Combustion Products Generator Patents (Class 60/722)
  • Patent number: 10539032
    Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine has opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution is defined by values set forth in Table 1, where the throat distribution values are within a +/?10% tolerance of the values set forth in Table 1. The throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: January 21, 2020
    Assignee: General Electric Company
    Inventors: Sumeet Soni, Rohit Chouhan, Ross James Gustafson, Matthew Peter Scoffone
  • Patent number: 10232474
    Abstract: An exemplary gas turbine engine component assembly includes, among other things, a case having a generally cylindrical outer surface. At least one synchronizing ring is received at least partially about the outer surface of the case. A plurality shims situated between an inner surface on the at least one synchronizing ring and the outer surface of the case at a plurality of shim locations are circumferentially spaced about the case outer surface. Each shim location includes at least one of the shims. A radial thickness of the shims at a first one of the shim locations is different than the radial thickness of the shims at a second one of the shim locations.
    Type: Grant
    Filed: June 22, 2016
    Date of Patent: March 19, 2019
    Assignee: United Technologies Corporation
    Inventor: John T. Pickens
  • Patent number: 10145000
    Abstract: A thermally dissipative article and a method of forming a thermally dissipative article are disclosed. The thermally dissipative article includes a component, a porous material formed in a layer on the component. The method of forming a thermally dissipative article includes providing a metal powder mixture and a soluble particulate mixture which forms a porous coating upon sintering and immersion in a solvent to remove the soluble particulate.
    Type: Grant
    Filed: May 27, 2016
    Date of Patent: December 4, 2018
    Assignee: General Electric Company
    Inventors: Yan Cui, Srikanth Chandrudu Kottilingam, Sandip Dutta, Brian Lee Tollison
  • Patent number: 9617385
    Abstract: Low dielectric constant (low-k) polyhemiaminal (PHA) and polyhexahydrotriazine (PHT) materials with cyclic aliphatic ring structures are described. The materials are formed by a method that includes heating a mixture comprising amines and paraformaldehyde. The reaction mixtures may be used to form low-k PHT prepregs, composites and dielectrics used in integrated circuits.
    Type: Grant
    Filed: October 16, 2015
    Date of Patent: April 11, 2017
    Assignee: INTERNATIONAL BUSINESS MACHINES CORPORATION
    Inventors: Dylan J. Boday, Jeannette M. Garcia, James L. Hedrick, Rudy J. Wojtecki
  • Patent number: 9127201
    Abstract: An electro-optical device includes: (1) a first electrode layer; (2) a second electrode layer; and (3) a middle layer disposed between the first electrode layer and the second electrode layer. The middle layer includes a material having the formula: [AaBbXxX?x?X?x?], where A is selected from potassium, rubidium, and cesium; B is selected from germanium, tin, and lead; X, X?, and X? are independently selected from fluorine, chlorine, bromine, and iodine; a is in the range of 1 to 9; b is in the range of 1 to 5; a sum of x, x?, and x? is in the range of 1 to 9; and the material is at least one of n-doped and p-doped.
    Type: Grant
    Filed: May 22, 2014
    Date of Patent: September 8, 2015
    Assignee: OMNIPV, INC.
    Inventors: John Kenney, Jian Jim Wang, William M. Pfenninger, Nemanja Vockic, John Midgley, Kai Shum
  • Patent number: 9032735
    Abstract: A combustor generally includes a plate that extends radially and circumferentially within at least a portion of the combustor. The combustor may also include a shroud that at least partially surrounds the plate and a plurality of tubes that extend through the plate. One or more flexible couplings may at least partially surround at least some of the plurality of tubes and the one or more flexible couplings may be connected to the plate.
