Porous Patents (Class 60/754)
  • Patent number: 10330204
    Abstract: A burner seal of a gas turbine with a substantially tubular base body, which has a ring-shaped inlet lip on the inflow side and a funnel at its outflow side, wherein an inner diameter of the inflow side is embodied to be larger than an inner diameter of a sealing surface that is arranged axially in front of the funnel, wherein cooling channels are formed in the base body distributed about the circumference, wherein the cooling channels are formed respectively in the base body in the area of the sealing surface and of the funnel, and respectively open into an end area of the funnel in an exit hole.
    Type: Grant
    Filed: November 10, 2017
    Date of Patent: June 25, 2019
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • Patent number: 10260748
    Abstract: A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.
    Type: Grant
    Filed: December 21, 2012
    Date of Patent: April 16, 2019
    Assignee: United Technologies Corporation
    Inventors: Timothy S. Snyder, Randal G. McKinney, James B. Hoke
  • Patent number: 10215410
    Abstract: A combustor for a turbine engine is provided that includes a combustor wall. The combustor wall includes a shell and heat shield, which is attached to the shell. One or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield. The apertures in the heat shield include a first aperture and a second aperture. An angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.
    Type: Grant
    Filed: November 4, 2014
    Date of Patent: February 26, 2019
    Assignee: United Technologies Corporation
    Inventors: Dennis M. Moura, Monica Pacheco-Tougas, Jonathan J. Eastwood, Lee E. Bouldin
  • Patent number: 9970660
    Abstract: There is disclosed a liner element in the form of an impingement/effusion tile for a gas turbine combustor having a structural wall. The liner element has a unitary construction defining a cooling side and combustion side, and a plurality of effusion holes extending between a cooling side surface of the element and a combustion side surface of the element. The liner element is configured to be affixed to the structural wall of a combustor with its cooling side surface spaced from the structural wall to define a chamber between the cooling side surface and the structural wall, and the liner element further includes integrally formed and internally threaded protuberances on its cooling side, the protuberances being arranged to engage the structural wall.
    Type: Grant
    Filed: July 1, 2015
    Date of Patent: May 15, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Paul I Chandler, Anthony Pidcock
  • Patent number: 9897320
    Abstract: A gas turbine engine combustor is provided. An inner liner has an upstream end and a downstream end and extends in an axial direction between the upstream and downstream ends. A dual wall outer liner has a hot wall, a cold wall at least partially surrounding the hot wall, an upstream end, and a downstream end. The outer liner extends in the axial direction between the upstream and downstream ends. A dome assembly is coupled between the upstream ends of the inner and outer liners to define a combustion chamber between the inner liner and the hot wall of the outer liner. Effusion cooling holes are disposed in the hot wall, including a first row disposed at a tangential angle of between about 70° and about 90° and a second row disposed at a tangential angle of between about 0° and about 20°.
    Type: Grant
    Filed: July 30, 2009
    Date of Patent: February 20, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Thomas J. Bronson, Frank Joseph Zupanc, Paul Yankowich, Nagaraja Rudrapatna
  • Patent number: 9810430
    Abstract: A conjoined grommet assembly for a combustor wall assembly of a gas turbine engine has a first grommet defining at least in-part a first dilution hole, and a second grommet defining at least in-part a second dilution hole. The first and second dilution holes are spaced closely together such that the first grommet is in contact with the second grommet.
    Type: Grant
    Filed: December 23, 2014
    Date of Patent: November 7, 2017
    Assignee: United Technologies Corporation
    Inventors: Jonathan P. Sandoval, Randolph J. Smith
  • Patent number: 9506652
    Abstract: A combustion chamber, for example for a turbine engine, presenting an inner annular wall, an outer annular wall, and a pierced annular chamber end wall extending around an axis, the chamber end wall including at least one opening receiving a fuel injector, the opening being substantially centered on a circular line defining a first chamber end wall portion extending radially between the circular line and the inner annular wall, and a second chamber end wall portion extending radially between the circular line and the outer annular wall. First and second channels are inclined relative to a normal vector normal to the chamber end wall while extending tangentially, the first channels arranged to provide a flow of air in a first rotary direction, the second channels arranged to provide a flow of air in a second rotary direction opposite to the first rotary direction.
