With Safety Device Patents (Class 60/39.091)
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Publication number: 20130152600Abstract: A method to detect shaft break includes monitoring first and second parameters and defining a two-dimensional parameter space that is a function of the first and second parameters, the two-dimensional parameter space includes integration regions. The method also includes defining an integration function for each integration region. For measured values of the first and second parameters, the method determines the applicable integration region and applies the integration function to the first parameter to give an integration result; and then sets a shaft break signal to TRUE when the integration result exceeds a predetermined threshold. The present invention also provides a shaft break detection system.Type: ApplicationFiled: October 23, 2012Publication date: June 20, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20130133306Abstract: Starter control valve failure prediction machines, systems, computer readable media, program products, and computer implemented methods to predict and trend starter control valve failures in gas turbine engines using a starter control valve health prognostic and to make predictions of starter control valve failures, are provided.Type: ApplicationFiled: January 24, 2013Publication date: May 30, 2013Applicant: LOCKHEED MARTIN CORPORATIONInventor: LOCKHEED MARTIN CORPORATION
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Publication number: 20130133333Abstract: The present invention provides a method of detecting shaft break in a shaft system comprising a shaft coupled between two masses. The method comprises a number of steps. Firstly, to define a time-dependent rotational speed equation for the shaft in terms of system inertia for an engine transient event. Then to discretize the rotational speed equation in terms of a discrete time constant in the discrete domain. Then to recursively define the discretized equation to give a recursive equation and to solve the recursive equation to determine the discrete time constant. Then to define a threshold as a function of engine power and then to set a shaft break signal to TRUE if the discrete time constant is greater than the threshold. A shaft break detection system is also provided by the present invention.Type: ApplicationFiled: November 2, 2012Publication date: May 30, 2013Applicant: ROLLS-ROYCE PLCInventor: Rolls-Royce PLC
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Patent number: 8439297Abstract: The present invention relates to an air inlet (10) for a turbine engine (2) of an aircraft (1), the air inlet comprising an air delivery duct (20) defined by a side wall (21) and extended by a dynamic inlet duct (30), said dynamic inlet duct (30) extending along a dynamic axis (AX1) towards a front flow section (31), said dynamic inlet duct (30) being provided with a grid (40) for protection against ingesting foreign bodies. The grid (40) is suitable for moving in translation along said dynamic axis (AX1) relative to said front flow section (31), and said air inlet (10) includes at least one lateral inlet (50) arranged in said side wall (21) and cover means (41) for covering said lateral inlet (50) that are movable relative to said lateral inlet (50), said air inlet (10) including movement means (60) controlled by said movement in translation of the grid (40) to request movement of said cover means (41) relative to said lateral inlet (50).Type: GrantFiled: November 8, 2010Date of Patent: May 14, 2013Assignee: EurocopterInventors: Marc Colaprisco, Victor Gerin-Roze
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Publication number: 20130111872Abstract: An aircraft gas turbine engine has first and second electrical harnesses formed from respective first and second flexible printed circuit boards which each provides a plurality of spaced conductive tracks. The conductive tracks carry signal types which either (i) provide engine control and can cause hazardous engine conditions in the event of their failure, (ii) detect or prevent hazardous conditions of the engine, or (iii) are not of type (i) and/or of type (ii). The first flexible printed circuit board provides all the conductive tracks which carry signals of type (i) or the first flexible printed circuit board provides all the conductive tracks which carry signals of type (ii). The second flexible printed circuit board provides all the remaining conductive tracks. The first electrical harness is fire-resistant for a period of five minutes without any exposure of its conductive tracks so that the conductive tracks can carry their signals.Type: ApplicationFiled: October 24, 2012Publication date: May 9, 2013Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Patent number: 8434291Abstract: A system may detect a flame about a fuel nozzle of a gas turbine. The gas turbine may have a compressor and a combustor. The system may include a first pressure sensor, a second pressure sensor, and a transducer. The first pressure sensor may detect a first pressure upstream of the fuel nozzle. The second pressure sensor may detect a second pressure downstream of the fuel nozzle. The transducer may be operable to detect a pressure difference between the first pressure sensor and the second pressure sensor.Type: GrantFiled: January 8, 2009Date of Patent: May 7, 2013Assignee: General Electric CompanyInventors: Gilbert Otto Kraemer, James Michael Storey, John Lipinski, Julio Enrique Mestroni, David Lee Williamson, Jason Randolph Marshall, Anthony Krull