    Type: Grant
    Filed: April 26, 2012
    Date of Patent: May 19, 2015
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Mark Carmine Bellino, David Edward Schick, Brian M. Leinonen
  • Patent number: 9035226
    Abstract: An exoatmospheric vehicle uses a control system that includes a thrust system to provide thrust to control flight of the vehicle. A regenerative heat system is used to preheat portions of the thrust system, prior to their use in control of the vehicle. The heat for preheating may be generated by consumption of a fuel of the vehicle, such as a monopropellant fuel. The fuel may be used to power a pump (among other possibilities), to pressurize the fuel for use by thrusters of the thrust system. The preheated portions of the thrust system may include one or more catalytic beds of the thrust system, which may be preheated using exhaust gasses from the pump. The preheating may reduce the response time of the thrusters that have their catalytic beds preheated. Other thrusters of the thrust system may not be preheated at all before operation.
    Type: Grant
    Filed: January 20, 2014
    Date of Patent: May 19, 2015
    Assignee: Raytheon Company
    Inventors: Wayne C Jouse, Mark S Muktoyuk
  • Publication number: 20150132117
    Abstract: A ducting arrangement (10), including: a plurality of discrete ducts (18), each defining a flow path and configured to receive a flow of combustion gases from a respective combustor can, where the plurality of discrete ducts merge to form a common duct structure; and a throat insert (50) configured to define at least part of a junction of one of the discrete ducts and the common duct structure.
    Type: Application
    Filed: November 8, 2013
    Publication date: May 14, 2015
    Inventors: John J. Marra, Jay A. Morrison, Ernie B. Campbell
  • Publication number: 20150121879
    Abstract: There is provided a gas turbine combustor capable of improving cooling performance of a combustion chamber thereof and reducing the amount of NOx emissions.
    Type: Application
    Filed: November 3, 2014
    Publication date: May 7, 2015
    Inventors: Yoshitaka HIRATA, Shohei YOSHIDA, Tomoki URUNO, Akinori HAYASHI, Hirokazu TAKAHASHI
  • Publication number: 20150121880
    Abstract: An interface assembly for a combustor includes an interface housing having a channel defined by a forward wall and at least one aft wall segment, the aft wall segment operatively coupled to an aft flange of a flow sleeve. Also included is a piston ring fittingly disposed in the channel.
    Type: Application
    Filed: November 1, 2013
    Publication date: May 7, 2015
    Applicant: General Electric Company
    Inventors: Kyle Lee Kidder, Donald Timothy Lemon, Stephen Gerard Pope
  • Publication number: 20150101331
    Abstract: A gas turbine engine having a fire wall that is configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone when the gas turbine engine is in use. The gas turbine also has an actuator that is located in the first zone and is configured to generate a mechanical force when operated, an actuatable device that is located in the second zone and is configured to be actuated by a mechanical force and a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall. The mechanical force transmitting device is configured to, when the actuator is operated, actuate the actuatable device by transmitting a mechanical force generated by the actuator to the actuatable device.
    Type: Application
    Filed: September 16, 2014
    Publication date: April 16, 2015
    Inventors: Robert GOULDS, Brian Richard LACE, Richard PEACE
  • Patent number: 8997494
    Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
    Type: Grant
    Filed: October 31, 2012
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventors: Sue-Li Chuang, Yuan Dong, Sanjay S. Hingorani, Dilip Prasad
  • Publication number: 20150089950
    Abstract: A method for determining the temperature of an aggressive and/or abrasive gas is described using an acoustic transmitter and an acoustic receiver. The transmitter emits an acoustic signal with varying frequencies and the receiver extracts from the acoustic input signal a frequency of the maximum. Based on this the frequency of this maximum the temperature of the gas between transmitter and receiver is calculated.
    Type: Application
    Filed: September 25, 2014
    Publication date: April 2, 2015
    Inventors: Bruno SCHUERMANS, Dominik WASSMER
  • Publication number: 20150082794
    Abstract: Acoustic damping resonators (60, 62, 76, 78) formed in pockets (32) between reinforcing ribs (30) in a grid of ribs on the outer surface of a wall (74) surrounding a combustion gas flow path (18). Each resonator has a perforated cover plate (64A-C) spanning between sides formed by the ribs (30). Film cooling exit holes (44) are provided in the wall (74) under each resonator. Resonating chambers (48A-C) of different volumes may be provided on the wall to damp different unwanted frequencies. Different sets of resonators with different volumes may be separately controlled by respective airflow control manifolds (66) via throttle valves (68, T1-T3). Control logic (70) may control the valves based on frequency/airflow response functions (80, 82) for each size of resonator to optimize damping and cooling and to lower emissions over varying engine operating conditions.