    Type: Grant
    Filed: January 11, 2011
    Date of Patent: November 29, 2016
    Assignee: TURBOMECA
    Inventors: Bernard Joseph Jean-Pierre Carrere, Jean-Marc Dubourdieu-Rayrot, Lorenzo Huacan Hernandez, Robert Serrot-Gracie
  • Patent number: 9416728
    Abstract: A combustor apparatus is provided, comprising a mixing arrangement for mixing a carbonaceous fuel with enriched oxygen and a working fluid to form a fuel mixture. A combustion chamber is at least partially defined by a transpiration member. The transpiration member is at least partially surrounded by a pressure containment member. The combustion chamber has opposed inlet and outlet portions. The inlet portion of the combustion chamber is configured to receive the fuel mixture for the fuel mixture to be combusted at a combustion temperature. The combustion chamber is further configured to direct the resulting combustion product toward the outlet portion. The transpiration member directs a transpiration substance therethrough toward the combustion chamber for buffering interaction between the combustion product and the transpiration member. Associated systems, apparatuses, and methods are also provided.
    Type: Grant
    Filed: February 26, 2010
    Date of Patent: August 16, 2016
    Assignees: 8 Rivers Capital, LLC, Palmer Labs, LLC
    Inventors: Miles R. Palmer, Rodney John Allam, Glenn William Brown, Jr.
  • Patent number: 9377198
    Abstract: A heat shield includes a panel having a forward face and an aft face, a circumferential outer side and a circumferential inner side such that the panel subtends a predetermined arc, and a first radially extending side and a second radially extending side each extending from the circumferential outer side to the circumferential inner side. The panel defines an opening extending between the forward face and the aft face, a lip projecting from the forward face and extending around the opening, a rail projecting from the forward face and extending around the lip to define a cavity region between the lip and the rail, and a plurality of holes in the cavity region. Each of the plurality of holes extends from the forward face to the aft face. A region of the panel extending from the lip to the circumferential outer side is free of any aft-projecting features.
    Type: Grant
    Filed: February 17, 2012
    Date of Patent: June 28, 2016
    Assignee: United Technologies Corporation
    Inventors: Jonathan Jeffery Eastwood, Joey Wong, Robert M. Sonntag, Albert K. Cheung, Timothy S. Snyder
  • Patent number: 9341118
    Abstract: A gas turbine engine component is disclosed having a construction that permits a working fluid to flow from one side of the component to the other. In one embodiment the construction includes multiple layers, and in one particular embodiment the construction includes three layers. One or more layers can have different properties. Additionally, one or more layers of the construction can include a cellular structure. In one embodiment the component is a gas turbine engine combustor liner.
    Type: Grant
    Filed: November 22, 2010
    Date of Patent: May 17, 2016
    Assignee: ROLLS-ROYCE CORPORATION
    Inventors: Philip M. Bastnagel, Edward Claude Rice
  • Patent number: 9303872
    Abstract: A fuel injector is provided and includes a member defining a flowpath through which a first fluid flows, the flowpath having a cross-section with transverse elongate and short axes, a head defining a plenum storing a supply of a second fluid and a system fluidly coupled to the flowpath and the plenum to inject the second fluid from the plenum and into the flowpath at first and second locations along the elongate axis. The injected second fluid is formed into jets at the first and second locations, the first fluid entrains the jets such that the injected second fluid flows through the flowpath and mixes with the first fluid, and the short axis has a sufficient dimension such that the jets remain spaced from a sidewall of the member.
    Type: Grant
    Filed: September 15, 2011
    Date of Patent: April 5, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Mark Allan Hadley, Jun Cai, Lucas John Stoia, Geoffrey David Myers, Jayaprakash Natarajan
  • Patent number: 9249977
    Abstract: A combustor includes a combustion chamber and an acoustic liner, wherein through-holes through are formed in a wall of the combustion chamber, a plurality of rows of the through-holes is arranged in a lengthwise direction of the combustor, the through-holes of a first through-hole row are shifted with respect to the through-holes of a second through-hole row so that centers of the through-holes of the first and second through-hole rows adjacent each other are staggered in the circumferential direction, cooling grooves are formed so as to avoid the through-holes inside that is sandwiched between the outer peripheral surface and the inner peripheral surface of the combustion chamber, and the cooling grooves include transverse cooling grooves extending in the circumferential direction between rows of the through-holes, and longitudinal cooling grooves extending in the lengthwise direction between the through-holes and connecting the transverse cooling grooves adjacent to each other.
