With Safety Device Patents (Class 60/39.091)
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Patent number: 7934367Abstract: A device for detecting breakage of a gas turbine engine shaft and for reducing the rotational speed of the turbine includes a rotor of a turbine or of a first stage turbine driving the shaft. The rotor has a turbine disk with a rim. A stator that the rotor rotates inside or a nozzle guide vanes assembly of the first turbine stage is provided. A temperature sensor is positioned on the stator or on the nozzle guide vanes assembly, immediately downstream of the rim. The sensor is located to sense temperature on a portion of the stator that contacts the rotor, or on a portion of the nozzle guide vanes assembly that contacts the first stage rotor, in the event of shaft breakage. An engine fuel control member connects to the sensor and can interrupt fuel supply to the engine, when the sensor emits a signal above a predetermined threshold.Type: GrantFiled: October 19, 2007Date of Patent: May 3, 2011Assignee: SNECMAInventor: Claude Marcel Mons
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Patent number: 7918081Abstract: A gas turbine engine includes an engine casing concentrically disposed around the following: a low pressure compressor; a turbine; and a high pressure compressor having at least one bleed tube and at least one joint proximate to the engine casing; and at least one flame prevention device adapted to cover at least a portion of at least one gas turbine engine component.Type: GrantFiled: December 19, 2006Date of Patent: April 5, 2011Assignee: United Technologies CorporationInventors: Kevin W. Schlichting, Donn R. Blankenship, Melvin Freling, Michael J. Maloney
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Publication number: 20110067378Abstract: A separator device is provided for separating dirt particles from a flow of cooling air fed to airfoils of the turbine section of a gas turbine engine. In use the separator device extends across a conduit which bypasses the combustor of the engine to convey pressurised cooling air carrying dirt particles from the compressor section of the engine to openings which direct the air into the airfoils. The separator device is configured to direct a first portion of the impinging cooling air flow away from the openings and to allow a second portion of the impinging cooling air to continue to the openings. The first portion of cooling air has a higher concentration of the coarsest dirt particles carried by the cooling air than the second portion of cooling air.Type: ApplicationFiled: September 7, 2010Publication date: March 24, 2011Applicant: ROLLS-ROYCE PLCInventors: Ian TIBBOTT, Dougal Jackson
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Patent number: 7902999Abstract: A system and method of at least reducing the likelihood of a rotor lock in an aircraft gas turbine engine is provided. A determination is made that each propulsion gas turbine engine on an aircraft has experienced a flameout. The rotational speed of each propulsion gas turbine engine is compared to a predetermined threshold rotational speed and, if the rotational speed of each propulsion gas turbine engine is below the predetermined threshold rotational speed, a warning is supplied to a flight crew.Type: GrantFiled: April 18, 2008Date of Patent: March 8, 2011Assignee: Honeywell International Inc.Inventor: Chris D. Eick
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Publication number: 20110023448Abstract: A driving device for a motor 15 is disclosed, the device including an inertia wheel 16, a free wheel 18 able to ensure a unidirectional automatic clutching on a torque reversal between the inertia wheel and the shaft 12 of the motor, and a run up device 20 for the inertia wheel. The driving device is mounted on the end of shaft 12 of the motor opposite to the end for coupling the motor to mechanical equipment driven by the motor 15.Type: ApplicationFiled: July 25, 2008Publication date: February 3, 2011Inventor: Daniel Livernais
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Patent number: 7874136Abstract: 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: April 27, 2006Date of Patent: January 25, 2011Assignee: Pratt & Whitney Canada Corp.Inventor: Jeffrey Bernard Heyerman
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Publication number: 20110011054Abstract: A combustor casing with an inner casing and an outer casing and a bimetallic element arranged on an inner side of the inner casing is provided. The inner casing includes a pre-chamber area, where combustion is initiated in a fuel rich state, with an upper end and a lower end, the upper end sized and configured to be connected to a burner head. The bimetallic element is located within the pre-chamber area.Type: ApplicationFiled: February 25, 2009Publication date: January 20, 2011Inventors: Ghenadie Bulat, Peter Senior