    Type: Application
    Filed: September 26, 2013
    Publication date: March 26, 2015
    Inventor: Reinhard Schilp
  • Patent number: 8990026
    Abstract: A power generation plant including a plurality of combustor cans, one or more sensors configured to measure acoustic vibrations from the plurality of combustor cans, and a controller that includes a processor. The processor is programmed to identify a dominant tone of the measured acoustic vibrations, the dominant tone being a frequency where a highest amount of energy lies, determine, for each of the plurality of combustor cans, a frequency of the dominant tone at predefined time intervals, and determine a degradation status of at least one of the plurality of combustor cans based on the frequency of the dominant tone at each of the predefine time intervals for the at least one of the plurality of combustor cans.
    Type: Grant
    Filed: January 3, 2012
    Date of Patent: March 24, 2015
    Assignee: General Electric Company
    Inventors: Tauseef Ahmed Shaikh, Robert Joseph Iasillo, Praveen Babulal Jain, KrishnaKumar Pg, Ajith Kizhuthrukovil Radhakrishnan, Mallareddy Soudary
  • Publication number: 20150068211
    Abstract: A can-annular gas turbine engine combustion arrangement (10), including: a combustor can (12) comprising a combustor inlet (38) and a combustor outlet circumferentially and axially offset from the combustor inlet; an outer casing (24) defining a plenum (22) in which the combustor can is disposed; and baffles (70) configured to divide the plenum into radial sectors (72) and configured to inhibit circumferential motion of compressed air (16) within the plenum.
    Type: Application
    Filed: September 12, 2013
    Publication date: March 12, 2015
    Inventor: Jose L. Rodriguez
  • Publication number: 20150059344
    Abstract: A turbomachine combustion chamber shell ring in which dilution holes in the turbomachine combustion chamber shell ring are covered with inserts defining chambers around same on an inner face of the shell ring. Ventilation holes, through the insert, induce ventilation of portions of the shell ring surrounding the dilution holes, cool the portions, and prevent crack formation.
    Type: Application
    Filed: May 23, 2013
    Publication date: March 5, 2015
    Applicant: SNECMA
    Inventor: Denis Jean Maurice Sandelis
  • Publication number: 20150047363
    Abstract: A gas turbine includes a combustion chamber and a microwave source to produce microwave radiation. The gas turbine is arranged to guide the microwave radiation into a cavity of the combustion chamber. Due to the microwave radiation, in the cavity of the combustion chamber, combustion in the cavity may be supported and thus lean operation of the gas turbine is made possible.
    Type: Application
    Filed: June 24, 2014
    Publication date: February 19, 2015
    Inventors: Juergen STEINWANDEL, Johannes STUHLBERGER
  • Publication number: 20150047364
    Abstract: The invention relates to a burner arrangement for using in a single combustion chamber or in a can-combustor comprising a center body burner located upstream of a combustion zone, an annular duct with a cross section area, intermediate lobes which are arranged in circumferential direction and in longitudinal direction of the center body. The lobes being actively connected to the cross section area of the annular duct, wherein a cooling air is guided through a number of pipes within the lobes to the center body and cools beforehand at least the front section of the center body based on impingement cooling. Subsequently, the impingement cooling air cools the middle and back face of the center body based on convective and/or effusion cooling. At least the back face of the center body includes on the inside at least one damper.
    Type: Application
    Filed: July 29, 2014
    Publication date: February 19, 2015
    Inventors: Xianfeng Gao, Urs Benz, Andre Theuer, Rohit Kulkarni
  • Publication number: 20150047356
    Abstract: A turbine engine, a turbojet, or a turboprop engine, including an annular combustion chamber defined by an inner shell and an outer shell, a turbine distributor arranged downstream of the combustion chamber, with a downstream end of the outer shell and/or of the inner shell of the chamber including a radial rim arranged opposite a radial rim of an upstream end of the distributor, a sealing mechanism including at least one strip extending between the rims to provide a seal between the combustion chamber and the distributor. The sealing strip extends axially and circumferentially between the rims and bears sealingly against free ends of the rims.
