Having Bleed Air To Cool Or Heat Motor Or Component Thereof (e.g., Active Clearance Control, Etc.) Patents (Class 60/782)
-
Patent number: 8210801Abstract: A method operates a gas turbine that includes a compressor section, a turbine section and an extraction cooling system. The method includes monitoring an operation of the gas turbine, directing a cooling air flow through the extraction cooling system from the compressor section to the turbine section in response to normal operation of the gas turbine, and directing a warming air flow through the extraction cooling system to the compressor section and the turbine section in response to shutdown of the gas turbine.Type: GrantFiled: January 29, 2009Date of Patent: July 3, 2012Assignee: General Electric CompanyInventors: Henry G. Ballard, Jr., Ian David Wilson, Stephen Christopher Chieco, Andrew Ray Kneeland, Bradley James Miller, Kenneth David Black, Raymond Goetze
-
Publication number: 20120159961Abstract: A gas turbine engine having a heat exchanger is disclosed. In one form the gas turbine engine includes a particle separator that can be used to separate particles or foreign objects and create a dirty flow and a clean flow. A blower can be used to discharge the particles or foreign objects from the separator. The heat exchanger includes a relatively warm flow path from a downstream region of a compressor and a relatively cool flow path from an upstream region of the compressor. The relatively cool flow path is merged with the dirty flow. In another embodiment, the gas turbine engine is a turbofan and the relatively cool flow path is merged with a bypass flow. In one embodiment of the engine the relatively warm flow path, after having exchanged heat with the relatively cool flow path is delivered to a working component without passing through a turbomachinery component.Type: ApplicationFiled: December 23, 2011Publication date: June 28, 2012Inventors: Michael Stephen Krautheim, Carlos Soto-Gonzalez
-
Publication number: 20120137703Abstract: A method is provided for operating an air-staged diffusion nozzle for a gas turbine combustor to cool the nozzle tip and improve mixing of gas fuel and air within a downstream burner space. Air is mixed with the gas-fuel in an outer swirler and expanded in a downstream burner tube space. Compressed air from a cooling air cavity in the nozzle flows through an inner swirler, passing downstream from the tip of the nozzle to the burner tube space, cooling the nozzle tip and improving the mixing of the gas-fuel with air, thereby reducing emissions from the gas turbine and reducing soot formation in startup. Direction and rotation of the discharged air from the nozzle tip into the burner space may be arranged to promote nozzle tip cooling and gas-fuel mixing with air.Type: ApplicationFiled: December 6, 2010Publication date: June 7, 2012Inventors: Anand Prafulchandra Desai, Karthick Kaleeswaran, Venugopal Polisetty
-
Publication number: 20120125010Abstract: A pressure relief apparatus for an engine compartment having a wall and an opening in the wall is provided. The pressure relief apparatus includes a door panel arranged in blocking relationship to the opening in the wall of the engine compartment, a plurality of hinges coupling the door panel to an inner surface of the wall of the engine compartment, a spring assembly coupled between each hinge and the inner surface of the wall, wherein the spring assembly includes a canister having an open end and a spring element housed within the canister, and a support fitting mounted to the engine compartment wall and having a portion extending toward the open end of the canister for applying a compressive force on the spring element.Type: ApplicationFiled: November 19, 2010Publication date: May 24, 2012Inventors: Armstrong E. Michael, Michael D. Jones, Kent W. Dunstan
-
Patent number: 8181443Abstract: A cooling system of a gas turbine engine, includes a heat exchanger having a common wall shared by a first air passage for directing a portion of a compressor air flow to be used as cooling air, and a second air passage for directing a portion of a bypass air flow, the portion of the compressor air flow being thereby cooled by the portion of the bypass air flow through the common wall.Type: GrantFiled: December 10, 2008Date of Patent: May 22, 2012Assignee: Pratt & Whitney Canada Corp.Inventor: Guiseppe Rago
-