    Type: Grant
    Filed: November 21, 2012
    Date of Patent: February 2, 2016
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Yuichiro Kimura, Satoshi Takiguchi, Keisuke Matsuyama, Satoshi Mizukami, Shinji Akamatsu, Kenji Sato, Hikaru Katano, Shigemi Mandai
  • Patent number: 9174309
    Abstract: A turbine component and a process of fabricating a component are disclosed. The process includes excavating a base metal of the component to form a fill region and filling the fill region with a filler metal. The filler metal has a filler metal elongation that is at least 25% greater than a base metal elongation of the base metal. The filler includes, by weight, between about 4% and about 7% iron, between about 14% and about 17% chromium, between about 15% and about 17% molybdenum, between about 3% and about 5% tungsten, up to about 0.02% carbon, up to about 1% manganese, up to about 2.5% cobalt, and a balance of nickel and/or the filler metal elongation is greater than about 35% in/in per two inches.
    Type: Grant
    Filed: July 24, 2012
    Date of Patent: November 3, 2015
    Assignee: General Electric Company
    Inventors: Eric Eicher McConnell, Stephen Gerard Pope, Bill Damon Johnston, John Gregory Obeirne
  • Patent number: 9038395
    Abstract: A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defining an air admission hole for directing a first jet of pressurized air into the combustion chamber, and the air admission hole may have a non-circular shape. The combustor further includes an insert positioned within the air admission hole to guide the first jet through the air admission hole and into the combustion chamber.
    Type: Grant
    Filed: March 29, 2012
    Date of Patent: May 26, 2015
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Nagaraja S. Rudrapatna, Philip Smalley, Lowell Frye, William Landram
  • Publication number: 20150128602
    Abstract: The present invention relates to a combustion chamber heat-shielding element of a gas-turbine, having a bolt for mounting the combustion chamber heat-shielding element on a combustion chamber wall or a combustion chamber head, where the combustion chamber heat-shielding element is designed substantially plate-like and where on one side at least one bolt, which is designed as a separate component, is anchored on it by means of a bonded connection.
    Type: Application
    Filed: November 12, 2014
    Publication date: May 14, 2015
    Inventor: Carsten CLEMEN
  • Publication number: 20150121885
    Abstract: There is provided a gas turbine combustor that achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity. A gas turbine combustor structure includes a plurality of circularity recesses 20 formed on a side of an annular passage 11 on a partial area of a combustion liner 8 that requires cooling. The circularity recesses 20 each have a rectangular surface 25 forming a convex at a right angle with respect to a flowing direction of combustion air 2. The circularity recesses 20 is a rectangular triangle having an oblique surface 26 facing upstream of the flowing direction of the combustion air 2.
    Type: Application
    Filed: November 3, 2014
    Publication date: May 7, 2015
    Inventors: Osami YOKOTA, Masataka HIDAKA, Shohei NUMATA, Tetsuma TATSUMI
  • Patent number: 9010123
    Abstract: A combustor for a turbine engine is provided. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween, the combustion chamber configured to receive an air-fuel mixture for combustion therein; and an insert including a body portion extending through the first liner, a shoulder circumscribing the body portion and abutting the first hot side, and an inlet portion coupled to the body portion and abutting the first cold side such that the inlet portion and the shoulder capture the second liner therebetween to retain the insert.
    Type: Grant
    Filed: July 26, 2010
    Date of Patent: April 21, 2015
    Assignee: Honeywell International Inc.
    Inventors: Nagaraja S. Rudrapatna, Daniel Ludwig, Art Payne, Philip Smalley, Richard Bishop
  • Patent number: 9010127
    Abstract: A transition piece aft frame assembly is provided, and includes a transition piece aft frame and a heat shield. The transition piece aft frame has an aft face. At least a portion of the aft face is exposed to an exhaust gas stream. The heat shield is connected to the transition piece aft frame. The heat shield is oriented to generally deflect the exhaust gas stream away from the aft face of the transition piece aft frame.
    Type: Grant
    Filed: March 2, 2012
    Date of Patent: April 21, 2015
    Assignee: General Electric Company
    Inventors: Christopher Paul Willis, William Lawrence Byrne, David William Cihlar, Donald Timothy Lemon, Patrick Benedict Melton
  • Patent number: 9010124
    Abstract: A gas turbine engine combustion chamber includes a first wall and a second wall. The second wall is arranged within and spaced from the first wall to define a cavity between the first wall and the second wall. The first wall has a plurality of impingement apertures extending there-through and the second wall has a plurality of effusion apertures extending there-through. The impingement apertures have a first diameter, a first pitch, and a first area. The effusion apertures have a second diameter, a second pitch, and a second area. The ratio of the first diameter to the second diameter is at least 3, the ratio of the first pitch to the second pitch is at least 4 and the ratio of the first area to the second area is at least 9. This arrangement increases the cooling performance of the effusion apertures in the second wall.