    Type: Application
    Filed: April 9, 2013
    Publication date: February 19, 2015
    Applicant: SNECMA
    Inventors: Francois Leglaye, Emeric D'Herbigny
  • Publication number: 20150047358
    Abstract: An inner barrel member for a gas turbomachine includes a body having an outer surface, an inner surface and one or more radial flow splitters provided on the outer surface. The one or more radial flow splitters are configured and disposed to be arranged along a combustor centerline at a combustion flow outlet radially inwardly of a transition piece.
    Type: Application
    Filed: August 14, 2013
    Publication date: February 19, 2015
    Applicant: General Electric Company
    Inventors: Carl Gerard Schott, Kenneth Damon Black, Matthew Stephen Casavant
  • Publication number: 20150040567
    Abstract: A turbine assembly is disclosed herein. The turbine assembly may include a rotor with at least one bucket extending radially therefrom. The turbine assembly also may include a stator assembly positioned adjacent to the at least one bucket. Moreover, the turbine assembly may include a seal assembly. The seal assembly may include a first flange extending in a substantially axial direction from the at least one bucket. The seal assembly also may include a second flange extending from the stator assembly in the substantially axial direction opposite the first flange. The second flange may include at least one protuberance projecting towards the first flange.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 12, 2015
    Applicant: General Electric Company
    Inventors: Guoqiang Lu, Xiaoqing Zheng, Jong Youn Pak
  • Publication number: 20150040566
    Abstract: A helical seal system includes a first component, and a second component rotatable relative to the first component. The second component extends from a high pressure portion to a low pressure portion through an intermediate portion. A helical seal is provided on the intermediate portion of the second component. The helical seal includes at least one thread component having a pitch that is configured and disposed to draw fluids from the low pressure portion toward the high pressure portion when the second component is rotated.
    Type: Application
    Filed: August 6, 2013
    Publication date: February 12, 2015
    Applicant: General Electric Company
    Inventors: Radu Ioan Danescu, David Martin Johnson
  • Publication number: 20150040568
    Abstract: A gas turbine combustor floating collar for mounting an igniter or fuel nozzle to a combustor is provided with an outer periphery in a non-circular shape, for example having at least one section thereof formed with a flat surface, such as a square or triangular shape. The outer periphery of the floating collar is complementary to and completely surrounded by an inner periphery surface of a recess of a boss affixed on the combustor, thereby preventing substantial rotation of the floating collar with respect to the boss.
    Type: Application
    Filed: August 12, 2013
    Publication date: February 12, 2015
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Honza STASTNY, Bhawan B. PATEL, Ram KULATHU, Sudhakara Reddy ANNEM, Balakrishna GAJA, Bharath Mandya NAGARAJ
  • Publication number: 20150033746
    Abstract: A heat shield for a combustion chamber of a gas turbine engine is disclosed. The heat shield includes a plate portion, an inner ring, and a plurality of standoffs. The plate portion includes an annular sector shape. The inner ring extends from an inner part of the plate portion. The inner ring includes a hollow cylinder shape. The plurality of standoffs extends from the plate portion, proximate outer edges of the plate portion and in the same direction as the inner ring. The plurality of standoffs forms a plurality of scallops. Each scallop is located between adjacent standoffs.
