the Venturi body; a plurality of upstream vane apertures interspaced between the plurality of upstream vanes; a plurality of downstream vanes positioned within the Venturi body; and a plurality of downstream vane apertures interspaced between the plurality of downstream vanes. At least one of the upstream vane hub and the downstream vane hub is radially offset from a Venturi center axis, thereby causing individual ones of the plurality of vanes coupled to the radially offset vane hub to differ in their geometry.
    Type: Grant
    Filed: June 14, 2019
    Date of Patent: April 28, 2020
    Assignee: Cummins Emission Solutions Inc.
    Inventors: Z. Gerald Liu, Apoorv Kalyankar, Achuth Munnannur, Niklas M. Schmidt, David Lee Dunnuck
  • Patent number: 10527288
    Abstract: The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine and includes a plurality of cooling elements integrally formed with the annular ring and projecting therefrom into impingement airflow. The cooling elements increase the effective surface area of the inner surface of the annular ring, which is adapted to be cooled by the impingement airflow.
    Type: Grant
    Filed: June 17, 2016
    Date of Patent: January 7, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza Stastny, Robert Sze
  • Patent number: 10473332
    Abstract: A combustor assembly for a gas turbine engine includes an inner liner, an outer liner, and a combustor dome. The inner liner, outer liner, and combustor dome together define at least in part a combustion chamber having an annulus height. Additionally, the combustor assembly includes a fuel-air injector hardware assembly positioned at least partially within an opening of the combustor dome. The fuel-air injector hardware assembly includes a heat shield located at least partially within the combustion chamber, the heat shield defining an outer diameter. A ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield may be at least about 1.5:1.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: November 12, 2019
    Assignee: General Electric Company
    Inventors: David Andrew Hannwacker, Stephen John Howell, John Carl Jacobson, Joseph Douglas Monty
  • Patent number: 10458654
    Abstract: The invention relates to an annular combustion chamber in a turbine engine, comprising two coaxial walls of revolution, one an internal wall (12) and the other an external wall (14), between which emerge fuel injectors (19) each engaged in centring means (36) which are moveable in the radial direction in support means (38), the chamber also comprising means (50, 68) of axial retention in the upstream direction of the centring means. According to the invention, the means of axial retention in the upstream direction are removably fixed to at least one of the internal (12) or external (14) walls of revolution.
    Type: Grant
    Filed: December 17, 2014
    Date of Patent: October 29, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Brice Le Pannerer, Laurent Bernard Cameriano, Pierre-Fran├žois Simon Paul Pireyre
  • Patent number: 10436448
    Abstract: An injector includes a feed arm extending from an inlet fitting to a nozzle body opposite the inlet fitting. The nozzle body includes a spray outlet in fluid communication with the inlet fitting for issuing a spray of fluid supplied at the inlet fitting. The inlet fitting of the feed arm includes a receptacle therein for receiving a fluid supply manifold inside the inlet fitting of the feed arm.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: October 8, 2019
    Assignee: Delavan Inc.
    Inventors: Jason A. Ryon, Brett A. Pfeffer, Mark A. Caples, Daniel E. Bleeker
  • Patent number: 10385809
    Abstract: A nozzle includes a nozzle body defining a longitudinal axis. The nozzle body has an air passage, a fuel circuit radially outboard from the air passage with respect to the longitudinal axis, and a cooling circuit. The fuel circuit extends from a fuel circuit inlet to a fuel circuit annular outlet. The fuel circuit is defined between a fuel circuit inner wall and a fuel circuit outer wall. At least a portion of the fuel circuit outer wall is radially outboard from the fuel circuit inner wall with respect to the longitudinal axis. A cooling circuit is defined within at least one of the fuel circuit inner wall or the fuel circuit outer wall. The cooling circuit extends from an axial position proximate the fuel circuit inlet to an axial position proximate the fuel circuit outlet.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: August 20, 2019
    Assignee: Delavan Inc.
    Inventor: Lev A. Prociw
  • Patent number: 10371382
    Abstract: Combustor assemblies having heat shields and features for attaching the heat shields are provided. For example, a combustor assembly includes a combustor dome defining an aperture, and a heat shield defining an opening and including a cup extending about the opening that extends toward the aperture of the combustor dome. The combustor assembly also includes a collar comprising a first piece and a second piece that each surround a portion of the heat shield cup. The collar may include a first arm, a second arm, and a body connecting the first and second arms such that the collar defines a recess between the first and second arms. The combustor assembly also may include an attachment piece with a flange that is positioned in the recess with a heat shield flange; the attachment piece attaches to the combustor dome to couple the heat shield and the combustor dome.