    Type: Grant
    Filed: March 15, 2012
    Date of Patent: April 21, 2015
    Assignee: ROLLS-ROYCE plc
    Inventors: Paul I. Chandler, Anthony Pidcock
  • Patent number: 9010122
    Abstract: A turbine engine assembly includes a combustor and a stator vane arrangement having a plurality of stator vanes. The combustor includes a combustor wall that extends axially from a combustor bulkhead to a distal combustor wall end, which is located adjacent to the stator vane arrangement. The combustor wall includes a support shell with a plurality of impingement apertures, and a heat shield with a plurality of effusion apertures. The combustor wall end includes a plurality of circumferentially extending film cooled regions. At least one of the film cooled regions is circumferentially aligned with one of the stator vanes and includes a cooling aperture.
    Type: Grant
    Filed: July 27, 2012
    Date of Patent: April 21, 2015
    Assignee: United Technologies Corporation
    Inventors: James P. Bangerter, Dennis J. Duhamel, Robert M. Sonntag, Reza Rezvani
  • Publication number: 20150101335
    Abstract: A gas turbine combustion chamber with an inner housing and an outer housing the inner housing having an inner wall element with a first hole arrangement and a second hole arrangement is provided. The inner wall element envelopes a burner volume. The first hole arrangement has first holes arranged in a first areal density, the second hole arrangement has second holes arranged in a second areal density. The outer housing has an outer wall element with a further first hole arrangement and a further second hole arrangement. The outer wall element of the outer housing envelops the inner wall element of the inner housing so that a gap in between is formed. The further first hole arrangement has further first holes arranged in a further first areal density, the further second hole arrangement has further second holes arranged in a further second areal density.
    Type: Application
    Filed: December 5, 2012
    Publication date: April 16, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventor: Charith Jayatunga
  • Patent number: 9003800
    Abstract: A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket.
    Type: Grant
    Filed: July 2, 2012
    Date of Patent: April 14, 2015
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Shinji Akamatsu, Hiroaki Kishida, Kenji Sato, Kentaro Tokuyama, Keisuke Matsuyama, Takayoshi Takashima
  • Patent number: 8997495
    Abstract: A combustor component of a gas turbine engine includes a substrate with a cold side, a central core section and a hot side, the cold side and the hot side have a porosity different than the central core section.
    Type: Grant
    Filed: June 24, 2011
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventor: James A. Dierberger
  • Patent number: 8959886
    Abstract: A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having an inner surface, an outer surface, a region, an inlet, and an outlet. The inner surface defines an inner volume of the conduit. The region extends between the inner and outer surfaces and includes cooling fluid structure defining a plurality of cooling passageways. The inlet extends inwardly from the outer surface and provides fluid communication between the inlet and the passageways. The outlet extends from the passageways to the inner surface to provide fluid communication between the passageways and the inner volume. At least one first cooling passageway intersects with at least one second cooling passageway such that cooling fluid flowing through the first cooling passageway interacts with cooling fluid flowing through the second cooling passageway.
    Type: Grant
    Filed: July 8, 2010
    Date of Patent: February 24, 2015
    Assignees: Siemens Energy, Inc., Mikro Systems, Inc.
    Inventors: Ching-Pang Lee, Humberto A. Zuniga, Jay A. Morrison
  • Patent number: 8959919
    Abstract: A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket.
    Type: Grant
    Filed: July 2, 2012
    Date of Patent: February 24, 2015
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Shinji Akamatsu, Hiroaki Kishida, Kenji Sato, Kentaro Tokuyama, Keisuke Matsuyama, Takayoshi Takashima
  • Publication number: 20150047313
    Abstract: A design for an effectively cooling a liner of a gas turbine combustor by means of convective cooling is disclosed.
    Type: Application
    Filed: July 29, 2014
    Publication date: February 19, 2015
    Inventors: Michael Thomas MAURER, Urs BENZ, Slawomir SWIATEK, Oliver KONRADT, Maurice MALLM
  • Patent number: 8955332
    Abstract: A gas turbine combustor including a fuel nozzle for injecting mixed gas of fuel and air, a cylindrical liner for burning and reacting the mixed gas of fuel and air in a combustion chamber, a transition piece which is a flow path for leading combustion gas generated in the liner to turbine blades, and a transition piece flow sleeve for wrapping an outside surface of the transition piece, wherein a plurality of air introduction holes for introducing air into the transition piece flow sleeve are formed in regions of the transition piece flow sleeve excluding regions which are corner portions of the transition piece flow sleeve in a sectional direction thereof.