    Type: Application
    Filed: August 2, 2013
    Publication date: February 5, 2015
    Applicant: SOLAR TURBINES INCORPORATED
    Inventors: Daniel William Carey, Robert Anthony Corr, II, Crosby Hayhurst Johnson, Yong Weon Kim
  • Publication number: 20150007570
    Abstract: The invention concerns a method for manufacturing of a gas turbine engine component (37) comprising an outer ring structure (42, 47), an inner ring structure (41), and a plurality of circumferentially spaced elements (46, 46a, 46b) extending between the inner ring structure (41) and the outer ring structure (42), wherein a primary gas channel for axial gas flow is defined between the elements (46, 46a, 46b), and wherein the component (37) has an inlet side for gas entrance and an outlet side for gas outflow. The invention is characterized in that the method comprises the step of machining a one-piece metal blank as to form a one-piece part (47) comprising: a portion (46b) of each of said elements (46), wherein said portion (46b) relates to a portion of an extension length of the elements (46) between said ring structures (41, 42); and a ring-shaped member (42) that connects said element portions (46b) and that is intended to form part of one of the ring structures.
    Type: Application
    Filed: December 20, 2011
    Publication date: January 8, 2015
    Applicant: GKN Aerospace Sweden AB
    Inventors: Lars-Olof Hellgren, Olof Lewin, Kent Holmedahl
  • Publication number: 20150000305
    Abstract: A variable area fan nozzle comprising an array of rigid petals and a petal actuation system comprising left and right assemblies, each assembly comprising: a multiplicity of tracks attached to or integrally formed with respective petals; a curved pivoting ring segment; an actuator coupled to the ring segment; and a multiplicity of sets of cam followers spaced along the ring segment and aligned with respective tracks. Each ring segment is pivotable between first and second angular positions depending on how the state of the actuator changes. As one ring segment pivots in one direction, one set of cam followers exert inward forces on the tracks to deflect petals inward; as that ring segment pivots in the other direction, another set of cam followers exert outward forces on the tracks to deflect petals outward.
    Type: Application
    Filed: June 27, 2013
    Publication date: January 1, 2015
    Applicant: The Boeing Company
    Inventor: Christopher T. Jasklowski
  • Publication number: 20150000297
    Abstract: The invention relates to a method for determining at least one firing temperature for controlling a gas turbine that comprises at least one compressor, at least one combustion chamber and at least one turbine, compressed air being drawn off at the compressor in order to cool the turbine and being fed to the turbine via at least one external cooling duct and via a control valve arranged in the cooling duct, in which method a plurality of temperatures and pressures of the working medium being measured in various positions of the gas turbine and the at least one firing temperature being derived from the measured temperatures and pressures. A more flexible and more accurate control is achieved additionally by determining the cooling air mass flow via the external cooling duct and by taking said flow into account when deriving the at least one firing temperature.
    Type: Application
    Filed: September 19, 2014
    Publication date: January 1, 2015
    Inventors: Manuel ARIAS CHAO, Anton NEMET, Ulrich Robert STEIGER, Darrel Shayne LILLEY
  • Publication number: 20140366546
    Abstract: A gas turbine engine includes a compressor, a combustor adjacent the compressor, a turbine adjacent the combustor, a shaft, a motor, a variable frequency drive, a stored energy source and a ride thru unit. The motor is coupled to the shaft. The variable frequency drive is electrically connected to the motor and to an AC power source. The ride thru unit electrically connects to the variable frequency drive, the AC power source and the stored energy source. The ride thru unit includes at least one DC to DC voltage converter.
    Type: Application
    Filed: June 13, 2013
    Publication date: December 18, 2014
    Inventors: Rachel Bruno, Daniel Fingleton, Scott Hitoshi Kato
  • Publication number: 20140360193
    Abstract: A support frame for assembling a combustion module for a gas turbine includes a base plate disposed at a bottom end of the support frame and a support plate that is vertically separated from the base plate by one or more vertical support members. The support plate defines an opening that is sized to allow a portion of the combustion module to pass therethrough. A support block extends vertically from the base plate towards the support plate where the support block defines one or more fastener holes for connecting an aft end of a combustion liner of the combustion module to the support block. A central support column extends vertically from the base plate towards the support plate. A horizontal support extends radially outward from the central support column to align the combustion liner with the opening in the support plate.