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Publication number: 20130104517Abstract: A component for a gas turbine engine is provided. The component includes a cooling aperture and a plug filling at least a portion of the cooling aperture to prevent airflow through the cooling aperture. The plug is configured to melt at a predetermined temperature during operation of the gas turbine engine to permit airflow through the cooling aperture.Type: ApplicationFiled: October 31, 2011Publication date: May 2, 2013Inventors: Victor Hugo Silva Correia, Robert Francis Manning
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Publication number: 20130067882Abstract: A bleed air duct joint insulation means is disclosed in which a leak vent comprises valve means.Type: ApplicationFiled: September 12, 2012Publication date: March 21, 2013Applicant: AIRBUS OPERATIONS LIMITEDInventor: Nicholas WEST
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Publication number: 20130061599Abstract: Cooling flow recirculation in fuel manifolds, such as fuel manifolds associated with gas turbine engines is disclosed. An example system for jet pump driven recirculation of manifold cooling flow according to at least some aspects of the present disclosure may include a flow split valve having a spool valve disposed therein, the flow split valve having a pilot manifold and a main manifold attached thereto; a jet pump fluidically coupled to the pilot manifold, the jet pump being arranged to drive recirculation of a cooling flow through the main manifold via a cooling flow circuit in a pilot only mode of operation; and/or a fuel nozzle in fluid communication with the pilot manifold and the main manifold.Type: ApplicationFiled: June 14, 2012Publication date: March 14, 2013Applicant: GENERAL ELECTRIC COMPANYInventor: Frederick Ehrwulf VAN ALEN
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Patent number: 8393160Abstract: A mixture of air and fuel is compressed in a compressor of a gas turbine system. The gas turbine system includes components that define one or more fuel leak locations, and leaked fuel is directed from the one or more leak locations to a reaction chamber of the gas turbine system. At least a portion of the leaked fuel is oxidized in the reaction chamber. The energy released by oxidation of the leaked fuel can be converted to mechanical motion.Type: GrantFiled: October 17, 2008Date of Patent: March 12, 2013Assignee: Flex Power Generation, Inc.Inventor: Edan Prabhu
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Patent number: 8387950Abstract: A flow device adapted to operate as a restrictor as well as provide a pressure relief capability in the event of an over-pressurization event within a fluid system containing the device. The flow device includes an expandable orifice that has an outer perimeter, a plurality of cantilevered tabs surrounded by the outer perimeter, and an opening surrounded and defined by the tabs. The tabs project from the outer perimeter toward the opening, which restricts flow of the bleed air through the expandable orifice at a pressure below a predetermined pressure level, but then expands to relieve an over-pressure condition of the bleed air at a pressure above the predetermined pressure level as a result of the cantilevered tabs being deflected by the over-pressure condition. The device is adaptable for use in aircraft applications, including the regulation of bleed air used in anti-icing/de-icing systems.Type: GrantFiled: April 6, 2011Date of Patent: March 5, 2013Assignee: General Electric CompanyInventors: Daniel Scott Hummel, Daniel Jean-Louis Laborie, Bradley James Holtsclaw
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Patent number: 8370046Abstract: A system for monitoring a gas turbine includes a memory containing information from comparable gas turbines and an input device that generates a unit data signal and a risk signal. A processor in communication with the memory and the input device incorporates the unit data signal into the database, projects information for the gas turbine, and calculates a conditional risk that the gas turbine will reach a limit. An output signal includes repair or maintenance schedules. A method for monitoring a gas turbine includes receiving information from comparable gas turbines, adding information from the gas turbine to the information from comparable gas turbines, and projecting information for the gas turbine. The method further includes calculating a conditional risk that the gas turbine will reach a limit and generating an output signal containing repair or maintenance schedules.Type: GrantFiled: February 11, 2010Date of Patent: February 5, 2013Assignee: General Electric CompanyInventors: Xiaomo Jiang, Michael Edward Bernard, Sameer Vittal