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Publication number: 20110000183Abstract: An assembly for the removal of contaminants from a contact zone between respective contact surfaces 6, 8 of a first component 2 and a second component 4. At least one of the contact surfaces has a low friction element 10 provided with grooves 12 which extend through the contact zone such that, in operation, a pressure difference across the contact zone causes contaminants entering the grooves 12 to be expelled along the grooves 12 from the contact zone.Type: ApplicationFiled: June 24, 2010Publication date: January 6, 2011Applicant: ROLLS-ROYCE PLCInventors: Stephen J. DIMELOW, Ian C.D. Care
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Patent number: 7841163Abstract: A turbine engine emergency power system includes low and high pressure spools, the lower pressure spool including a low pressure compressor. A turbofan is coupled to the low pressure spool. The turbofan drives the low pressure spool in a windmill condition in which the low pressure turbine fails to provide rotational drive to the turbofan. A generator is rotationally driven by the low pressure spool in the windmill condition. A gear train is used to increase the speed of the generator in one example. In one example embodiment, a centrifugal clutch is used to selectively decouple the generator from the low pressure spool at a predetermined engine speed, which corresponds to normal operating speeds when the turbine engine is under power.Type: GrantFiled: November 13, 2006Date of Patent: November 30, 2010Assignees: Hamilton Sundstrand Corporation, Pratt & Whitney Canada Corp.Inventors: Richard C. Welch, Gerard H. Bueche, William T. DeGroff, Jose Albero, Jerzy Makuszewski
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Publication number: 20100287906Abstract: A fiber-optic dynamic sensing module comprises a support member, a beam extending from the support member, and a pre-strained fiber Bragg grating sensor and a strain-free fiber Bragg grating sensor mounted on the beam. The pre-strained and strain-free fiber Bragg grating sensors each comprise a Bragg grating inscribed in a fiber. The Bragg grating of the pre-strained fiber Bragg grating sensor is packaged more tightly along a longitudinal direction of the beam than the Bragg grating of the strain-free fiber Bragg grating sensor.Type: ApplicationFiled: May 14, 2009Publication date: November 18, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Hua Xia, Kevin Thomas McCarthy, Jeffrey Scott Goldmeer, Ertan Yilmaz, Ted Carlton Kreutz, Clayton Ming Young, Russell Stephen Demuth, Hunt Adams Sutherland
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Publication number: 20100287907Abstract: An example method of estimating a gas turbine engine surge margin and surge margin deterioration includes monitoring debris in at least a portion of an engine and establishing an estimated surge margin for the engine using information from the monitoring The method may use gas path parameters, such as pressures, temperatures, and speeds to establish the estimated surge margin. An example gas turbine engine surge margin assessment system includes a debris monitoring system configured to monitor debris moving through a portion of an engine, and a controller programmed to execute an engine deterioration model that establishes an estimated surge margin and loss in surge margin of the engine based on information from the debris monitoring system.Type: ApplicationFiled: May 18, 2009Publication date: November 18, 2010Inventors: Rajendra K. AGRAWAL, Ravi RAJAMANI, William F. SCHNEIDER, Coy Bruce WOOD
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Publication number: 20100281843Abstract: In certain embodiments, a system includes a controller configured to obtain an inter-stage pressure measurement between stages of a multi-stage compressor. The controller is also configured to identify actual damage in the multi-stage compressor based at least in part on the inter-stage pressure measurement.Type: ApplicationFiled: May 7, 2009Publication date: November 11, 2010Applicant: General Electric CompanyInventor: Raub Warfield Smith
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Patent number: 7827780Abstract: A protocol for assembling a fuel shut off pin valve assembly for a turbo fan engine. The protocol outlines a specific sequence of events in order to ensure failsafe incorporation of a fuel shut off valve assembly within the low pressure turbine area and specifically within the engine casing of the turbo fan.Type: GrantFiled: November 15, 2006Date of Patent: November 9, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Guy Lefebvre, Claude Giardetti
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Publication number: 20100275573Abstract: A combustor of a turbine engine having a combustion zone defined therein is provided and includes a fuel nozzle, including two or more burners, each of the burners having a passage defined therein through which combustible materials are permitted to travel toward the combustion zone, a plurality of sensors disposed in relative association with each of the burners to respectively sense static pressures within the passages of each of the burners and to respectively issue sensed static pressure signals accordingly, and a controller, coupled to the sensors and receptive of the signals, which is configured to determine from an analysis of the signals whether any of the burners are associated with a flashback risk and to mitigate the flashback risk in accordance with the determination.Type: ApplicationFiled: April 30, 2009Publication date: November 4, 2010Applicant: GENERAL ELECTRIC COMPANYInventor: Garth Curtis Frederick