    Type: Grant
    Filed: September 30, 2016
    Date of Patent: August 6, 2019
    Assignee: General Electric Company
    Inventor: Donald Michael Corsmeier
  • Patent number: 10317083
    Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall. The lip generally increases in diameter as it extends downstream.
    Type: Grant
    Filed: October 3, 2014
    Date of Patent: June 11, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Yen-Wen Wang, Nigel Davenport, Eduardo Hawie
  • Patent number: 10253985
    Abstract: The invention concerns a sequential liner for a gas turbine combustor, having a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall. The sequential liner outer wall includes a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face. The invention also concerns a method of cooling using the sequential liner and a method of retrofitting a gas turbine.
    Type: Grant
    Filed: February 22, 2016
    Date of Patent: April 9, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Michael Thomas Maurer, Jeffrey De Jonge, Felix Baumgartner, Patrik Meng
  • Patent number: 10215419
    Abstract: A floating collar assembly for a gas turbine engine combustor includes a ferrule having a peripheral wall and a recessed surface bounded by the peripheral wall, the recessed surface of the ferrule including a particulate collecting groove adjacent the peripheral wall, and a cap secured to the peripheral wall of the ferrule. The recessed surface of the ferrule, an interior surface of the cap and the peripheral wall of the ferrule define a cavity. A floating collar is disposed within the cavity and includes a peripheral flange inwardly spaced a distance from the peripheral wall of the ferrule.
    Type: Grant
    Filed: July 8, 2016
    Date of Patent: February 26, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jakub Strzepek, Sri Sreekanth, Kian McCaldon, Honza Stastny, Dan Titirica
  • Patent number: 10208956
    Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: February 19, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Parham Zabeti
  • Patent number: 10209146
    Abstract: An apparatus and a process for experimentally determining a heat transfer coefficient of a surface which includes a duct having an outer passage for water flow and an inner passage for air flow, the two passages separated by a thin wall membrane such that the water flow establishes a datum temperature on the thin wall membrane, and where air flowing through the second passage and over the thin wall membrane surface which can include heat transfer enhancements features will be heated by the features, and where the heat transfer coefficient can be determined from the surface temperature of the thin wall membrane and the change in temperature of the air flow. The duct with the thin wall membrane and heat transfer enhancement features is produced using a plastic or metallic additive manufacture process for low cost and quit turnaround time.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: February 19, 2019
    Assignee: FLORIDA TURBINE TECHNOLOGIES, INC
    Inventors: Christopher K Rawlings, Phillip M Redman, Bryan C Bernier, James P Downs
  • Patent number: 10202861
    Abstract: A sealing arrangement for sealing a gap between two components which bear flat against one another on the gap side and which can be assembled only by transverse movement, wherein each component has a step on the gap side to form an overlapping stop and the steps are curved along their edges. One of the two components has a first groove which extends in a manner analogous to the curved edge and which is arranged in the set-back partial surface of the gap side of the component in question. The other of the two components has a recess located opposite the groove, and a modular sealing element comprising a sealing strip and a spiral strip is provided, which bears with its first sealing section, protruding from the groove, against a side face of the recess.
    Type: Grant
    Filed: January 19, 2015
    Date of Patent: February 12, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Berthold Vogel, Karl Klein, Stephan Sonnen
  • Patent number: 10197282
    Abstract: A multistaged lean prevaporizing premixing fuel injector apparatus is provided. The fuel injector may be utilized with a turbogenerator. Preheated combustion air from the turbogenerator's recuperator may be utilized by the fuel injector to prevaporize liquid fuel. The injector may provide for premixing of multiple fuel streams and include multiple stages with a flow distributor plate separating adjacent stages. The injector may include multiple stages, with a pilot tube located in a final stage splitting the fuel stream into a premixed pilot stream and a premixed final fuel and air mixture stream.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: February 5, 2019
    Assignee: Capstone Turbine Corporation
    Inventors: Mark G. Mitchell, Junhua Chen
  • Patent number: 10139108
    Abstract: A combustor basket assembly for a gas turbine engine that includes a combustor basket having a basket liner including an input end and an output end. An integrated exit cone and splash plate member is affixed to the output end of the basket liner and includes a base portion, an exit cone portion and a splash plate portion. The base portion includes an annular cooling channel that receives a cooling air flow and the exit cone portion and the splash plate portion each include an array of cooling feed holes in fluid communication with the cooling channel. The spacing between the feed holes and the size of the feed holes can be optimized to provide more cooling for hotter regions.