    Type: Grant
    Filed: July 8, 2014
    Date of Patent: February 17, 2015
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Takeo Saitou, Yasuyuki Watanabe, Shouhei Yoshida
  • Patent number: 8955331
    Abstract: A nut (64) is affixed to an outer surface of a transition impingement sleeve forward ring (50) that encircles, and is affixed to, a forward end (44) of a tubular transition impingement sleeve (45). The nut has a threaded hole (63) aligned with a hole (66) in the impingement sleeve forward ring. A machine screw (68) is threaded into the nut and extends through the hole (66), and has a radially inner end with a wear pad (70), and a radially outer end with a turning tool engagement element (72). The wear pad contacts an outer surface of an aft portion of a transition piece forward outer ring (52) that is surrounded by the transition impingement sleeve forward ring (50). The rotational position of the machine screw (68) sets a radial gap (76) between the transition impingement sleeve forward ring and the transition piece forward outer ring.
    Type: Grant
    Filed: October 24, 2011
    Date of Patent: February 17, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Frank Moehrle, John Pula, Jeremy Lefler, Martin Konen
  • Publication number: 20150040570
    Abstract: In one embodiment, a gas turbine engine component includes a foam based core and a composite skin member. Both the foam based core and the composite skin member can be used to structurally support the gas turbine engine component. The composite skin member can be a CMC material and is used to partially encapsulate the foam core. The gas turbine engine component can take the form of an airfoil member such as a blade or a vane, a combustor liner, etc. A first portion of the composite skin member includes a first surface extending past an edge of the component creating a step approximate an edge section. In another embodiment, composite skin members can be used to form a continuous shape for the edge section such that the foam core forms part of a gas path surface.
    Type: Application
    Filed: December 23, 2013
    Publication date: February 12, 2015
    Inventors: Richard C. Uskert, Ted J. Freeman, David J. Thomas
  • Patent number: 8950190
    Abstract: In a gas turbine combustor and a gas turbine, an air passage (54) that supplies combustion high-pressure air, a pilot nozzle (44), a main fuel nozzle (45), and a top hat nozzle (47) that supply fuel, and openings (64) that supply film air (cooling air) are provided with respect to a combustor inner cylinder (42), and contraction members (71, 72, and 73) are arranged along a circumferential direction on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder (42). The contraction members (71, 72, and 73) are provided in a predetermined area in the circumferential direction excluding penetrating portions (74, 75, and 76), which do not disturb the flow of cooling air, thereby enabling to suppress generation of carbon monoxide and the like and to suppress the occurrence of unstable combustion.
    Type: Grant
    Filed: November 5, 2010
    Date of Patent: February 10, 2015
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Keijiro Saito, Shinji Akamatsu, Kenji Sato, Shigemi Mandai
  • Publication number: 20150033749
    Abstract: In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, a flow sleeve disposed at an offset about the combustor liner to define a passage, and a barrier within the passage. The head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber. The passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor. The gas flow includes a substantially inert gas. The barrier is configured to block the portion of the oxidant flow toward the turbine end and to block the gas flow toward the head end within the passage.
    Type: Application
    Filed: July 28, 2014
    Publication date: February 5, 2015
    Inventors: Ilya Aleksandrovich Slobodyanskiy, Lewis Berkley Davis, JR., Karl Dean Minto
  • Publication number: 20150027128
    Abstract: A heat-shield element (14), for lining a combustion-chamber wall (13), the chamber wall has a first wall (17) with a hot side (18) which can be loaded with a hot medium, a cold side (19) which lies opposite the hot side (18), and a circumferential edge (24) which extends on a first (20), a second (21) and a third narrow side (22) of the first wall (17) to a first height (25) beyond the cold side (19), the circumferential edge (24) extends on a fourth narrow side (23) to a second shorter height (26), substantially at the second height (26), a second wall (27) lies opposite the cold side (19) and extends over the width of the fourth narrow side (23) from the fourth narrow side (23) and over a part of the length of the narrow sides (20, 22), which adjoin the fourth narrow side; (23), the second wall (27) has an edge (29) at the end (28) thereof which faces away from the fourth narrow side (23), which edge (29) extends to the first height (25). Furthermore, a combustion chamber and a gas turbine are disclosed.
