With Diversely Oriented Inlet Or Additional Inlet For Diverse Fluid (e.g., Heating, Cooling Or Mixed Working Fluid, Etc.) Patents (Class 415/116)
  • Patent number: 10132194
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling flow inserts direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: November 20, 2018
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Daniel K. Vetters
  • Patent number: 10132197
    Abstract: Shrouds and shroud assemblies for gas turbine engines are provided. A shroud includes a shroud body. The shroud body includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a flange extending from the shroud body, and a bore hole defined in the flange. The bore hole extends generally circumferentially through the flange between a first opening and a second opening.
    Type: Grant
    Filed: April 20, 2015
    Date of Patent: November 20, 2018
    Assignee: General Electric Company
    Inventors: Bryce Loring Heitman, Michael Todd Radwanski, Darrell Glenn Senile
  • Patent number: 10107206
    Abstract: A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A high pressure air tap includes a lower temperature tapped path and a higher temperature tapped path and a valve for selectively delivering one of the lower temperature tapped path and the higher temperature tapped path into the bore of the disc. The valve is operable to selectively block flow of either of the lower pressure and higher pressure tapped paths to the bore of the disc, with the disc including holes to allow air from compressor chambers to communicate with the bore of the disc. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.
    Type: Grant
    Filed: October 8, 2015
    Date of Patent: October 23, 2018
    Assignee: United Technologies Corporation
    Inventors: Matthew P. Forcier, Paul J. Hiester, Andrew J. Murphy
  • Patent number: 10107103
    Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is configured for guiding a medium in its interior. In order to guide the medium in the interior with low flow losses, a pair of rotor disks lie on one another, of which the first of the two rotor disks of the pair has holes, in order to feed the medium from the outside into the rotor interior, and rib-shaped ribs, in order to guide the medium further in the direction of the rotational axis, and the second rotor disk of the pair being configured with the aid of an auxiliary web in such a way that the flow passages which are formed between the ribs as viewed in the circumferential direction are delimited axially at least over the large part of the radial extent of the ribs.
    Type: Grant
    Filed: June 26, 2014
    Date of Patent: October 23, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventors: Karin Costamagna, Karsten Kolk, Sebastian Stock, Vyacheslav Veitsman
  • Patent number: 10100667
    Abstract: A gas turbine engine component is provided. The gas turbine engine component comprises a main body and a leading edge cooling passage defined within the main body. The main body has a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The leading edge cooling passage comprises an axial flow cooling passage defined within the main body and adjacent to the leading edge wall and has a leading edge periphery that generally conforms to the elongated transition portion of the leading edge wall.
    Type: Grant
    Filed: January 15, 2016
    Date of Patent: October 16, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Anthony B. Swift, Paul M. Lutjen, Neil L. Tatman, Dominic J. Mongillo, Jr., Matthew A. Devore, Ken F. Blaney
  • Patent number: 10100659
    Abstract: A component of a turbine is disclosed. The component includes an carrier segment having a rail, an frame segment including a hanger having a flange supported on the rail of the carrier segment, and an inner surface having a section of a track for a turbine blade defined therein. The component also includes a retainer segment secured to the carrier segment such that the hanger is secured between the retainer segment and the carrier segment.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: October 16, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce plc
    Inventors: Joseph P. Lamusga, Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Simon L. Jones
  • Patent number: 10100738
    Abstract: A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the first conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage. A gas turbine engine is also provided and may comprise a compressor, a combustor in fluid communication with the compressor, and a diffuser around the combustor and a turbine. A heat exchanger may have an inlet fluidly coupled to the diffuser. A second conduit may be fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the second conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: October 16, 2018
    Assignee: United Technologies Corporation
    Inventors: James D. Hill, William K. Ackermann
  • Patent number: 10100649
    Abstract: A gas turbine engine assembly includes a supporting component and a supported component. The supporting component includes features engaged by the supported component. The supported component comprises ceramic-containing materials.