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Publication number: 20100275574Abstract: In one embodiment, a system includes a rotary machine including a casing, a shaft extending through the casing, and multiple blades coupled to the shaft inside the casing. The system also includes a plug disposed in an opening in the casing, wherein the plug includes a filler coupled to a base, and the filler is configured to break away upon impact with the blades.Type: ApplicationFiled: April 30, 2009Publication date: November 4, 2010Applicant: General Electric CompanyInventor: Anil Salunkhe
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Publication number: 20100257867Abstract: A device and method for monitoring a high-pressure pump in a turbomachine fuel supply circuit by detecting opening of a pressurizing and shut-off valve mounted on an outlet side of a fuel flow regulating valve, by measuring rotational speed of the turbomachine corresponding to the opening of the pressurizing and cut-off valve, and by monitoring change in a value of the rotational speed to propose replacement of the high-pressure pump when the measure value rotational speed reaches a predetermined threshold.Type: ApplicationFiled: November 18, 2008Publication date: October 14, 2010Applicant: SNECMAInventors: Christian Aurousseau, Jonathan Benitah, Xavier Flandrois, Jean-Remi Masse, Mickael Sauzedde, Franck Godel, Julien Maille
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Publication number: 20100257838Abstract: A method for monitoring the health of a turbine is provided. The method comprises monitoring a turbine engine having a plurality of engine modules and determining one or more health estimates, which may included trended data, for one or more of the engine modules, based on a plurality of engine parameters. The method further determining and transmitting appropriate notifications that indicate repairs to be made to the turbine engine.Type: ApplicationFiled: April 9, 2009Publication date: October 14, 2010Applicant: General Electric CompanyInventors: Maria Cecilia Mazzaro, Michael Evans Graham, Harry Kirk Mathews, JR., Kevin Thomas McCarthy, Donald Bleasdale, Dhiraj Arora, Mohammad Waseem Adhami, Adriana Elizabeth Trejo
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Publication number: 20100251688Abstract: A containment system for a gas turbine engine comprises a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine. The force absorbing arrangement circumferentially surrounds a major proportion of the axial length of the engine.Type: ApplicationFiled: January 10, 2007Publication date: October 7, 2010Applicant: ROLLS-ROYCE PLCInventor: Kenneth F. Udall
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Patent number: 7806364Abstract: A containment system for a gas turbine engine comprises a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine. The force absorbing arrangement circumferentially surrounds a major proportion of the axial length of the engine.Type: GrantFiled: January 10, 2007Date of Patent: October 5, 2010Assignee: Rolls-Royce PLCInventor: Kenneth F Udall
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Patent number: 7802433Abstract: A method for operating a gas turbine engine including a compressor is provided. The method includes defining a predetermined concentration, placing at least one sensor in an inlet of the gas turbine engine, detecting a sand and dust concentration value using the at least one sensor; and deploying a boot to facilitate preventing particles from entering the compressor when the sand and dust concentration value equals or exceeds the predetermined concentration. The boot includes a plurality of fluid exit slots such that clean air is facilitated to be adhered to a flow path surface downstream from the boot.Type: GrantFiled: September 27, 2006Date of Patent: September 28, 2010Assignee: General Electric CompanyInventor: Timothy J. Higgins
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Patent number: 7788895Abstract: When a temperature of cooling steam being measured by a temperature-measuring device 13 in one combustor 2-x among combustors 2-1 through 2-8 is confirmed to be higher than a temperature of a predetermined time before by a predetermined value and temperatures of cooling steams being measured by temperature-measuring devices 13 in combustors 2-y and 2-z being adjacent to the combustor 2-x on both sides are confirmed to be lower than a temperature of a predetermined time before by a predetermined value, an occurrence of a flashback is detected in the combustor 2-x.Type: GrantFiled: July 5, 2006Date of Patent: September 7, 2010Assignee: Mitsubishi Heavy Industries, Ltd.Inventor: Kentaro Fujii