    Type: Grant
    Filed: June 8, 2015
    Date of Patent: November 27, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Richard L. Thackway, Charalambos Polyzopoulos, Jr., James M. Hurney
  • Patent number: 10101031
    Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.
    Type: Grant
    Filed: June 30, 2014
    Date of Patent: October 16, 2018
    Assignee: United Technologies Corporation
    Inventors: Alexander W. Williams, Seth A. Max, Christopher B. Lyons
  • Patent number: 10060622
    Abstract: The present invention relates to an axial swirler, in particular for premixing of oxidizer and fuel in gas turbines. The axial swirler for a gas turbine burner includes a plurality of swirl vanes with a streamline cross-section being arranged around a swirler axis and extending in radial direction between an inner radius Rmin and an outer radius Rmax. Each swirl vane has a leading edge, a trailing edge, and a suction side and a pressure side extending each between the leading and trailing edges. A discharge flow angle ? between a tangent to the swirl vane camber line at its trailing edge and the swirler axis is first function of radial distance R from the swirler axis. A position of maximum camber of the swirl vane is second function of radial distance R from the swirler axis. At least one swirl vane of the first and second functions include each a respective local maximum and local minimum values along said radial distance from Rmin to Rmax. The invention also relates to a burner with such a swirler.
    Type: Grant
    Filed: July 8, 2015
    Date of Patent: August 28, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Fernando Biagioli, Madhavan Narasimhan Poyyapakkam, Stefan Wysocki
  • Patent number: 10018167
    Abstract: A combustion chamber includes an upstream end wall having an aperture and a fuel injector. An air swirler is mounted such that the air swirler is movable radially with respect to the aperture. An inner wall of the air swirler has a first portion. A fuel injector head of the fuel injector is arranged coaxially within the air swirler. An outer wall of the fuel injector head has a first portion. The inner diameter of the first portion of the air swirler is less than the outer diameter of the first portion of the fuel injector head. One of the first portions is elastically radially deformable to allow the fuel injector head to be installed and removed from the air swirler. The inner wall and the outer wall have inter-engaging radially and axially extending faces to align the fuel injector head axially and radially within the air swirler.
    Type: Grant
    Filed: November 6, 2014
    Date of Patent: July 10, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Luca Tentorio
  • Patent number: 9957897
    Abstract: A gimbal tube system for an onboard injector (OBI) includes a transfer tube having a first transfer tube end that can be mounted to an inner diameter of a stator platform and a second transfer tube end defining a transfer tube pivot connector. The system also includes a gimbal tube including a first gimbal tube end that defines a gimbal tube pivot connector that can movably mount to the transfer tube pivot connector such that the gimbal tube and the transfer tube can move relative to each other at a pivot joint defined between the transfer tube and the gimbal tube. The gimbal tube further includes a second gimbal tube end defining a nozzle that can be inserted into the OBI.
    Type: Grant
    Filed: March 19, 2015
    Date of Patent: May 1, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas E. Clark, Jeffrey Vincent Anastas
  • Patent number: 9958161
    Abstract: A gas turbine engine comprises an annular combustor chamber formed between an inner liner and an outer liner. An annular upstream zone is adapted to receive fuel and air from an annular nozzle. An annular mixing zone is located downstream of the upstream zone. The mixing zone has a reduced radial height relative a downstream combustion zone of the combustion chamber, the mixing zone defined by straight wall sections.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: May 1, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Tin Cheung John Hu
  • Patent number: 9939157
    Abstract: A fuel nozzle apparatus for a gas turbine engine includes: a first pilot fuel injector disposed on a centerline axis of the fuel nozzle which defines a direction of air flow through the fuel nozzle, the first pilot fuel injector being of a pressure atomizing type; an annular second pilot fuel injector at least partially surrounding the first pilot fuel injector, the second pilot fuel injector being of an air blast type and having a fuel outlet disposed axially downstream and radially outboard of the first pilot fuel injector; an annular venturi surrounding the first and second pilot fuel injectors, the venturi including a throat of minimum diameter; an array of inner swirl vanes extending between the first pilot fuel injector and the second pilot fuel injector; and an array of outer swirl vanes extending between the second pilot fuel injector and the venturi.