    Type: Application
    Filed: March 18, 2013
    Publication date: December 11, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: General Electric Company
  • Publication number: 20140360203
    Abstract: A process of producing heat energy for use in heat exchange with other fluids and substances so as to impart said heat energy to said fluid or substances which includes several steps. In a first step, a mixture of fuel and oxidant is ignited in a combustion zone or zones (16, 18, 98, 122) to create a combusted fuel mix which in the form of shockwaves are carried away from the combustion zone or zones (16, 18, 98, 122) to provide a low pressure area within the combustion zone or zones (16, 18, 98, 122).
    Type: Application
    Filed: December 21, 2012
    Publication date: December 11, 2014
    Inventor: Matthew Fox
  • Publication number: 20140360194
    Abstract: A toroidal combustion chamber and a plurality of plates are disposed with respect to one another such that their labyrinthine walls are juxtaposed and form labyrinthine conduits leading from an exhaust outlet of the toroidal combustion chamber to an exit perpendicular to the exhaust outlet.
    Type: Application
    Filed: August 22, 2014
    Publication date: December 11, 2014
    Applicant: Power Generation Technologies Development Fund, L.P.
    Inventor: Ernst BERGEN
  • Patent number: 8895134
    Abstract: A running-in coating for a compressor housing is disclosed. The running-in coating has at least two layers where a first layer is dimensionally stable and at least one additional layer has run-in capability.
    Type: Grant
    Filed: April 29, 2005
    Date of Patent: November 25, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Wilfried Smarsly, Renate Mendritzki, Horst Mueller-Wittek
  • Patent number: 8893382
    Abstract: A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.
    Type: Grant
    Filed: September 30, 2011
    Date of Patent: November 25, 2014
    Assignee: General Electric Company
    Inventors: David Bruce Patterson, Donald Michael Corsmeier, Craig Douglas Young, Donald Lee Gardner, James Edward Thompson, Daniel Dale Brown, Glenn Edward Wiehe, Donald Scott Yeager, Mark Willard Marusko, Michael Joseph Zerbe
  • Publication number: 20140338336
    Abstract: A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber.
    Type: Application
    Filed: September 26, 2012
    Publication date: November 20, 2014
    Applicant: United Technologies Corporation
    Inventors: Frank J. Cunha, Nurhak Erbas-Sen
  • Publication number: 20140338349
    Abstract: The present application provides a combustion nozzle for use with a gas turbine engine. The combustion nozzle may include a number of mixing tubes, an outer shell surrounding the mixing tubes, and a floating aft plate assembly. The floating plate assembly may enclose the outer shell. The mixing tubes may extend through the aft plate assembly.
    Type: Application
    Filed: October 29, 2012
    Publication date: November 20, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: General Electric Company
  • Publication number: 20140298814
    Abstract: A system for pre-heating a working fluid within a combustor includes a compressor for providing the working fluid to the combustor. An outer casing is disposed downstream from the compressor. The outer casing at least partially defines a high pressure plenum that at least partially surrounds the combustor. A combustion chamber is defined within the combustor downstream from the high pressure plenum. A catalytic combustor is disposed within the high pressure plenum upstream from the combustion chamber so as to provide thermal energy to the working fluid upstream from the combustion chamber.
    Type: Application
    Filed: April 8, 2013
    Publication date: October 9, 2014
    Applicant: General Electric Company
    Inventors: John Anthony Conchieri, Roy Marshall Washam, Gilbert Otto Kraemer
  • Publication number: 20140260277
    Abstract: A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.
    Type: Application
    Filed: March 18, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Richard Martin DiCintio, Patrick Benedict Melton, Lucas John Stoia, Christopher Paul Willis, Ronnie Ray Pentecost
  • Publication number: 20140260273
    Abstract: A combustion liner for a gas turbine combustor includes an annular main body having a forward end axially separated from an aft end, and a transitional intersection defined between the forward end and the aft end. The main body extends continuously from the forward end to the aft end. A plurality of fuel injector passages extend radially through the main body upstream from the transitional intersection. The main body comprises a conical section having a circular cross section that diverges between the forward end and the transitional intersection, and a transition section having a non-circular cross section that extends from the transitional intersection to the aft end of the main body.