    Type: Grant
    Filed: March 10, 2016
    Date of Patent: October 16, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Joseph P. Lamusga, Ted J. Freeman, Andrew J. Lazur
  • Patent number: 10094296
    Abstract: A gas turbine engine has a compressor rotor with blades and a disk. A bore is defined radially inwardly of the disk. A combustor includes a burner nozzle. A tap taps air that has been combusted in the combustor section through a valve, and into the bore of the disk. A method is also disclosed.
    Type: Grant
    Filed: February 11, 2014
    Date of Patent: October 9, 2018
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Paul W. Duesler
  • Patent number: 10094285
    Abstract: A gas turbine engine including an outer case and an exhaust gas passage defined within the outer case for conducting an exhaust gas flow from a turbine section of the gas turbine engine. A cooling channel is associated with an outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct structure is provided and includes an inlet end in fluid communication with the channel outlet and includes an outlet end in fluid communication with an area of reduced pressure relative to the air duct structure inlet end. An exit cavity is located at the air duct structure outlet end, wherein the exit cavity effects a reduced pressure at the outlet end to draw air from the cooling channel into the air duct.
    Type: Grant
    Filed: January 22, 2013
    Date of Patent: October 9, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Mrinal Munshi, John W. Finneran, Yevgeniy Shteyman, Daryl J. Graber, Matthew R. Porter, Jonathan M. Leagon
  • Patent number: 10087762
    Abstract: A turbine wheel is disposed about an axis and has a back face including a plurality of lobes disposed about a periphery of the back face. The lobes define scalloped areas therebetween. The scalloped areas are further defined by a radius BR2 that blends into a first lobe and into a radius BR1 that also blends into a flat area.
    Type: Grant
    Filed: July 11, 2011
    Date of Patent: October 2, 2018
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Loc Quang Duong, Xiaolan Hu, Gao Yang, Anthony C. Jones
  • Patent number: 10087782
    Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.
    Type: Grant
    Filed: March 12, 2014
    Date of Patent: October 2, 2018
    Assignee: United Technologies Corporation
    Inventors: Cheng-Zhang Wang, Jorn A. Glahn, David F. Cloud, Peter M. Munsell, Clifton J. Crawley, Jr., Robert Newman, Michelle Diana Stearns
  • Patent number: 10087906
    Abstract: A hydraulic turbine according to an embodiment includes a turbine body, a running water surface provided in the turbine body, the running water surface defining a channel for water, and a coating layer provided on the running water surface, the coating layer being formed by water-repellent paint or hydrophilic paint.
    Type: Grant
    Filed: July 28, 2014
    Date of Patent: October 2, 2018
    Assignee: KABUSHIKI KAISHA TOSHIBA
    Inventors: Kazuyuki Nakamura, Toshimasa Mukai, Satoru Kuboya, Hajime Koyama, Takuya Tomioka, Takanori Nakamura, Naritoshi Nakagawa
  • Patent number: 10087843
    Abstract: An assembly for a gas turbine engine includes a first component, a second component, and a first mount. The first mount includes an annular body that is connected to the first component and a plurality of circumferentially spaced tabs extending from the body. The tabs are connected to the second component and are deflectable to allow the second component to move relative to the first component.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: October 2, 2018
    Assignee: United Technologies Corporation
    Inventor: Matthew Budnick
  • Patent number: 10082039
    Abstract: An annular seal includes an annular outer casing, a plurality of seal segments, and a plurality of spring components. The plurality of seal segments is coupled to the annular outer casing to cumulatively form an annular sealing surface, the annular sealing surface is configured to face a rotating structure to inhibit fluid leakage between the rotating structure and the annular sealing surface, and each seal segment of the plurality of seal segments is configured for independent radial movement relative to other seal segments of the plurality of seal segments. In various embodiments, the plurality of spring components are configured to bias the plurality of seal segments relative to the radial movement.
    Type: Grant
    Filed: November 2, 2016
    Date of Patent: September 25, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Russell B. Hanson
  • Patent number: 10066630
    Abstract: A fan assembly is provided. The fan assembly includes a fan, a fan casing circumscribing the fan, and a fan casing heating system in thermal communication with the fan casing. The fan includes a hub, and a plurality of fan blades extending from the hub. Each fan blade of the plurality of fan blades terminates at a respective blade tip. A clearance gap is defined between the fan casing and the blade tips. The fan casing heating system is configured to apply heat to the fan casing when the fan is operating in a first operational mode, and remove the applied heat when the fan transitions into a second operational mode.