    Type: Grant
    Filed: March 10, 2015
    Date of Patent: April 10, 2018
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Duane Douglas Thomsen
  • Patent number: 9927126
    Abstract: A pilot fuel injector is provided for a fuel nozzle of a gas turbine engine. The pilot fuel injector can include an axially-elongated, inner pilot centerbody wall extending from an upstream end to a downstream end, with the axially-elongated, inner pilot centerbody wall having a diverging-converging orientation with respect to a centerline axis to define a hollow tube having an upstream diameter, a throat, and a downstream diameter such that the throat has an inner diameter that is less than both of the upstream diameter and the downstream diameter. The pilot fuel injector also includes a center air circuit positioned at the upstream end, and an annular fuel passage defining the downstream end and intersecting with the centerbody wall at a pilot fuel metering orifice. A pilot fuel film surface is downstream from the annular fuel passage.
    Type: Grant
    Filed: June 10, 2015
    Date of Patent: March 27, 2018
    Assignee: General Electric Company
    Inventors: Michael Anthony Benjamin, Alfred Albert Mancini, Rameshkumar Muthuvel Chandrasekaran
  • Patent number: 9920693
    Abstract: A fuel injector component includes a body, an elongate void and a plurality of bores. The body has a first surface and a second surface. The elongate void is enclosed by the body and is integrally formed between portions of the body defining the first surface and the second surface. The plurality of bores extends into the second surface to intersect the elongate void. A process for making a fuel injector component includes building an injector component body having a void and a plurality of ports connected to the void using an additive manufacturing process that utilizes a powdered building material, and removing residual powdered building material from void through the plurality of ports.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: March 20, 2018
    Assignee: United Technologies Corporation
    Inventor: Russell B. Hanson
  • Patent number: 9709279
    Abstract: A system includes a gas turbine engine that includes a first combustor and a second combustor. The first combustor includes a first oxidant flow path and a first perforated structure comprising a first plurality of oxidant ports, wherein the first perforated structure is disposed in the first oxidant flow path. The second combustor includes a second oxidant flow path and a second perforated structure comprising a second plurality of oxidant ports. The second perforated structure is disposed in the second oxidant flow path and the first perforated structure has at least one difference relative to the second perforated structure.
    Type: Grant
    Filed: February 27, 2014
    Date of Patent: July 18, 2017
    Assignee: General Electric Company
    Inventors: Sarah Lori Crothers, Lucas John Stoia, William Francis Carnell, Jr.
  • Patent number: 9625152
    Abstract: A heat shield for a combustor of a gas turbine engine has a heat shield adapted to be mounted to a combustor wall with a back face of the heat shield in spaced-apart facing relationship with an inner surface of the combustor wall to define an air gap. Rails extend from the back face of the heat shield across the air gap. Grooves are defined in at least one of the rails. The rail grooves are in fluid flow communication with the air gap when the heat shield is mounted to the combustor wall.
    Type: Grant
    Filed: June 3, 2014
    Date of Patent: April 18, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Papple, Robert Sze
  • Patent number: 9599022
    Abstract: A modular fuel nozzle tip for a gas turbine engine includes a body defining one or more fuel conveying passages extending therethrough, an annular cap having a radially inner shoulder surface interfacing with the peripheral end surface of the body to define a plurality of air channels extending through the head portion of the modular fuel nozzle tip. At least two fasteners fasten the annular cap to the body.
    Type: Grant
    Filed: January 30, 2013
    Date of Patent: March 21, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza Stastny, Bhawan B Patel, John Greer, Parthasarathy Sampath
  • Patent number: 9592480
    Abstract: An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection portion extending radially inward and axially from the annular disk portion. The transition end also includes a plurality of wipe passages extending through the transition end. The tip end includes a cylindrical portion with a hollow right circular cylinder shape. The premix tube inner surface is a radially outer surface including the redirection portion outer surface and the cylindrical portion outer surface.
    Type: Grant
    Filed: May 13, 2013
    Date of Patent: March 14, 2017
    Assignee: Solar Turbines Incorporated
    Inventors: Donald James Cramb, James Scott Piper, Sean Kelly Spivey, Michael John Ramotowski, Matthew Mayer
  • Patent number: 9506352
    Abstract: The present invention relates to a turbine blade of a gas turbine with an airfoil arranged on a blade root and having at least one cooling air duct running in the longitudinal direction of the turbine blade, arranged inside the turbine blade and extending through the blade root, characterized in that at least one swirl-generating element is arranged in the transitional area between blade root and airfoil in the cooling air duct, with the swirl-generating element including an outer ring and several swirl-generating stator vanes arranged thereon, which are connected to a centric area, as well as to a method for its manufacture.