Publication number: 20120117977Abstract: A method for controlling the generation of turbine cooling air from air extracted from a compressor of a gas turbine including: extracting compressed air from a low pressure and a high pressure stage of the compressor; adding in an ejector the compressed air from the low pressure stage to the air from the high pressure stage and discharging the combined air as turbine cooling air; bypassing the ejector with a bypass portion of the extracted compressed air from the high pressure stage; in response to turning on the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air, and adjusting the bypass flow in response to the changed set point to cause the actual pressure ratio to approach the changed set point.Type: ApplicationFiled: May 14, 2008Publication date: May 17, 2012Inventors: Priscilla Childers, Mark Disch, Curtis Newton, III, David Wesley Ball, JR., Kenneth Neil Whaling, Alan Meier Truesdale
-
Publication number: 20120111020Abstract: A control method for cooling a turbine stage of a gas turbine, whereby cooling air is bled from combustion air flowing in a compressor of the gas turbine, and is fed to a cooling circuit staring from a stator of the turbine stage; and cooling airflow is adjusted as a function of the pressure at the inlet of the cooling circuit, and as a function of the combustion air pressure at the exhaust of the compressor; more specifically, there is a feedback control setting a setpoint, which is predetermined as a function of the power output of the turbine to reduce contaminating emissions.Type: ApplicationFiled: October 5, 2011Publication date: May 10, 2012Applicant: ANSALDO ENERGIA S.P.A.Inventors: Luca BOZZI, Marco MANTERO, Federico BONZANI
-
Patent number: 8167543Abstract: A method of manufacturing a wind turbine rotor blade is provided. Anticipated primary load paths within the rotor blade are predicted. Fibers of reinforcing material are dispensed onto a mold, having an orientation pattern of the fibers which is selected in dependence on the predicting step. Resin is also dispensed into the mold. A wind turbine rotor blade is provided. The blade comprises fibers of reinforcing material which are embedded in resin. The fibers are short, say in the range of 5 to 200 mm, and are orientated in dependence on an anticipated structural loading pattern of the rotor blade.Type: GrantFiled: January 26, 2009Date of Patent: May 1, 2012Assignee: Vestas Wind Systems A/SInventor: Paul Hibbard
-
Patent number: 8167551Abstract: A core case section for a gas turbine engine a multitude of discreet radial extending 2.5 bleed ducts defined in part by a rear structural wall.Type: GrantFiled: March 26, 2009Date of Patent: May 1, 2012Assignee: United Technologies CorporationInventors: Brian D. Merry, Gabriel L. Suciu
-
Patent number: 8157241Abstract: A method for regulating gas turbine engine fluid flow may include the steps of providing a flow tube having an open valve, a first bend and a second bend, flowing fluid through the flow tube, actuating a piston so that the piston moves in the axial direction, and closing the valve due to the axial movement of the piston.Type: GrantFiled: February 29, 2008Date of Patent: April 17, 2012Assignee: General Electric CompanyInventor: Mark Douglas Swinford
-
Patent number: 8146366Abstract: A method involved operating a combined-cycle power plant (10), which has a gas turbine (11) with a compressor (12) and a turbine (13), a heat recovery steam generator (17) which is connected downstream to the gas turbine (11) and is for producing steam in a water/steam cycle, and also at least one once-through cooler (21), through which flows compressed air which is compressed in the compressor (12) and intended for cooling the gas turbine (11), and, cooling down, converts feed-water (24) which is fed from the heat recovery steam generator (17) into steam, and discharges the steam to the heat recovery steam generator (17). Making the operation more flexible is achieved, without lowering the load of the gas turbine (11), by the combined-cycle power plant (10) being switched between a first operating mode, in which only the gas turbine cycle is used for power generation, and a second operating mode, in which the gas turbine cycle and the water/steam cycle are used for power generation.Type: GrantFiled: August 26, 2008Date of Patent: April 3, 2012Assignee: ALSTOM Technology Ltd.Inventors: Gijsbertus Oomens, Christoph Ruchti, François Droux
-
Patent number: 8136361Abstract: A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.Type: GrantFiled: May 4, 2006Date of Patent: March 20, 2012Assignee: General Electric CompanyInventors: Carl Gerard Schott, Kevin W. Kinzie, John Joseph Lynch, David W. Ball, Gunnar Leif Siden, Kenneth Neil Whaling
-