    Type: Grant
    Filed: June 15, 2016
    Date of Patent: September 4, 2018
    Assignee: General Electric Company
    Inventors: Hemanth Gudibande Sathyakumar Kumar, Bhaskar Nanda Mondal, Thomas Ory Moniz
  • Patent number: 10066497
    Abstract: A blade outer air seal (BOAS) actuator assembly, according to an exemplary aspect of the present disclosure includes, among other things, an actuator member; and a retractor configured to move with the actuator member to move a BOAS segment from a first position to a second position that is radially outside the first position, the BOAS segment seated against a support structure when in the first position and spaced from the support structure when in the second position.
    Type: Grant
    Filed: February 18, 2014
    Date of Patent: September 4, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Brian Duguay
  • Patent number: 10053999
    Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.
    Type: Grant
    Filed: April 7, 2014
    Date of Patent: August 21, 2018
    Assignee: United Technologies Corporation
    Inventors: Michael G. McCaffrey, Brandon T. Rouse, Mark Borja, Igor S. Garcia, John R. Farris, Thomas Almy, Brian R. Pelletier
  • Patent number: 10047624
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: January 22, 2016
    Date of Patent: August 14, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman
  • Patent number: 10047618
    Abstract: A component system of a turbine engine including a first component segment and a second component segment configurable in a ring segment shape, so that at least one abutment surface of the first component segment and an abutment surface of the second component segment abut against each other; together, the first component segment and the second component segment including at least three overlapping elements for sealing a gap between the abutment surfaces. In the case of mutually abutting abutment surfaces, each overlapping element overlapping radially with the respective other component segment. At least two of the overlapping elements are configured on the first component segment, while at least one of the overlapping elements is configured on the second component segment. In the case of mutually abutting abutment surfaces, the overlapping element of the second component segment is axially configured between the overlapping elements of the first component segment.
    Type: Grant
    Filed: September 23, 2014
    Date of Patent: August 14, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Thomas Hess, Manfred Feldmann
  • Patent number: 10047620
    Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.
    Type: Grant
    Filed: December 16, 2014
    Date of Patent: August 14, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Davide Giacché, John David Stampfli, Ramakrishna Venkata Mallina, Vittorio Michelassi, Giridhar Jothiprasad, Ajay Keshava Rao, Rudolf Konrad Selmeier, Sungho Yoon, Ivan Malcevic
  • Patent number: 10047630
    Abstract: A method of mixing airflow within an inner diameter (ID) mixing chamber of a turbine exhaust case (TEC) includes directing pressurized airflow into the ID mixing chamber. Cooling airflow is directed radially inward via a tube and is then expelled into the ID mixing chamber in a circumferential direction for mixing with the pressurized airflow.
    Type: Grant
    Filed: December 17, 2013
    Date of Patent: August 14, 2018
    Assignee: United Technologies Corporation
    Inventors: William Yeager, Donna Clough
  • Patent number: 10041353
    Abstract: A blade cascade of a turbomachine whose at least one side wall is configured to be circumferentially undulated and which has at least two elevations and at least one depression or at least two depressions having at least one elevation, as well as a turbomachine having a blade cascade of this kind.
    Type: Grant
    Filed: August 6, 2014
    Date of Patent: August 7, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Jochen Gier, Yavuz Guendogdu, Karl Engel
  • Patent number: 10036324
    Abstract: A turbine exhaust case frame (100) comprises an inner ring (104), an outer ring (102), and a plurality of load-bearing struts (106). The inner ring is configured to carry a load from inner bearings. The outer ring has installation bosses (116) with downward-facing mount surfaces (120). The load-bearing struts connect the inner ring to the outer ring.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: July 31, 2018
    Assignee: United Technologies Corporation
    Inventors: Jonathan Ariel Scott, John J. Henderson, Ralph D. Harris
  • Patent number: 10036277
    Abstract: A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connected to the metal part by an axial connection and a second fixing portion connected to the composite part by an axial connection, the connecting element including an axially extending free end; and a rigid locking element including a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the connecting element to limit deformation of the connecting element while the engine is in operation.