    Type: Grant
    Filed: September 3, 2013
    Date of Patent: November 29, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Knut Lehmann, Tijana Filipova
  • Patent number: 9500371
    Abstract: A device for injecting air and fuel into a combustion chamber of a turbine engine, the device including a fuel injector, at least one first element mounted on the fuel injector, and at least one second element mounted on an end wall of the combustion chamber. The first element includes a radial rim that is movable in a radial groove of the second element, which groove is defined by a sheath and by a closure ring welded to an inside of the sheath. The closure ring includes a radial wall and a cylindrical rim extending from the radially outer periphery of the radial wall towards a radial wall of the sheath and bearing via its corresponding free end against the radial wall of the sheath.
    Type: Grant
    Filed: February 8, 2013
    Date of Patent: November 22, 2016
    Assignee: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Frederic Marius Mathieu, Gilles Ulryck
  • Patent number: 9476429
    Abstract: A feed diffuser is disclosed. The diffuser may comprise a base disposed orthogonal to a flow, a body extending from the base toward the flow, and an apex provided at a termination of the body in a direction toward the flow. The body may decrease in cross-sectional area from the base to the apex.
    Type: Grant
    Filed: December 19, 2012
    Date of Patent: October 25, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Brian Beach
  • Patent number: 9447974
    Abstract: The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirl assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.
    Type: Grant
    Filed: September 13, 2012
    Date of Patent: September 20, 2016
    Assignee: United Technologies Corporation
    Inventors: Seth A. Max, Jonathan M. Jause
  • Patent number: 9447976
    Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas gallery and a gas passage. The gas gallery is an annular passage configured to circumferentially distribute gas fuel. The gas passage includes an inlet and an outlet. The inlet is distal to the gas gallery and includes an inlet area with a circular shape. The outlet adjoins the gas gallery and includes an outlet area including an annular sector shape. The gas passage is configured to diffuse the gas fuel and discharge the gas fuel from the outlet and into the gas gallery.
    Type: Grant
    Filed: January 10, 2014
    Date of Patent: September 20, 2016
    Assignee: Solar Turbines Incorporated
    Inventors: Christopher Zdzislaw Twardochleb, Rasoul Z. Paydar
  • Patent number: 9429042
    Abstract: An acoustic damping device is provided which includes at least one opening for a sealing gas to deflect a grazing gas flow away from the mouth of an acoustic damper.
    Type: Grant
    Filed: February 26, 2015
    Date of Patent: August 30, 2016
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Franklin Marie Genin, Devis Tonon, Mirko Ruben Bothien, Douglas Anthony Pennell
  • Patent number: 9360218
    Abstract: A fuel injection device is provided. The device includes a pilot injector opening out into a venturi and an annular row of multipoint injection orifices opening out axially in a downstream direction and radially outside the venturi, the venturi being connected at its downstream end to a separation wall. The outer peripheral edge of the separation wall has a diameter greater than the diameter of the annular row of injection orifices, whereby the separation wall forms a thermal protection screen for these orifices against heat radiation coming from the chamber.
    Type: Grant
    Filed: September 27, 2013
    Date of Patent: June 7, 2016
    Assignee: SNECMA
    Inventors: Matthieu Francois Rullaud, Galadriel Dancie, Romain Nicolas Lunel, Thomas Olivier Marie Noel
  • Patent number: 9347378
    Abstract: A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet.
    Type: Grant
    Filed: May 13, 2013
    Date of Patent: May 24, 2016
    Assignee: Solar Turbines Incorporated
    Inventors: Donald James Cramb, James Scott Piper, Sean Kelly Spivey, Michael John Ramotowski, Matthew Mayer
  • Patent number: 9322554
    Abstract: A combustor for a turbine engine includes a first liner defined about an axis with a first row of first combustion air holes, one of the first combustion air holes is defined along each of a multiple of fuel injector zero pitch lines. A second liner defined about the axis with a second row of second combustion air holes, each of the second combustion air holes circumferentially offset relative to each of the multiple of fuel injector zero pitch lines.
    Type: Grant
    Filed: July 29, 2011
    Date of Patent: April 26, 2016
    Assignee: United Technologies Corporation
    Inventors: Won-Wook Kim, James B. Hoke, Timothy S. Snyder