    Type: Application
    Filed: March 18, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Patrick Benedict Melton, Lucas John Stoia, Richard Martin DiCintio
  • Publication number: 20140260257
    Abstract: An annular wall of a combustion chamber of a turbine engine including: a cold side and a hot side; plural dilution holes to allow circulating air of the cold side to enter the hot side for dilution of an air/fuel mixture; plural cooling orifices to allow the circulating air of the cold side to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices distributed spaced axially from one another and with geometric axes inclined, in an axial direction of flow of combustion gases, by an inclination angle relative to a normal to the annular wall; plural additional cooling orifices arranged directly downstream of the dilution holes and distributed spaced axially from one another, with geometric axes arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination relative to a normal to the annular wall.
    Type: Application
    Filed: October 25, 2012
    Publication date: September 18, 2014
    Applicants: SNECMA, TURBOMECA
    Inventors: Matthieu Francois Rullaud, Bernard Joseph, Jean-Pierre Carrere, Hurbert Pascal Verdier
  • Publication number: 20140260288
    Abstract: In accordance with one aspect of the present technique, a method is disclosed. The method includes modifying one or more operational parameters of a gas turbine (GT) to increase an exhaust gas temperature above a standard start-up temperature. The method also includes receiving at least one of GT operational data, heat recovery steam generator (HRSG) operational data, and steam turbine (ST) operational data from a plurality of sensors. The method further includes predicting a ST roll-off time based on at least one of the GT operational data, the HRSG operational data, and the ST operational data. The method further includes modifying the one or more operational parameters of the GT to satisfy one or more ST roll-off permissives at the predicted ST roll-off time.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Applicant: General Electric Company
    Inventors: Fernando Javier D'Amato, Rodrigo Lopez-Negrete de la Fuente, Aditya Kumar, Emrah Biyik
  • Publication number: 20140260256
    Abstract: A combustion chamber includes an inner wall, an outer wall surrounding the inner wall, and a flow passage between the inner wall and outer wall that permits forward flow and restricts reverse flow. The inner wall has a plurality of effusion holes in fluid communication with the inside of the combustion chamber. The outer wall has a plurality of cooling side holes in fluid communication with a cooling source. The inner wall and the outer wall define a flow passage therebetween that fluidly connects one or more of the cooling side holes with one or more of the effusion holes. The flow passage has a geometric configuration to permit forward flow of gases through the flow passage from the cooling source to the inside of the combustion chamber and to restrict reverse flow of gases through the flow passage from the inside of the combustion chamber to the cooling source. The permitted flow rate is greater than the restricted flow rate.
    Type: Application
    Filed: March 10, 2014
    Publication date: September 18, 2014
    Inventors: James C. Loebig, Christopher D. DeBruhl, John D. Holdcraft
  • Publication number: 20140230440
    Abstract: A combustion chamber comprises an outer wall and an inner wall. The outer wall has mounting apertures extending there-though and the inner wall has threaded studs extending there-from. The threaded studs extend through the mounting apertures in the outer wall. Cooperating nuts locate on the studs. Walls are positioned between the outer wall and the inner wall. Each wall is spaced from and extends around a respective fastener to form a chamber around the respective fastener. Apertures extend through the outer wall. Each aperture is spaced from a respective mounting aperture. Each aperture allows a flow of coolant into the associated chamber and around the associated fastener to cool the fastener. Each wall has an opening at a position diametrically opposite to associated aperture to allow the flow of coolant out of the chamber to a space between the outer wall and the inner wall.
    Type: Application
    Filed: January 28, 2014
    Publication date: August 21, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventor: Timothy Hal SUMMERS
  • Publication number: 20140223912
    Abstract: An annular combustion chamber for a turbine engine, the chamber including an inner wall and an outer wall forming surfaces of revolution, the walls being connected together by a chamber end wall fitted with a fuel injection mechanism, each of the inner and outer walls including primary holes and dilution holes situated downstream from the primary holes in a gas flow direction, the primary and dilution holes being regularly distributed around the circumference of the inner and outer walls. The outer wall has a greater number of dilution holes than the inner wall.