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Patent number: 8359870Abstract: A flame-holding control method in a gas turbine having a combustor can and a fuel nozzle disposed in the combustor can. The method can include performing a first scheduled injection of a diluent stream into the nozzle, checking to see if a time period has exceeded a time threshold and in response to the time period being greater than that the time threshold, performing a second scheduled injection of the diluent stream into the nozzle.Type: GrantFiled: May 12, 2009Date of Patent: January 29, 2013Assignee: General Electric CompanyInventors: Robert Thomas Thatcher, Joel Meador Hall, Andrew Mitchell Rodwell
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Patent number: 8353150Abstract: A nozzle is provided and includes an outer annulus defined by an exterior wall and an interior wall and including air inlets through which air flows to a fuel mixing zone and a combustion zone, an inner annulus disposed within the interior wall and including a fuel volume into which fuel is fed to a distal end thereof, which is adjacent to and isolated from the combustion zone and an airflow line, disposed between the fuel volume and the interior wall, through which air flows to the combustion zone with the airflow line and the combustion zone isolated from the fuel volume, and a fuse configured to melt during a flameholding incident and to form a breach through which fuel flows from the fuel volume, bypassing the fuel mixing zone, to a fuel burning zone downstream from the fuel mixing zone.Type: GrantFiled: June 7, 2012Date of Patent: January 15, 2013Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Stanley Kevin Widener, John Wilbur
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Publication number: 20120324906Abstract: A heat and/or fire protection assembly for a component, the assembly comprising: a plurality of protrusions distributed about a surface of the component, the protrusions protruding with respect to the surface of the component; the protrusions comprising a barrier material, the barrier material being arranged and configured to form a first protective layer under the action of heat, the first protective layer being arranged to protect the component from the heat.Type: ApplicationFiled: June 11, 2012Publication date: December 27, 2012Applicant: ROLLS-ROYCE PLCInventors: Alec R. GROOM, Philip A. BRAZIL
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Patent number: 8328504Abstract: A gas turbine engine has a nacelle, a plurality of pipes and a drains assembly, the drains assembly including a drains mast that extends through the nacelle and provides an outlet for the pipes. The engine is characterised in that drains assembly has a connection block defining internal passages and is arranged to connect between the pipes and the drains mast. The connection block also has lateral connections to the pipes enabling the nacelle to have a lower profile; thereby reducing aerodynamic drag.Type: GrantFiled: January 8, 2008Date of Patent: December 11, 2012Assignee: Rolls-Royce PLCInventor: Michael Edwin Russell
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Patent number: 8322145Abstract: Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.Type: GrantFiled: April 23, 2009Date of Patent: December 4, 2012Assignee: General Electric CompanyInventors: David August Snider, Harold Lamar Jordan, Jr., Timothy Andrew Healy, John David Stampfli
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Patent number: 8297036Abstract: A controller for a turbine power plant that is operable to identify a failure condition and measure a shutoff valve performance.Type: GrantFiled: June 11, 2008Date of Patent: October 30, 2012Assignee: United Technologies CorporationInventors: Ruurd A. Vanderleest, Stuart S. Hay
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Patent number: 8291688Abstract: A nozzle is provided and includes an outer annulus defined by an exterior wall and an interior wall and including air inlets through which air flows to a fuel mixing zone and a combustion zone, an inner annulus disposed within the interior wall and including a fuel volume into which fuel is fed to a distal end thereof, which is adjacent to and isolated from the combustion zone and an airflow line, disposed between the fuel volume and the interior wall, through which air flows to the combustion zone with the airflow line and the combustion zone isolated from the fuel volume, and a fuse configured to melt during a flameholding incident and to form a breach through which fuel flows from the fuel volume, bypassing the fuel mixing zone, to a fuel burning zone downstream from the fuel mixing zone.Type: GrantFiled: March 31, 2008Date of Patent: October 23, 2012Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Stanley Kevin Widener, John Wilbur