    Type: Grant
    Filed: June 12, 2013
    Date of Patent: July 31, 2018
    Assignee: SNECMA
    Inventors: Antoine Jean-Philippe Beaujard, Jacques Rene Bart
  • Patent number: 10030582
    Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.
    Type: Grant
    Filed: February 9, 2015
    Date of Patent: July 24, 2018
    Assignee: United Technologies Corporation
    Inventors: Kevin Zacchera, Matthew Andrew Hough, Jonathan Lemoine, Christopher Treat, Alberto A. Mateo
  • Patent number: 10030523
    Abstract: An article for gas turbine engine includes a body that has a gaspath side for exposure in a core gaspath of a gas turbine engine. The gaspath side has an undulating surface. A cooling passage is in the body. The cooling passage has a undulating profile that corresponds to the undulating surface.
    Type: Grant
    Filed: February 13, 2015
    Date of Patent: July 24, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: San Quach, Tracy A. Propheter-Hinckley, Steven Bruce Gautschi
  • Patent number: 10018068
    Abstract: A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 1 herein, wherein the Cartesian coordinates are provided with respect to a point P which is at the center of an arc W and co-planer with a machined surface V. A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 2 herein, wherein the Cartesian coordinates are provided with respect to a point P? which is at the center of an arc W? and co-planer with a machined surface V?.
    Type: Grant
    Filed: January 13, 2015
    Date of Patent: July 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter J. Milligan, Paul M. Lutjen, Ken F. Blaney, Thurman C. Dabbs, Kevin J. Ryan
  • Patent number: 10012147
    Abstract: An engine and particle decelerator is provided herein. The engine having: an inlet opening for directing air towards a compressor of the engine; and a particle decelerator located between the inlet opening and the compressor such that air travelling towards the compressor from the inlet opening must travel through the particle decelerator and wherein an area of the particle decelerator is greater than an inlet and an outlet of the particle decelerator.
    Type: Grant
    Filed: August 17, 2015
    Date of Patent: July 3, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Hoyt Y. Chang, Shayan Ahmadian
  • Patent number: 10012100
    Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track. The blade track includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend through the carrier to couple the annular runner with the carrier.
    Type: Grant
    Filed: January 6, 2016
    Date of Patent: July 3, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Jun Shi, Jeffrey A. Walston, Aaron D. Sippel
  • Patent number: 9995217
    Abstract: Disclosed is a gas turbine engine including a compressor section in communication with a bleed flow path. A rotary valve is provided in communication with the bleed flow path to selectively regulate a flow of fluid within the bleed flow path.
    Type: Grant
    Filed: February 3, 2014
    Date of Patent: June 12, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Enzo DiBenedetto
  • Patent number: 9988922
    Abstract: An impingement baffle for a gas turbine engine is provided. The impingement baffle is a one piece impingement ring with one opening and with fastening elements at both free ends of the impingement ring to enable the closing of the impingement ring. A gas turbine engine including at least one such an impingement baffle is also provided.
    Type: Grant
    Filed: September 16, 2010
    Date of Patent: June 5, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Johan Friis
  • Patent number: 9988909
    Abstract: A turbocharger including a wheel having suction surfaces and hub surfaces contoured to reduce secondary flow. The suction surfaces are radially contoured with a sinusoidal component, and further have a chamfered edge at the shroud edge. The hub end-walls are contoured both streamwise and cross-stream with sinusoidal components.
    Type: Grant
    Filed: April 25, 2011
    Date of Patent: June 5, 2018
    Assignee: Honeywell International, Inc.