    Type: Application
    Filed: March 12, 2013
    Publication date: January 29, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventors: Francois Benkler, Thomas Brandenburg, Olga Deiss, Thomas Grieb, Marco Link, Nicolas Savilius, Daniel Vogtmann, Jan Wilkes
  • Publication number: 20150013340
    Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.
    Type: Application
    Filed: December 27, 2013
    Publication date: January 15, 2015
    Applicants: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Donald E. Pinnick, Kenneth W. Froemming, Bruce E. Varney, James C. Loebig, Todd Taylor
  • Patent number: 8931280
    Abstract: A venturi assembly for a turbine combustor includes a first outer annular wall and a second intermediate annular wall radially spaced from each other in substantially concentric relationship. The first outer annular wall and said second intermediate annular wall shaped to define a forward, substantially V-shaped throat region, and an aft, axially extending portion. A third radially innermost annular wall is connected to the second intermediate annular wall at an aft end of said throat region. A first plurality of apertures is provided in the first outer annular wall in the substantially V-shaped throat region, and a second plurality of apertures is provided in the aft, axially extending portion of said second intermediate annular wall so that cooling air flows through the first and second pluralities of apertures to impingement cool the third radially innermost annular wall.
    Type: Grant
    Filed: April 26, 2011
    Date of Patent: January 13, 2015
    Assignee: General Electric Company
    Inventors: Karthick Kaleeswaran, Kodukulla Venkat Sridhar, James Butts, Bhaskara Rao Atchuta, Prabhu Kumar Ippadi Siddagangaiah
  • Publication number: 20150007573
    Abstract: An annular combustion chamber (1) for a gas turbine, the chamber having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) which opens into a turbine chamber (8), wherein ducts (14) which can be closed, which are oriented substantially parallel to the symmetry axis (2) of the annular combustion chamber (1), and through which final compressor air is guided into the annular combustion chamber (1) are provided in the outer shell (12) in the region of the outlet (7). Ring segments around the outer shell have projections selectively movable to at least partially block and open the ducts. A gas turbine is also disclosed.
    Type: Application
    Filed: March 15, 2013
    Publication date: January 8, 2015
    Inventors: Francois Benkler, Thomas Brandenburg, Olga Deiss, Thomas Grieb, Marco Link, Nicolas Savilius, Daniel Vogtmann, Jan Wilkes
  • Publication number: 20150000288
    Abstract: Described is an abradable component for a gas turbine engine, comprising: a base having an outboard side which receives a supply of cooling air in use and a plurality of walls on an inboard side thereof, the walls adjoining one another to provide an abradable network of open faced cells at a gas washed surface thereof; wherein at least one wall includes one or more through-holes for providing a flow of cooling air from the outboard side to the gas washed surface of the abradable network of open faced cells, when in use.
    Type: Application
    Filed: June 19, 2014
    Publication date: January 1, 2015
    Inventors: Simon Lloyd JONES, Kevin Paul SELF, Mark John SIMMS
  • Patent number: 8919127
    Abstract: A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure between the combustion liner and the flow sleeve. The structure obstructs an airflow through the air passage. The gas turbine combustor also includes a wake reducer disposed adjacent the structure. The wake reducer directs a flow into a wake region downstream of the structure.
    Type: Grant
    Filed: May 24, 2011
    Date of Patent: December 30, 2014
    Assignee: General Electric Company
    Inventors: Patrick Benedict Melton, Ronald James Chila, Abdul Rafey Khan, Carolyn Ashley Antoniono
  • Publication number: 20140373549
    Abstract: A gas turbine engine component includes a cooling hole. The component includes a first wall having an inlet, a second wall having an outlet and a metering section extending downstream from the inlet and having a substantially convex first surface and a substantially concave second surface. The component also includes a diffusing section extending from the metering section to the outlet. A gas turbine engine wall includes first and second surfaces and a cooling hole extending between an inlet at the first surface and an outlet at the second surface. The cooling hole includes a metering section commencing at the inlet and a diffusing section in communication with the metering section and terminating at the outlet. The metering section includes a top portion having a first arcuate surface and a bottom portion having a second arcuate surface. The first and second arcuate surfaces have arcs extending in substantially similar directions.