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Publication number: 20120247115Abstract: In a method for operating a gas compressor which compresses gas whose supply conditions change and which is equipped with an intake-flow regulating mechanism, a limit pressure ratio that defines the operational upper limit of the pressure ratio relative to the intake flow rate of the gas compressor or the degree of opening of the intake-flow regulating mechanism to prevent surging in the gas compressor is corrected by multiplying a reference limit pressure ratio calculated from the design conditions of the gas compressor by a first correction factor calculated depending on a detected operating-state value of the gas compressor.Type: ApplicationFiled: October 7, 2011Publication date: October 4, 2012Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Jun Sasahara, Masamitsu Okuzono
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Publication number: 20120247081Abstract: A nozzle is provided and includes an outer annulus defined by an exterior wall and an interior wall and including air inlets through which air flows to a fuel mixing zone and a combustion zone, an inner annulus disposed within the interior wall and including a fuel volume into which fuel is fed to a distal end thereof, which is adjacent to and isolated from the combustion zone and an airflow line, disposed between the fuel volume and the interior wall, through which air flows to the combustion zone with the airflow line and the combustion zone isolated from the fuel volume, and a fuse configured to melt during a flameholding incident and to form a breach through which fuel flows from the fuel volume, bypassing the fuel mixing zone, to a fuel burning zone downstream from the fuel mixing zone.Type: ApplicationFiled: June 7, 2012Publication date: October 4, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Lewis Berkley Davis, JR., Stanley Kevin Widener, John Wilber
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Patent number: 8272201Abstract: Means for cooling a bearing assembly supporting a rotor stage of a gas turbine engine after engine shutdown. The engine comprises a combustion section, a compressor for the delivery of air to the combustion section, and a bearing assembly supporting a rotor stage. The means for cooling a bearing assembly comprises a means operable to generate a signal representative of turbine duct temperature immediately prior to engine shutdown, a means for determining the duration for cooling after engine shutdown as a function of the signal representative of turbine duct temperature, and the compressor operable as a cooling means to deliver cooling air to the rotor stage after engine shutdown. Thereby the amount of heat conducted to the bearing assembly is limited such that the temperature of the bearing assembly is limited to below a predetermined temperature.Type: GrantFiled: February 14, 2008Date of Patent: September 25, 2012Assignee: Rolls-Royce PLCInventors: Lee Skelton, John Ingle, Andrew Gwynne, Clary Susanne I. Svensdotter
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Patent number: 8272223Abstract: A twin-shaft gas turbine 1, which has a gas generator 2 including a compressor 7, a combustor 8, and a high-pressure turbine 9, is configured to make a first control mode and a second control mode selectively useable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.Type: GrantFiled: December 28, 2010Date of Patent: September 25, 2012Assignee: Hitachi, Ltd.Inventors: Kenji Nanataki, Nozomi Saito, Hidetaro Murata
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Patent number: 8261527Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.Type: GrantFiled: January 31, 2012Date of Patent: September 11, 2012Assignee: United Technologies CorporationInventors: Ethan K. Stearns, Jorn A. Glahn, Daniel J. McKaveney
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Publication number: 20120210694Abstract: A turbo machine includes a spool. A microwave detection system is configured to detect a spool parameter associated with the spool. A controller is in communication with the microwave position sensing system and is programmed to determine a spool condition, such as shaft torque and/or shear in response to the spool parameter.Type: ApplicationFiled: April 11, 2007Publication date: August 23, 2012Inventor: Eric B. Holmquist
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Publication number: 20120204572Abstract: The invention proposes a method for determining the capacity of an aircraft pump to deliver a predetermined fuel flow rate, characterised in that it comprises a step of rotating the pump at a predetermined speed; a step of supplying at least one cylinder with the totality of the fuel coming out of the pump; a step of determining the fuel flow rate supplying said cylinder, and a diagnostic step which consists in determining whether the pump is able to supply a sufficient flow rate as a function of the determined value of the flow rate supplying the cylinder. The invention also proposes a device implementing the method.Type: ApplicationFiled: February 14, 2012Publication date: August 16, 2012Applicant: SNECMAInventor: Nicolas Alain BADER