    Inventor: Cheng Xu
  • Patent number: 9988928
    Abstract: System and methods for predicting a turbomachine engine safe start clearance following a shutdown of the turbomachine engine is provided. The system includes a controller operatively connected to a plurality of temperature detecting means (TDM). The TDMs are arranged at an upper and lower part of the engine casing, and are configured to sense parameters of the engine and to transmit the sensed parameters to the controller. The controller is configured to receive the sensed parameters and to determine, via a control application of the controller, whether components of the engine have sufficient clearance. The controller is further configured to transmit the clearance information, e.g., to a user. Based on the clearance information, the turbomachine engine is restarted.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: June 5, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Cristina C. Popescu, Michael J. Olejarski, Timothy E. Mazzotta
  • Patent number: 9982560
    Abstract: An airfoil platform includes a platform body having an arcuate base defining a centerline axis. A rail extends radially outboard from a side of the arcuate base. A feed orifice is defined at least partially in the rail. The inner diameter edge of an axially facing opening of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body and forming the feed orifice through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.
    Type: Grant
    Filed: January 16, 2015
    Date of Patent: May 29, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Mark A. Boeke, Kristopher K. Anderson, Jeffrey J. De Gray, Jeffrey R. Levine, Sarah Riley, Richard M. Salzillo, Jr.
  • Patent number: 9982598
    Abstract: A variable bleed valve includes a variable bleed valve door disposed in a bleed inlet in transition duct and rotatable about an axis at or near a forward end of door. Valve is operable to open and close a bleed slot open to a booster bleed flowpath located outwardly of transition duct and having an airflow restrictor. Airflow restrictor may be variable such as a flapper valve. Booster bleed flowpath may pass through a bifurcated bleed duct including an inner passage radially bound by spaced apart inner and middle bleed walls and an outer passage radially bound by middle bleed wall and an outer bleed wall. Airflow restrictor may include an outlet area smaller than an inlet area of inner passage. Door seals against middle bleed wall to open inner passage and against outer bleed wall to open both passages.
    Type: Grant
    Filed: October 22, 2012
    Date of Patent: May 29, 2018
    Assignee: General Electric Company
    Inventors: Byron Andrew Pritchard, Jr., Charles Daniel Califf, Peter John Wood, Raymond Gust Holm, Allan George van de Wall, Peter Alfred Pezzi
  • Patent number: 9970452
    Abstract: Embodiments of a forward-swept impeller are provide, as are embodiments of a gas turbine engine containing a forward-swept impeller. In one embodiment, the gas turbine engine includes a shaft and a forward-swept impeller mounted to the shaft. The forward-swept impeller includes, in turn, an inboard impeller section, an outboard impeller section circumscribing the inboard impeller section, and a plurality of hub flow paths extending over the forward-swept impeller from the inboard impeller section to the outboard impeller section. The plurality of hub flow paths each have a flow path exit that is tilted in a forward direction, as taken along a line tangent to the flow path exit.
    Type: Grant
    Filed: February 17, 2015
    Date of Patent: May 15, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Richard David Conner, Michael Todd Barton, Yoseph Gebre-Giorgis, Harry Lester Kington, John Repp
  • Patent number: 9963993
    Abstract: A turbine ring of a turbomachine is described, having a one-piece ring structure which has an outer ring which is continuous in the circumferential direction of the turbine ring and has a fastening section for fastening the turbine ring on a housing section of the turbomachine, an inner ring which is segmented in the circumferential direction and has a plurality of inner ring segments which are mutually displaceable in the circumferential direction for guiding the hot gas and has front sealing segments and rear sealing segments, as seen in the axial direction of the turbine ring, these sealing segments being spaced a distance apart from one another in the axial direction and extending between the inner ring and the outer ring, as well as a turbomachine having such a turbine ring.
    Type: Grant
    Filed: October 29, 2013
    Date of Patent: May 8, 2018
    Assignee: MTU Aero Engines AG
    Inventor: Manfred Feldmann
  • Patent number: 9963996
    Abstract: A shroud cooling system configured to cool a shroud adjacent to an airfoil within a gas turbine engine is disclosed. The turbine engine shroud may be formed from shroud segments that include a plurality of cooling air supply channels extending through a forward shroud support for impingement of cooling air onto an outer radial surface of the shroud segment with respect to the inner turbine section of the turbine engine. The channels may extend at various angles to increase cooling efficiency. The backside surface may also include various cooling enhancement components configured to assist in directing, dispersing, concentrating, or distributing cooling air impinged thereon from the channels to provide enhanced cooling at the backside surface. The shroud cooling system may be used to slow down the thermal response by isolating a turbine vane carrier from the cooling fluids while still providing efficient cooling to the shroud.