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Publication number: 20100205928Abstract: A system for detecting onset of a stall in a rotor is disclosed, the system comprising a sensor spaced radially outwardly and apart from tips of a circumferential row of blades at a location on a static component that is between a first location and a second location wherein the first location is at a first distance of about 25% blade tip-chord length axially forward from the leading edge of a blade and the second location is at a second distance of about 25% blade tip-chord length axially aft from the trailing edge of a blade and wherein the sensor is capable of generating an input signal corresponding to a flow parameter at a location near the tip of a blade and indicative of the onset of a stall and a correlation processor that generates a stability correlation signal.Type: ApplicationFiled: April 23, 2010Publication date: August 19, 2010Inventors: CURTIS W. MOECKEL, Aspi Wadia, David S. Clark, Andrew Breeze-Stringfellow
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Publication number: 20100199628Abstract: An impingement shield assembly for a turbine includes a first impingement shield portion and a second impingement shield joined to the first impingement shield portion. The assembly also includes a first connection portion formed on the first impingement shield portion, a second connection portion formed on the first impingement shield portion and first and second wedge weld portions that mate with and hold the first and a second connection portions in a fixed relationship to one another.Type: ApplicationFiled: February 6, 2009Publication date: August 12, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Jonathan Dwight Berry, Timur Rustemovich Repikov, Heath Michael Ostebee
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Patent number: 7770375Abstract: A material having a plurality of impurity collection spaces has an outer face facing into a cooling air flow stream for a gas turbine engine component. Impurities such as sand or dirt will collect in the plurality of spaces. In a disclosed embodiment, a honeycombed material is utilized. The material may have a surface that will sit with at least a component parallel to an axial centerline of a gas turbine engine that is to receive the collection material. The material surface may also have a component which is generally perpendicular to the axial centerline. The material may be placed in a gas turbine engine upstream of the turbine section, and downstream of the combustion section. Moreover, the collection material may be placed such that there is cleaner air flow radially inwardly of the collection material, and heavier dirt-laden air passing along the collection material such that impurities can be collected.Type: GrantFiled: February 9, 2006Date of Patent: August 10, 2010Assignee: United Technologies CorporationInventors: Ioannis Alvanos, Bernard A. Andrews, Robert A. Charbonneau, Susan M. Tholen, Thurman Carlo Dabbs, Michael J. Bruskotter
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Patent number: 7762082Abstract: An apparatus and method is disclosed for recovering a flammable vapor emanating from a vent of a tank. The apparatus comprises an input conduit for connecting to the vent of the tank. An input manifold connects the input conduit to an input of a compressor with an output manifold connecting an output of the compressor to an input of a storage tank. An output conduit connects an output of the storage tank to the turbine generator for generating electrical power by burning the flammable vapor. An electrical connector directs electrical power from the turbine generator to drive the apparatus as well as to supply surplus power to an external load.Type: GrantFiled: September 23, 2004Date of Patent: July 27, 2010Assignee: IES Consulting Inc.Inventors: James William Knight, Donald Edward Haynes, Jr.
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Patent number: 7762084Abstract: A system for actively controlling the working line location within a low pressure compressor. The system includes a plurality of variable inlet guide vanes that are adjusted to maintain the working line at a constant level as the low pressure compressor rotates at a constant speed.Type: GrantFiled: November 11, 2005Date of Patent: July 27, 2010Assignee: Rolls-Royce Canada, Ltd.Inventors: Dan Martis, Arthur Rowe
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Patent number: 7757776Abstract: Reactive fire suppression transport agents may be used to release catalytic fire suppression agents, in reaction zones, which may then be transported by naturally occurring flows paths downstream to the vicinity of flame holding regions for fire suppression for example, in aircraft. The reactive fire suppression agents may be delivered in projectiles.Type: GrantFiled: January 12, 2006Date of Patent: July 20, 2010Assignee: Eclipse Aerospace, Inc.Inventors: Peter D. Haaland, Ken Harness