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Patent number: 8240120Abstract: Systems and methods involving vibration management of gas turbine engines are provided. In this regard, a representative method includes: detecting vibrations of a gas turbine engine; automatically adjusting rotational speed of a component of the gas turbine engine in order to attempt to reduce the vibrations to within predefined vibration limits; and automatically adjusting operating parameters of the gas turbine engine such that, if the vibrations are reduced to within the predefined vibration limits, thrust of the gas turbine engine is set to an amount of thrust corresponding to the amount of thrust provided prior to the adjusting of the rotational speed of the component.Type: GrantFiled: October 25, 2007Date of Patent: August 14, 2012Assignee: United Technologies CorporationInventors: Robert D. Southwick, Joseph P. Pascuitti
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Patent number: 8234875Abstract: A fuel system for a turbine engine is provided. The fuel system includes a positive displacement pump driven by an electric motor. The pump is rotated in a first direction to deliver fuel to the turbine engine, and a second direction for evacuating fuel from the turbine engine. A shut-off check valve is open in a first direction in response to a first differential pressure created by the pump in the first direction. The shut-off check valve is biased to a closed position when the pump is rotating in the second direction. An ecology check valve is biased to a closed position in the first direction and open in the second direction in response to a second differential pressure created by the pump. The check valves open and close automatically in response to the pressures generated by the positive displacement pump in each of the first and second rotational directions. In this manner, simple, reliable valves are utilized to regulate the flow of fuel in the fuel system.Type: GrantFiled: August 5, 2011Date of Patent: August 7, 2012Assignee: Hamilton Sundstrand CorporationInventors: Charles H. Falke, Leo J. Veilleux, Douglas A. Parsons
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Patent number: 8196414Abstract: A twin-shaft gas turbine 1, which has a gas generator 2 including a compressor 7, a combustor 8, and a high-pressure turbine 9, is configured to make a first control mode and a second control mode selectively usable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.Type: GrantFiled: June 29, 2009Date of Patent: June 12, 2012Assignee: Hitachi, Ltd.Inventors: Kenji Nanataki, Nozomi Saito, Hidetaro Murata
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Patent number: 8186168Abstract: A method of at least partially balancing axial thrust loads and an engine in which the method is carried out is disclosed herein. The engine includes a combustion chamber and a fuel system operable to direct pressurized fuel to the combustion chamber. The engine also includes a rotor operable to rotate about a centerline axis and subjected to axial thrust loads during operation. The engine also includes a balance piston engaged with the rotor. The balance piston includes a pressure face positioned in a thrust cavity. The engine also includes a fluid passageway extending between the fuel system and the thrust cavity. Pressurized fuel is delivered to the pressure face to counteract axial thrust loads on the rotor.Type: GrantFiled: July 18, 2008Date of Patent: May 29, 2012Assignee: Rolls-Royce CorporationInventor: Craig Heathco
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Publication number: 20120119021Abstract: One embodiment of the present invention is a unique aircraft. Another embodiment is a unique propulsion system for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and aircraft propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: ApplicationFiled: November 16, 2010Publication date: May 17, 2012Inventors: Donald Burns, Kaushik Rajashekara
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Publication number: 20120102966Abstract: An operation control method for a gas turbine comprising the steps of: making a molten salt map in a liquid phase state by calculating a dew point and a solidus temperature of molten salt for causing high-temperature corrosion on high-temperature components of the turbine due to impurities using a thermodynamic equilibrium calculation on the basis of the impurities contained in low-quality fuel and operation data of the gas turbine, indicating a surface temperature and a pressure of the high-temperature components of the turbine on the molten salt map to determine a superposition state thereof on a region of molten salt in a liquid phase, predicting a lifetime of the high-temperature components of the gas turbine by estimating a corrosion rate thereof, and controlling the flow rate of the low-quality fuel supplied to a combustor on the basis of the prediction of the lifetime of the high-temperature components so that an area of surface temperature and pressure regions of the high-temperature components superpType: ApplicationFiled: July 7, 2009Publication date: May 3, 2012Inventors: Hiroshi Haruyama, Hideki Tamaki, Yoshitaka Kojima, Hironori Kamoshida