    Type: Grant
    Filed: August 22, 2014
    Date of Patent: May 8, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Darryl Eng, Christopher Rawlings, Thomas Pechette, Friedrich T. Rogers, Jae Y. Um, Ching-Pang Lee
  • Patent number: 9957900
    Abstract: One embodiment of the present discloses includes a system. The system includes a turbine and a fluid supply system. The turbine includes a main flow path, a plurality of turbine blades disposed along the main flow path, at least one flow control area disposed along the main flow path, and at least one fluid injection port fluidly coupled to the main flow path. The fluid supply system is fluidly coupled to the at least one fluid injection port, wherein the fluid supply system is configured to supply a fluid to the at least one fluid injection port to adjust an effective area of the at least one flow control area.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: May 1, 2018
    Assignee: General Electric Company
    Inventors: Mehdi Milani Baladi, Edward Michael Yanosik, Jr., Richard Bradford Hook, Jr., Scott Edward Farley, Gordon Jeffery Follin
  • Patent number: 9957829
    Abstract: A method of setting a clearance between a rotor and a stator of a rotor assembly for a turbine engine. The rotor assembly has a plurality of rotor-to-stator stages and the stator has a nominal centerline. Typically the stator is a casing or an array of vane tips. The method includes (i) correlating in-service rotor-to-stator rub patterns for a rotor-to-stator stage of a number of turbine engines, (ii) setting a position of a machining centerline relative to the nominal centerline of the stator, the position being towards a heavy rub, (iii) machining the stator about the machining centerline, (iv) repeating steps (i) to (ii) for each rotor-to-stator stage of the plurality of the rotor-to-stator stages, wherein the machined stator having been formed by at least two machining steps having different center-lines.
    Type: Grant
    Filed: May 12, 2014
    Date of Patent: May 1, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventor: Andrew Shepherd
  • Patent number: 9952117
    Abstract: Methods for determining strain on turbine components include providing a turbine component comprising a plurality of strain sensor reference features disposed along the turbine component separated from one another by a plurality of first distances at a first time, reading the plurality of strain sensor reference features at a second time to determine a plurality of second distances between the plurality of strain sensor reference features, and comparing the plurality of second distances to the plurality of first distances to determine a plurality of non-linear strain measurements between the plurality of strain sensor reference features.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: April 24, 2018
    Assignee: General Electric Company
    Inventors: Gregory Lee Hovis, John David Ward, Jr., William Farris Ranson
  • Patent number: 9951634
    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body having circumferential sides between a forward face and an aft face, each of the circumferential sides defining a mate face, an attachment member extending from the body, and a transition member adjacent to the body and the attachment member. The transition member and the body define a slot configured to receive a seal member. The transition member is sloped inwardly from one of the circumferential sides. A method of fabricating a gas turbine engine component is also disclosed.
    Type: Grant
    Filed: June 11, 2015
    Date of Patent: April 24, 2018
    Assignee: United Technologies Corporation
    Inventors: Carson A. Roy Thill, Russell E. Keene, Paul M. Lutjen
  • Patent number: 9945244
    Abstract: A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, and a biasing apparatus. The biasing apparatus is arranged and disposed to bias the inner shroud in a direction away from the hot gas path, loading the inner shroud to the outer shroud. In another embodiment, the biasing apparatus is a springless biasing apparatus including at least one bellows, at least one thrust piston, or a combination of at least one bellows and at least one thrust piston. A method for loading the turbine shroud assembly is disclosed including biasing the inner shroud having a surface adjacent to a hot gas path in a direction away from the hot gas path toward the outer shroud, wherein biasing the inner shroud includes a biasing force exerted by the biasing apparatus.