    Type: Application
    Filed: September 25, 2012
    Publication date: August 14, 2014
    Applicant: SNECMA
    Inventors: Matthieu Francois Rullaud, Michel Pierre Cazalens
  • Publication number: 20140208755
    Abstract: A method and system for measuring a mass flow rate in a portion of a flow path in an inlet duct of a gas turbine engine is provided. The system includes a sensor assembly attached to the inlet duct. The sensor assembly includes a tube with a longitudinal axis disposed in a substantially laminar flow region of the inlet duct, and a flow conditioner disposed in the tube. A hot wire sensor disposed in the tube is also provided.
    Type: Application
    Filed: October 23, 2013
    Publication date: July 31, 2014
    Applicant: General Electric Company
    Inventors: Sanji Ekanayake, Alston Ilford Scipio, Rex Allen Morgan, Sascha Schieke, Thomas C. Billheimer
  • Publication number: 20140208771
    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion having an exterior surface and an internal surface. A cavity is disposed inside of the body portion. A cooling hole extends between the exterior surface and the internal surface and includes a metering section having an outlet and an inlet. The inlet is shaped dissimilar to the outlet.
    Type: Application
    Filed: December 28, 2012
    Publication date: July 31, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: United Technologies Corporation
  • Publication number: 20140202158
    Abstract: A heat exchanger assembly comprises a heat exchanger body including a first fluid circuit and a second fluid circuit. The first circuit includes a first bypass valve in flow communication with a first fluid circuit inlet channel. The first fluid circuit also includes a plurality of cooling channels in flow communication with the first bypass valve. The first bypass valve is configured to channel a first fluid to the plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the first fluid. The second fluid circuit includes a second bypass valve configured to facilitate a flow of a second fluid through at least a portion of the heat exchanger body during the first mode of operation.
    Type: Application
    Filed: May 22, 2013
    Publication date: July 24, 2014
    Applicant: UNISON INDUSTRIES, LLC
    Inventors: Michael Ralph Storage, Dennis Alan McQueen, Roger Earl Foster
  • Publication number: 20140196464
    Abstract: A system includes a gas turbine engine that includes a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section, and a fluid supply system coupled to the exhaust section. The fluid supply system is configured to route an inert gas to the exhaust section.
    Type: Application
    Filed: December 19, 2013
    Publication date: July 17, 2014
    Applicants: EXXONMOBIL UPSTREAM RESEARCH COMPANY, GENERAL ELECTRIC COMPANY
    Inventors: Pramod K. Biyani, Rajarshi Saha, Anil Kumar Dasoji, Richard A. Huntington, Franklin F. Mittricker
  • Publication number: 20140190166
    Abstract: A combustion chamber comprises an outer wall and an inner wall spaced from the outer wall. The outer wall has at least one mounting aperture extending there-through and the inner wall has threaded studs extending there-from. The threaded studs extend through the mounting apertures in the outer wall. Cooperating nuts locate on the studs and washers are positioned between the outer wall and the cooperating nuts. Each washer has a rim and a bore. The washers have one or more passages extending there-through from the rim to the bore of the washer to provide a flow of coolant through the passages in the washers, the mounting apertures in the outer wall and around the threaded studs to cool the threaded studs to increase the working life of the inner wall. Other cooling arrangements for the threaded studs are disclosed.
    Type: Application
    Filed: December 5, 2013
    Publication date: July 10, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventors: Anthony PIDCOCK, Paul Ian CHANDLER
  • Publication number: 20140182292
    Abstract: An article includes a body portion made of a metal and configured for use in a gas turbine engine, a sensing feature monolithically formed with the body portion, and an interior passage connected to the sensing feature and passing through the body portion. An article with integrated sensing features may be made additive manufacturing, resulting in a structure having internal passageways connecting an aperture at one surface of the monolithic article to a second aperture at another surface of the monolithic article at the opposite end of the internal passageway.
    Type: Application
    Filed: December 29, 2012
    Publication date: July 3, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: David J. Hudon, Steven D. Roberts, Gary A. Schirtzinger, Joe Ott