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Publication number: 20120102912Abstract: A containment case for a turbine engine having a plurality of blades rotating therein has a first plurality of metallic layers each of the first plurality of layers being resistant to penetration of fragments therethrough and a second plurality of metallic layers, each of the second plurality of layers absorbing kinetic energy of fragments striking said second plurality of layers.Type: ApplicationFiled: October 27, 2010Publication date: May 3, 2012Inventors: Said Izadi, Bohdan Skarzynski
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Patent number: 8166746Abstract: A containment system for containing fragments of a burst rotor including first and second means for frangibly connecting a containment element to first and second walls, the first and second means rupturing upon being subjected to a load mainly produced by a translational motion of at least one fragment impacting the element.Type: GrantFiled: November 23, 2010Date of Patent: May 1, 2012Assignee: Pratt & Whitney Canada Corp.Inventor: Jeffrey Bernard Heyerman
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Patent number: 8161727Abstract: A device for, in a gas turbine engine, braking a turbine including a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking is disclosed. The device includes a first braking member provided with at least one abrasive element and a second braking member including a ring-shaped element (120A) made of a material capable of being eroded by the abrasive element. One of the two braking members being secured to the rotor and the other of the two braking members being secured to the stator. The braking members come into contact with one another through axial displacement of the rotor once the shaft has broken. The abrasive element of the first braking member eroding the ring-shaped element of the second braking member.Type: GrantFiled: May 23, 2008Date of Patent: April 24, 2012Assignee: SNECMAInventors: Jacques Rene Bart, Didier Rene Andre Escure, Claude Marcel Mons, Stephane Rousselin
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Patent number: 8151573Abstract: Methods and apparatus are provided for detecting a flameout of an operating turbomachine that is configured to receive a controlled flow of bleed air from a bleed air source and a controlled flow of fuel from a fuel source. A value of an operational parameter within the turbomachine is detected and a determination is made as to whether it has varied by a predetermined amount. If the operational parameter has varied by the predetermined amount, a flameout confirmation test is triggered. The flameout confirmation test includes holding the controlled flow of bleed air constant, commanding an increase in turbomachine speed, and confirming that a flameout has occurred by detecting that the controlled fuel flow to the turbomachine is at a maximum fuel flow limit and that actual turbomachine speed differs from the commanded turbomachine speed by a predetermined speed error.Type: GrantFiled: November 6, 2008Date of Patent: April 10, 2012Assignee: Honeywell International Inc.Inventors: Matthew Christopher, Hanif Vhora
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Patent number: 8127525Abstract: A device for, in a gas turbine engine, braking a turbine including a rotor, having at least one disk with a rim driving a shaft and capable of rotating with respect to a stator, is disclosed. The device is for the event of the shaft breaking and includes a first braking member, secured to the rim and provided with at least one cutting element, and a second braking member secured to the stator downstream of the rim and including a ring-shaped element made of a material that can be cut by the cutting element. The two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken. The cutting element of the first braking member cuts the ring-shaped element of the second braking member.Type: GrantFiled: May 23, 2008Date of Patent: March 6, 2012Assignee: SNECMAInventors: Jacques Rene Bart, Didier Rene Andre Escure, Claude Marcel Mons, Stephane Rousselin
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Patent number: 8127524Abstract: A fuel system for a turbine engine is provided. The fuel system includes a positive displacement pump driven by an electric motor. The pump is rotated in a first direction to deliver fuel to the turbine engine, and a second direction for evacuating fuel from the turbine engine. A shut-off check valve is open in a first direction in response to a first differential pressure created by the pump in the first direction. The shut-off check valve is biased to a closed position when the pump is rotating in the second direction. An ecology check valve is biased to a closed position in the first direction and open in the second direction in response to a second differential pressure created by the pump. The check valves open and close automatically in response to the pressures generated by the positive displacement pump in each of the first and second rotational directions. In this manner, simple, reliable valves are utilized to regulate the flow of fuel in the fuel system.Type: GrantFiled: January 10, 2007Date of Patent: March 6, 2012Assignee: Hamilton Sundstrand CorporationInventors: Charles H. Falke, Leo J. Veilleux, Douglas A. Parsons