    Type: Grant
    Filed: August 13, 2015
    Date of Patent: April 17, 2018
    Assignee: General Electric Company
    Inventors: Frederic Woodrow Roberts, Victor John Morgan, Matthew Troy Hafner
  • Patent number: 9945247
    Abstract: An anti-icing system for an engine section stator of a gas turbine engine. The system includes an environmental control system pre-cooler heat exchange system and a conduit. The environmental control system pre-cooler heat exchange system is configured to exchange heat between air bled from a compressor of the engine and bypass duct air. The conduit is configured to exchange heat from the pre-cooler heat exchange system to a heat transfer medium. The conduit is also configured to transfer the heat from the heat transfer medium to the engine section stator.
    Type: Grant
    Filed: July 30, 2015
    Date of Patent: April 17, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Ajith Appukuttan, Benjamin Keeler, Paolo Vanacore
  • Patent number: 9938904
    Abstract: A device and methods are provided for controlling a gas turbine engine based at least in part on real-time detection of spatially resolved temperature distributions of a turbine engine components. In one embodiment, a method includes detecting surface temperature of one or more blade elements, by an thermal probe, in a plurality of radial locations of an airfoil row to determine real-time spatially resolved surface temperature data for the one or more blade elements of the airfoil row, and controlling the engine based on the real-time spatially resolved surface temperature data.
    Type: Grant
    Filed: December 16, 2014
    Date of Patent: April 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas N. Slavens, Jr., Charles W. Halderman
  • Patent number: 9938846
    Abstract: A turbine shroud for a gas turbine engine includes a plurality of shroud segments arranged around a central axis. Each shroud segment includes a carrier component, a blade track component, and a retainer component that couples the blade track component to the carrier component. The turbine shroud further includes a plurality of circumferential seals that seal circumferential interfaces between the shroud segments.
    Type: Grant
    Filed: June 10, 2015
    Date of Patent: April 10, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Aaron D. Sippel
  • Patent number: 9932857
    Abstract: A bypass engine bearing holder (1) that holds an upstream bearing (6) and defines, with said upstream bearing, an oil chamber (100) and an air chamber (200), comprising a frusto-conical portion (11) defining an upstream bearing chamber (160) and a downstream inner chamber (150), and includes an outer collar (13) connected, by a weld (135), to a flange (15) that extends outward from the frusto-conical portion (11). The outer collar (13) has a sealable gimlet (131) engaging with the upstream bearing (6) such as to seal the oil chamber (100). The bearing holder (1) includes a plurality of oil recovery ducts (8) leading to the downstream inner chamber (150) and to the upstream bearing chamber (160). The oil recovery ducts (8) lead to the upstream bearing chamber (160), downstream from the weld (135) of the outer collar (13) on the flange (15), the weld (135) of the outer collar (13) being axisymmetric.
    Type: Grant
    Filed: November 18, 2014
    Date of Patent: April 3, 2018
    Assignee: SNECMA
    Inventors: Frederic Noel, Benoit Argemiro Matthieu Debray, Mario Cesar De Sousa, Gregory Ghosarossian-Prillieux, Nicolas Pommier
  • Patent number: 9920656
    Abstract: A barrier coating for isolating a metallic support component from a composite component in a gas turbine engine is provided. The barrier coating may be applied to the metallic support component so that when the ceramic component is mounted on the metallic support component the barrier coating is engaged.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: March 20, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: Sean E. Landwehr, Sungbo Shim, Adam L. Chamberlain, Ann Bolcavage
  • Patent number: 9915204
    Abstract: Systems and methods are disclosed herein for distributing cooling air in gas turbine engines. A tangential on board injector (“TOBI”) may supply cooling air to a turbine section of a gas turbine engine. The cooling air may be split into a first cooling air path and a second cooling air path. The first cooling air path may fluidly connect the TOBI and the interior of a first stage rotor blade. The second cooling air path may fluidly connect the TOBI and a cavity. The cavity may be located between a first disk and a second disk. The cooling air paths from a single cooling air source may thermally isolate portions of the turbine section.
    Type: Grant
    Filed: April 1, 2015
    Date of Patent: March 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, James D. Hill