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Patent number: 7757474Abstract: A gas turbine has a plurality of combustors in a toroidal arrangement to provide combustion gases to turbine blades, thereby rotating the turbine body. Thermocouples, the number of which is the same as or greater than the number of the combustors, are arranged toroidally at the outlets of the turbine blades and measure the temperatures of the combustion gases at the respective outlets. During the operation of the gas turbine, if an abnormality, such as misfire or fuel injection nozzle obstruction, occurs in one or more of the combustors, the resulting change in gas temperature triggers a signal to stop, and thereby protect the gas turbine. Based on the measured values of the blade pass temperatures of the thermocouples and set threshold temperatures, a fuel supply system may be caused to gradually decrease the fuel supplied to the combustors to bring the gas turbine body to an automatic stop, or it may be cut off instantaneously, thus immediately stopping the gas turbine.Type: GrantFiled: November 26, 2004Date of Patent: July 20, 2010Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Satoshi Tanaka, Toshimitsu Morimoto, Shouichi Nagata, Kozo Toyama
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Publication number: 20100170217Abstract: 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: ApplicationFiled: January 8, 2009Publication date: July 8, 2010Applicant: 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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Patent number: 7743599Abstract: A method of monitoring and controlling the combustion dynamics of a gas turbine engine system is provided. The system includes at least one gas turbine that includes at least one combustor can. The method includes receiving a signal from a gas turbine engine sensor that is indicative of combustion dynamics in at least one of the combustor cans, processing the received signal to determine a probability of lean blowout for at least one combustor can, and controlling the gas turbine engine system to facilitate reducing a probability of a lean blowout (LBO) event using the determined probability of lean blowout.Type: GrantFiled: July 17, 2007Date of Patent: June 29, 2010Assignee: General Electric CompanyInventors: Avinash Vipayak Taware, Minesh Ashok Shah, Ajai Singh, Willy Steve Ziminsky, Pingchuan Wu
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Patent number: 7735310Abstract: A gas turbine, such as an aircraft engine, has at least one compressor, at least one turbine, a combustion chamber, and a fuel pump to supply fuel to the combustion chamber. Upon identification of a break of a shaft that couples a compressor with a turbine, the gas turbine is shut off. For this purpose, at least one electrical current conductor is arranged on the shaft, whereby this current conductor is a component of a current supply for the fuel pump or for a fuel pump regulation. When the integrity of the current conductor is disrupted, thereby the current supply of the fuel pump or of the fuel pump regulation is interrupted in order to automatically shut off the gas turbine.Type: GrantFiled: September 17, 2005Date of Patent: June 15, 2010Assignee: MTU Aero Engines GmbHInventor: Martin Metscher
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Patent number: 7734443Abstract: Systems and methods for prediction of gas turbine trips due to component failures such as thermocouple failures. Exemplary embodiments include prediction of gas turbine trips due to component failures, including collecting raw gas turbine operational data and using the raw gas turbine operational data to generate a prognostic indicator for the prediction of a turbine trip due to the failed thermocouples.Type: GrantFiled: August 23, 2007Date of Patent: June 8, 2010Assignee: General Electric CompanyInventors: Soumen De, Ravi Yoganatha Babu, Viany Bhaskar Jammu, Achalesh Kumar Pandey, Richard John Rucigay
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Patent number: 7726951Abstract: A fuel control system is provided in a single compact modular unit. The unit includes a motor driving a highly accurate cam-operated double-acting piston metering pump, both of which are contained in a liquid fuel environment. As the liquid fuel is pumped it works to cool internal components including the motor. An electronic motor drive is contained in a dry chamber of the unit for controlling operation of the motor and pump and is cooled indirectly by the fuel as well. A pressure sensitive flow divider is also included for selectively providing one or multiple output fuel flow paths depending upon whether a pressure threshold is reached, for example to send fuel to primary and secondary burner nozzles. Filter, filter bypass, pressure relief, and fuel shut-off components are also integrated into the single modular unit.Type: GrantFiled: June 20, 2005Date of Patent: June 1, 2010Assignee: Jansen's Aircraft Systems Controls, Inc.Inventors: Harvey B. Jansen, John F. Calleja, Raymond A. Forrester, Jr.