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Patent number: 8117820Abstract: A jet engine intake deflector system for preventing foreign objects from entering the intake of a jet engine. The jet engine intake deflector system generally includes an air intake frame, a plurality of fins and a deflection member. The air intake frame is generally comprised of a plurality of laterally extending outer supports arranged at equidistance from each other in a substantially circular configuration around a center support. Each fin is generally comprised of a flat plate, wherein a front end of each fin is attached to the deflection member and a rear end of each fin is attached to the air intake frame. The free end of the air intake frame is generally welded directly onto a jet engine to protect its intake from foreign objects, such as birds. Upon striking a foreign object, the deflector member will direct the foreign object out and away from the jet engine intake.Type: GrantFiled: May 26, 2009Date of Patent: February 21, 2012Inventor: Edward V. Briscoe
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Publication number: 20120036860Abstract: A gas turbine plant is provided with exhaust gas recirculation and includes a main gas turbine having a main compressor and main turbine driving a main generator, and a combustion chamber, with an outlet connected to the inlet of the main gas turbine, has a fuel feed, and via the recuperator's high-pressure side obtains combustion air from the main gas turbine's compressor outlet. The outlet of the main turbine and the inlet of the main compressor are connected via the recuperator's low-pressure side and a cooler for exhaust gas recirculation. On the recuperator's low-pressure side, a charging unit, with a compressor and a turbine is arranged, and draws in air via an air intake and by the outlet of its compressor is connected to the recuperator's low-pressure side outlet and by the inlet of its turbine is connected to a surplus-gas extraction line on the recuperator's low-pressure side.Type: ApplicationFiled: April 26, 2011Publication date: February 16, 2012Applicant: ALSTOM TECHNOLOGY LTDInventors: Hans WETTSTEIN, Manfred WIRSUM, Steffen SCHULZ
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Publication number: 20120031068Abstract: A compressed air supply system for routing compressed air from a compressor to at least one combustor of a gas turbine engine is disclosed. The compressed air supply system may be formed from one or more plenums having an upstream end in fluid communication with an inner chamber of the compressor in which air is compressed and having a downstream end in fluid communication with the at least one combustor. Channeling compressed air through the plenum reduces damage to other components by confining the compressed air within the plenum. An upstream end of the plenum may be sealed to at least a portion of the compressor, and a downstream end of the plenum may be sealed to at least a portion of one or more combustors.Type: ApplicationFiled: August 9, 2010Publication date: February 9, 2012Inventor: Richard Charron
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Publication number: 20120023894Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for monitoring corrosion or corrosive contaminants associated with liquid fuel. According to an example embodiment of the invention, a method is provided for monitoring and predicting corrosion. The method can include monitoring corrosion or corrosive contaminants associated with liquid fuel in a fuel supply system of a gas turbine, predicting, based at least in part on the monitoring, a cumulative level of corrosion of one or more components associated with a gas turbine, and outputting information associated with the monitoring.Type: ApplicationFiled: July 28, 2010Publication date: February 2, 2012Applicant: GENERAL ELECTRIC COMPANYInventor: Paul Joseph Martin
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Publication number: 20120006035Abstract: An air turbine starter includes an air turbine starter rotor rotatably located at a central axis. The rotor includes a plurality of aerodynamic surfaces extending from a platform. At least one cutting element is located in the air turbine starter such that travel of the rotor along the central axis during operation of the air turbine starter results in removal of the platform and aerodynamic surfaces from the rotor via contact between the at least one cutting element and the rotor.Type: ApplicationFiled: July 7, 2010Publication date: January 12, 2012Applicant: Hamilton Sundstrand CorporationInventors: Jeffrey M. Makulec, Matthew Gorajski, Matthew Slayter
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Publication number: 20110308229Abstract: An impeller for use in a containment structure has a hub, a blade attaching to the hub for compressing air as the blade rotates with the hub, and an annulus disposed about the hub whereby the annulus reduces an effect of the hub breaking apart such that a weight of the containment structure is reduced.Type: ApplicationFiled: June 18, 2010Publication date: December 22, 2011Inventor: Behzad Hagshenas