    Type: Application
    Filed: September 5, 2014
    Publication date: December 25, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dominic J. Mongillo, Matthew S. Gleiner
  • Publication number: 20140366545
    Abstract: In a gas turbine engine (1) that has a plurality shrouds (8c and 9c), in which each one of the shrouds (8c and 9c) are provided with a groove portion (20) that is provided in a surface facing a turbine rotor blade (8a and 9a) and a plurality of film cooling holes (21) that open to a bottom portion of the groove portion (20), blocking of the film cooling holes (21 and 22) is prevented.
    Type: Application
    Filed: August 28, 2014
    Publication date: December 18, 2014
    Inventor: Chiyuki NAKAMATA
  • Patent number: 8910481
    Abstract: A combustor for a gas turbine engine is provided. The combustor includes a forward bulkhead, an inner radial combustor wall, and an outer radial combustor wall. The bulkhead includes a plurality of circumferentially disposed injector apertures. The inner radial combustor wall includes a plurality of inner quench aperture sets. Each inner quench aperture set includes a first inner quench aperture and a second inner quench aperture separated from each other by an inner interset distance. Each inner quench aperture set is separated from an adjacent inner quench aperture set by an inner intraset distance. The inner intraset distance is different than the inner interset distance. The outer radial combustor wall includes a plurality of circumferentially disposed outer quench apertures. The outer radial combustor wall is disposed radially outside of the inner radial combustor wall, thereby defining an annular combustion region therebetween.
    Type: Grant
    Filed: May 15, 2009
    Date of Patent: December 16, 2014
    Assignee: United Technologies Corporation
    Inventors: Won-Wook Kim, Timothy S. Snyder
  • Patent number: 8904800
    Abstract: A combustor dome heat shield and a louver are separately metal injection molded and then fused together to form a one-piece combustor heat shield.
    Type: Grant
    Filed: October 10, 2012
    Date of Patent: December 9, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Lorin Markarian, Melissa Despres
  • Patent number: 8893501
    Abstract: The present application and the resultant patent provide a combustor for mixing a flow of air and a flow of fuel. The combustor may include an air path for the flow of air, a number of fuel injectors positioned in the air path for the flow of fuel, and a crossfire tube positioned within the air path upstream of the fuel injectors. The crossfire tube may include a number of purge holes positioned on a downstream side thereof to reduce a wake in the flow of air caused by the crossfire tube in the air path.
    Type: Grant
    Filed: March 28, 2011
    Date of Patent: November 25, 2014
    Assignee: General Eletric Company
    Inventors: Carolyn Ashley Antoniono, Patrick Benedict Melton
  • Publication number: 20140338347
    Abstract: A combustor is provided for a turbine engine. The combustor includes a first liner having a first side and a second side and a second liner having a first side and a second side. The second side of the second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber is configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second side of the first liner. The plurality of effusion cooling holes including a first effusion cooling hole extending from the first side to the second side with a non-linear line of sight.
    Type: Application
    Filed: January 23, 2013
    Publication date: November 20, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: HONEYWELL INTERNATIONAL INC.
  • Publication number: 20140338346
    Abstract: A combustor assembly includes a hot skin of a combustion chamber wall having an inner face exposed to the combustion chamber and an opposite outer face, a receiving skin having a securing portion affixed to the hot skin outer face in an air-tight manner and a receiving flange, extending from the securing portion, that is offset from the hot skin outer face to form a female recess, a cold skin having a cold wall portion spaced from the hot skin and forming a cooling cavity therebetween, a securing portion extending from a first end of the cold wall portion affixed to the hot skin outer face in an air-tight manner and a male flange extending from a second end of the cold wall portion opposite the first end, the male flange snugly received in the female recess and forming a sliding engagement therebetween.
    Type: Application
    Filed: October 15, 2012
    Publication date: November 20, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: PRATT & WHITNEY CANADA CORP.
  • Patent number: 8887508
    Abstract: An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, a method for designing an impingement sleeve is disclosed. The method includes determining a desired operational value for a transition piece, inputting a combustor characteristic into a processor, and utilizing the combustor characteristic in the processor to determine a cooling hole pattern for the impingement sleeve, the cooling hole pattern comprising a plurality of cooling holes, at least a portion of the plurality of cooling holes being generally longitudinally asymmetric, the cooling hole pattern providing the desired operational value.