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Patent number: 7726409Abstract: Non-reactive test agents may be used to test fire suppression systems in which reactive fire suppression agents may be used to release catalytic fire suppression agents for transport by naturally occurring flows paths downstream to the vicinity of flame holding regions for fire suppression for example, in aircraft.Type: GrantFiled: June 29, 2006Date of Patent: June 1, 2010Assignee: Eclipse Aerospace, Inc.Inventors: Peter D. Haaland, Ken Harness
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Patent number: 7721553Abstract: A method and apparatus for detecting a flashback condition in a fuel nozzle (8) of a gas turbine (10) are provided. The fuel nozzle is configured to pass a flow of air (20) to be mixed with a fuel in a premixing zone (11). The apparatus includes at least one fuel injecting device (12) positioned to define a point of fuel injection in the premixing zone. The apparatus further includes an electrode (16) positioned upstream of the point of fuel injection. The electrode is adapted to sense a flashback condition that can occur in the premixing zone.Type: GrantFiled: July 18, 2006Date of Patent: May 25, 2010Assignee: Siemens Energy, Inc.Inventors: Sean A. Miller, Ramarao V. Bandaru
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Patent number: 7712299Abstract: An anti-bogdown control system monitors and regulates operation of a turbine and a compressor to prevent underspeed trip of the turbine while avoiding surge of the compressor. A turbine speed controller receives a turbine speed signal and a turbine temperature signal, generates a surge margin setpoint, and regulates overfiring of the turbine. A surge margin controller associated with the compressor receives the surge margin setpoint from the turbine speed controller and receives a load signal from one or more sensors and modulates a compressor throttle valve so that the compressor operates at a surge margin that is approximately equal to the surge margin setpoint. In a system with multiple compressors driven by a single turbine, a surge margin controller is associated with each compressor.Type: GrantFiled: September 5, 2006Date of Patent: May 11, 2010Assignee: ConocoPhillips CompanyInventors: John R. Wolflick, Megan V. Evans, Jaleel Valappil, Bobby D. Martinez, Marc Bellomy
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Publication number: 20100101205Abstract: A protective device for treating at least one piece of debris that comes from a source of an aircraft, in particular a compressor stage or a turbine stage of an aircraft power plant, and to prevent it from reaching a target of the aircraft, characterized in that it has a geometry and a position relative to the source and to the target that make it possible to deflect the debris with the most energy so as to protect the target that is placed in a predefined protected zone.Type: ApplicationFiled: March 28, 2008Publication date: April 29, 2010Applicant: AIRBUS FRANCEInventors: Gilles Weyland, Bernadette Dulay, David Hardy
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Patent number: 7703270Abstract: A mistake proof cable assembly for promoting short time engine assembly and method of assembling same. The mistake proof cable assembly comprises a slotted member defining a slot having an open end, and a cable connected to the slotted member and extending longitudinally through the slot. First and second restrainers are mounted on the cable on opposite sides of the slotted member for limiting free movement of the cable in the longitudinal direction of the slotted member. A lock prevents removal of the cable from the slot through the open end thereof.Type: GrantFiled: July 15, 2005Date of Patent: April 27, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Guy Lefebvre, Eric Durocher
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Publication number: 20100077721Abstract: A turbofan engine which has a composite fan case surrounding a fan with a plurality of fan blades is disclosed. The composite fan case includes a containment zone having an inner fabric layer composed of resin-impregnated fibres substantially uni-axially oriented in a common angular direction corresponding to a blade release angle of the fan blades. The fan case also includes a composite outer shell and an energy absorbing core disposed radially between the inner fabric layer and the composite outer shell. The energy absorbing core includes non resin impregnated multidirectional fibres.Type: ApplicationFiled: September 26, 2008Publication date: April 1, 2010Inventor: Andrew R. MARSHALL
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Patent number: 7681402Abstract: A gas turbine engine comprising an oil system and a gearbox, the gearbox is driven by at least one engine shaft, the oil system comprises a pump drivingly connected to the gearbox, an oil tank connected to the pump via a supply pipe and a delivery pipe connecting the pump to the engine for delivery of oil thereto, an anti-siphon pipe is connected between the tank and the delivery pipe to provide an excess oil flow to the engine characterized in that the anti-siphon pipe includes a variable flow valve for regulating the flow of oil passing therethrough such that at low engine speeds an adequate supply of oil is provided to a sight glass in the tank.Type: GrantFiled: September 12, 2005Date of Patent: March 23, 2010Assignee: Rolls-Royce plcInventors: Clare D Champion, Philippe Christol
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Publication number: 20100024431Abstract: A method of detecting a partial flame failure in a gas turbine is provided. The method includes a gas duct to guide a propulsion gas and several combustors, each combustor leads into the gas duct and includes a burner. The method includes measuring a first temperature over time at each of at least two probing points located downstream from the combustors in the gas duct, measuring a second temperature over time in each of at least two of the burners, and detecting a partial flame failure from the first temperature measurements and the second temperature measurements, wherein the detecting of a partial flame failure includes determining a first detection parameter, the first detection parameter is determined from a rate of change of a variation between the first temperature measurements at different probing points. A gas turbine including temperature sensors to detect a partial flame failure is also provided.Type: ApplicationFiled: January 28, 2008Publication date: February 4, 2010Inventor: Vili Panov