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Publication number: 20110296810Abstract: A method, system and computer program product for life management and monitoring of a high temperature gas turbine including components having a thermal barrier coating is disclosed. The method, system and computer program product uses design, monitoring and diagnostics, and inspection data to determine the cumulative damage and remaining useful life of gas turbine components and unit risk and classification probability to determine thermal barrier coating damage probability, remaining useful life, and inspection recommendations.Type: ApplicationFiled: June 7, 2010Publication date: December 8, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Canan Uslu HARDWICKE, Subrat Nmn NANDA, Achalesh Kumar PANDEY, Sameer VITTAL, Jagmeet SINGH
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Publication number: 20110257864Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for detecting failure in gas turbine hardware. According to an example embodiment of the invention, a method for detecting a failure in a gas turbine is provided. The method can include monitoring a parameter associated with the turbine, wherein the monitored parameter comprises at least one turbine bucket temperature, detecting an event associated with operation of the turbine, wherein the event is based at least in part on the monitored parameter, and initiating shutdown of the turbine upon detection of the event wherein the monitored parameter is above a predetermined value for at least a predetermined time duration.Type: ApplicationFiled: April 15, 2010Publication date: October 20, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Justin V. John, Nirm Velumylum Nirmalan, John Charles Intile, Scott William Szepek, Daniel Joseph Peczka, Bradley Steven Carey
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Publication number: 20110203251Abstract: An elongate fireseal having two ends joined by a longitudinal axis. The fireseal comprises at least two portions having D-shaped cross section and adjacent portions share a common dividing wall. Each end of the fireseal is configured to interlock with a complementary opposite end of the same or a further fireseal.Type: ApplicationFiled: January 19, 2011Publication date: August 25, 2011Applicant: ROLLS-ROYCE PLCInventors: Harold G. MAYES, Andrew J. MULLENDER, Graeme C. HUNT, Paul R. ADLINGTON
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Publication number: 20110154801Abstract: A fan containment system for a gas turbine engine, and a method of making the same, is disclosed that in one embodiment includes casing that surrounds at least a portion of a plurality of fan blades. In one form, a pair of standoff rings is formed in an outer surface of the casing that are spaced apart from one another a predetermined distance running circumferentially about the inner nacelle ring. A containment ring is positioned around a radially outer surface of the standoff rings to form an interference fit between the two.Type: ApplicationFiled: July 20, 2010Publication date: June 30, 2011Inventor: Vance A. Mahan
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Publication number: 20110138769Abstract: A fan section of a gas turbine engine having an axially extending centerline is provided. The fan section includes a fan assembly, a fan containment case, and a plurality of structural exit guide vanes. The fan assembly includes a fan rotor hub centered on and rotatable about the centerline, and a plurality of fan blades that are attached to and extend radially out from the fan rotor hub. The fan containment case is disposed radially outside of and circumferentially around the fan assembly. The fan containment case includes a shell and an integral flange ring that extends around the circumference of the shell, a circumferentially extending blade outer air seal disposed between the fan blades and the shell. The structural exit guide vanes are mechanically attached to the fan containment case at a position aligned with the integral flange ring.Type: ApplicationFiled: December 11, 2009Publication date: June 16, 2011Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Mark W. Costa, Darin S. Lussier
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Publication number: 20110126508Abstract: A fan is disclosed herein. The fan includes a shaft rotatable about an axis. The fan also includes a blade engaged with the shaft for rotation about the axis. The fan also includes a case encircling the axis. The case is positioned radially outward of the blade and the shaft. The fan also includes a blanket mounted to the case. The case and the blanket are operable to cooperate with one another to prevent the blade from escaping the case upon the blade separating from the shaft. The blanket is at least partially impregnated with shear thickening fluid.Type: ApplicationFiled: December 1, 2009Publication date: June 2, 2011Inventor: EDWARD CLAUDE RICE