    Type: Grant
    Filed: March 15, 2011
    Date of Patent: November 18, 2014
    Assignee: General Electric Company
    Inventors: Jerome David Brown, Ronald James Chila, Patrick Benedict Melton, Russell DeForest, David William Cihlar, Matthew Paul Berkebile, Wei Chen, John Drake Vanselow
  • Publication number: 20140318129
    Abstract: The invention relates to a combustion chamber for burning an air-fuel mixture, a gas mixture or a gas-liquid mixture, including an outer casing; a flame tube located inside the outer casing and provided with an inner space, whereby the outer casing and the flame tube form an annular channel therebetween, the flame tube including flow apertures which penetrate through its casing and interconnect the annular channel and the inner space of the flame tube; a cover part arranged in inlet ends of the outer casing and the flame tube and provided with flow apertures opening up into the annular channel; a combustion air inlet part which is arranged in an outer surface of the cover part and which is in connection with the flow apertures of the cover part; a fuel jet located in the cover part and extending inside the flame tube for feeding fuel into the flame tube.
    Type: Application
    Filed: November 22, 2012
    Publication date: October 30, 2014
    Inventor: Markus Viitamäki
  • Patent number: 8857055
    Abstract: A process is provided for forming shaped air holes, such as for use in turbine blades. Aspects of the disclosure relate to forming shaped portions of air holes using a short pulse laser, forming a metered hole corresponding to each shaped portion, and separately finishing the shaped portion using a short-pulse laser. In other embodiments, the order of these operations may be varied, such as to form the shaped portions and to finish the shaped portions using the short-pulse laser prior to forming the corresponding metered holes.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: October 14, 2014
    Assignee: General Electric Company
    Inventors: Bin Wei, Jon Conrad Schaeffer, Ronald Scott Bunker, Wenwu Zhang, Kathleen Blanche Morey, Jane Marie Lipkin, Benjamin Paul Lacy, Wilbur Douglas Scheidt
  • Publication number: 20140290258
    Abstract: A method for the arrangement of effusion holes and impingement cooling holes in a combustion chamber wall including: distribution of the effusion holes in the surface to be cooled in accordance with pattern, diameter and dimension selections made; distribution of the impingement cooling holes in accordance with pattern, diameter and dimension selections made; checking of the number of matches and their spacing from one another, taking into account the component and assembly tolerances; comparison with the permitted number and their minimum spacing; and, if quality requirements are not met, taking corrective actions, including selecting alternative diameters and patterns.
    Type: Application
    Filed: December 19, 2013
    Publication date: October 2, 2014
    Applicant: Rolls-Royce Deutschaland Ltd. & Co KG
    Inventors: Miklos GERENDAS, Maren FANTER, Volker HERZOG
  • Patent number: 8844260
    Abstract: A low calorific value fuel-fired can combustor for a gas turbine include a generally cylindrical housing, and a generally cylindrical liner disposed coaxially within the housing to define with the housing a radial outer flow passage for combustion air, the liner also defining inner combustion and a dilution zone, the dilution zone being axially distant a closed housing end relative to the combustion zone. A nozzle assembly disposed at the closed housing end includes an air blast nozzle and surrounding swirl vanes. An impingement cooling sleeve coaxially disposed in the combustion air passage between the housing and the liner impingement cools the portion of the liner defining the combustion zone. The combustion liner has an L/D ratio of in the range 1?L/D?4, and a ratio of the combustion zone volume (m3) to heat energy flow rate Q (MJ/sec) in the range 0.0026?V/Q?0.018.
    Type: Grant
    Filed: November 9, 2010
    Date of Patent: September 30, 2014
    Assignee: Opra Technologies B.V.
    Inventors: Martin Beran, Michal Koranek, Axel Lars-Uno Eugen Axelsson
  • Patent number: 8839627
    Abstract: An annular combustor includes an annular outer shell that includes a first flange that defines an inner diameter IDOS and an annular inner shell that includes a second flange that defines an outer diameter ODIS. An annular hood includes a radially outer hood flange and a radially inner hood flange. A bulkhead includes a radially outer bulkhead flange that defines an outer diameter ODB and a radially inner bulkhead flange that defines an inner diameter IDB. The first flange is secured at a radially outer joint between the radially outer hood flange and the radially outer bulkhead flange. The second flange is secured at a radially inner joint between the radially inner hood flange and the radially inner bulkhead flange. The IDOS and the ODB define a ratio R1 of IDOS/ODB that is 0.998622-1.001129, and the IDB and the ODIS define a ratio R2 of IDB/ODIS that is 0.998812-1.001388.
    Type: Grant
    Filed: February 17, 2012
    Date of Patent: September 23, 2014
    Assignee: United Technologies Corporation
    Inventors: Jonathan Jeffery Eastwood, Joey Wong, Robert M. Sonntag