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Patent number: 7654093Abstract: A method of adjusting a triggering clearance and a trigger wherein the triggering clearance can be readily adjusted directly on the assembly line by selectively fixing an axial adjustive position between first and second triggering members.Type: GrantFiled: September 26, 2005Date of Patent: February 2, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Guy Lefebvre, John Walter Pietrobon
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Publication number: 20090313966Abstract: A controller for a turbine power plant that is operable to identify a failure condition and measure a shutoff valve performance.Type: ApplicationFiled: June 11, 2008Publication date: December 24, 2009Inventors: Ruurd A. Vanderleest, Stuart S. Hay
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Publication number: 20090312930Abstract: A stall prediction apparatus of an axial compressor provided with: a rotor provided with a plurality of rotor blades; and a cylindrical casing facing the rotor blades and provided so as to cover the outer circumference of the rotor, comprising: pressure sensors provided in equal numbers at a plurality of locations in a circumferential direction of an inner wall surface of the casing, an index calculator for calculating an index (stall risk index) for evaluating the stall risk based on time-series data detected by each of the pressure sensors, and a signal processor for predicting the stall occurrence based on the stall risk indexes obtained corresponding to said each of the pressure sensors. In accordance with the present invention, it is possible to obtain a stall risk index which is highly accurate (supersensitive) and stable necessary for the active stall control, and to realize an engine control system with high reliability.Type: ApplicationFiled: May 18, 2007Publication date: December 17, 2009Inventors: Tomofumi Nakakita, Takashi Tomiyama, Fumitaka Takemura
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Publication number: 20090301055Abstract: Gas turbine engine systems and methods involving vibration monitoring are provided. In this regard, a representative vibration monitoring method for a gas turbine engine includes: receiving information corresponding to detected vibrations of a gas turbine engine; isolating vibrations attributable to rotating blades of the gas turbine engine from the detected vibrations; and comparing the isolated vibrations to information corresponding to predicted vibrations of the rotating blades.Type: ApplicationFiled: June 4, 2008Publication date: December 10, 2009Applicant: UNITED TECHNOLOGIES CORP.Inventor: Pattada A. Kallappa
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Publication number: 20090293447Abstract: A method provides fire protection for titanium components of an aircraft gas turbine. To enable the use of titanium components on aircraft gas turbines without the risk of titanium fire, a surface-near, nonflammable, intermetallic phase of titanium and at least one further metal, selected from the group of aluminum, nickel, vanadium and chromium, including combinations thereof, is produced in the surface of the component by a diffusion process.Type: ApplicationFiled: April 16, 2009Publication date: December 3, 2009Inventors: Dan Roth-Fagaraseanu, Moritz Wirth
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Publication number: 20090277153Abstract: A composite component such as a fan casing liner panel for a gas turbine engine comprises an abradable layer and a layer. The layer is provided with a septum layer, to which the abradable layer is bonded. The septum layer is perforated by holes, which enable air to be extracted from the region between the septum layer and the abradable layer during the process of bonding the components together, for example by a vacuum bonding process.Type: ApplicationFiled: April 1, 2009Publication date: November 12, 2009Applicant: ROLLS-ROYCE PLCInventors: Cedric B. Harper, Neil Humphries
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Patent number: 7596938Abstract: A turbomachine front portion includes an internal support shroud for the fan outlet guide vanes, and a flow splitter fairing from which a primary duct and a secondary duct originate. The front portion includes at least one deflector system configured to prevent/limit the ingress of hailstones inside the primary duct, the system including at least one deflecting surface together with an actuator for moving the surface from a retracted position to a deployed position for deflecting the hailstones, the system being mounted on the shroud such that, in the deployed position, a downstream end of the surface is situated upstream of the splitter fairing.Type: GrantFiled: March 18, 2008Date of Patent: October 6, 2009Assignee: SNECMAInventors: Jacques Rene Bart, Laurent Behaghel, Stephane Rousselin
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Publication number: 20090241508Abstract: 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: March 31, 2008Publication date: October 1, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Lewis Berkley Davis, JR., Stanley Kevin Widener, John Wilber
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Publication number: 20090235670Abstract: The invention relates to a bleed air supply system and a safety device for closing a valve in at least one of the several bleed air supply lines depending on an alarm signal that indicates an opening in at least one of the several bleed air supply lines. To stop the supply of bleed air irrespective of the type of the bleed air source, the safety device comprises a filter device for generating the alarm signal depending on the ground connection signal and on an opening signal from an opening signal device that indicates any opening of the bleed air supply line that is connected to the high-pressure ground connection.Type: ApplicationFiled: October 17, 2006Publication date: September 24, 2009Inventors: Norbert Rostek, Jürgen Rehbock