Publication number: 20120060506Abstract: A gas turbine engine has a compressor section with rotational compressor components rotatable with respect to static compressor components. A compressed air bleed arrangement is provided to cool one or more other rotational components of the gas turbine engine. The compressed air bleed arrangement takes a flow of compressed air from the compressor section along an off-take passage. The off-take passage opens in the compressor section at an off-take port. The off-take passage is rotatable, in use, with the rotational compressor components. The compressed air bleed arrangement is operable to provide the air in the off-take passage with higher static pressure than the air in the compressor section at the off-take port, by diffusing the air in the off-take passage. The off-take passage further includes off-take vanes, operable to increase the tangential velocity of the air in the off-take passage compared with the air at the off-take port.Type: ApplicationFiled: August 24, 2011Publication date: March 15, 2012Applicant: ROLLS-ROYCE PLCInventors: Jonathan M. KING, Crispin D. BOLGAR, Guy D. SNOWSILL
-
Publication number: 20120060507Abstract: A gas turbine engine comprising a turbine section cooling system and a method of cooling a turbine section of a gas turbine engine is provided. The gas turbine engine comprises in flow series a compressor section, a combustor, and a turbine section, the engine further comprising a turbine section cooling system. The turbine section cooling system including a first compressed air bleed arrangement and a second compressed air bleed arrangement. The first compressed air bleed arrangement bleeds a first flow of compressed air from a high pressure stage of the compressor section. The first flow of compressed air bypasses the combustor and arrives at the turbine section to form a sealing and/or cooling flow at a row of stator vanes upstream of an adjacent rotor disc. The second compressed air bleed arrangement bleeds a second flow of compressed air from one or more lower pressure stages of the compressor section.Type: ApplicationFiled: September 2, 2011Publication date: March 15, 2012Applicant: ROLLS-ROYCE PLCInventors: Jonathan M. KING, Crispin D. BOLGAR, Guy D. SNOWSILL, Michael J. SHEATH, Geoffrey M. DAILEY
-
Publication number: 20120047908Abstract: An exemplary burner arrangement and method for operating a burner arrangement are disclosed. During operation of the burner arrangement a hot combustion gas, including combustion air, flows essentially parallel to a burner wall through a mixing chamber, which is delimited by the burner wall, to a combustion chamber. In the mixing chamber the hot combustion gas is mixed with an injected fuel, where cooling air from the outside of the burner wall flows through effusion holes in the burner wall into an interior of the mixing chamber. The cooling air, on the outside of the burner wall, is deflected in a directed manner in its flow direction by means of deflection elements which are in a distributed arrangement.Type: ApplicationFiled: August 26, 2011Publication date: March 1, 2012Applicant: ALSTOM Technology LtdInventors: Madhavan Poyyapakkam, Adnan Eroglu, Andrea Ciani, Diane Lauffer, Uwe Ruedel
-
Patent number: 8126628Abstract: A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.Type: GrantFiled: August 3, 2007Date of Patent: February 28, 2012Assignee: General Electric CompanyInventors: John Erik Hershey, Brock Estel Osborn, Donald Lee Gardner, Rafael Jose Ruiz, William Lee Herron
-
Publication number: 20120036864Abstract: A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.Type: ApplicationFiled: August 4, 2011Publication date: February 16, 2012Applicant: ALSTOM Technology LtdInventors: Sergei RIAZANTSEV, Holger Kiewel, Sven Olmes, Thomas Kramer, Sergey Shchukin
-
Publication number: 20120031105Abstract: A plug for regulating a flow of gas in a system is disclosed. The plug includes a housing disposed on a temperature boundary in a system. The housing defines a passage for flowing gas therethrough. The plug further includes at least one pressure-actuated valve disposed in the passage and movable between an open position and a closed position. The at least one pressure-actuated valve moves from the open position to the closed position as the pressure of the gas increases and moves from the closed position to the open position as the pressure of the gas decreases.Type: ApplicationFiled: August 3, 2010Publication date: February 9, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Manikandan Thiyagarajan, Anantha Ramesh Rangaswamy, Pugalenthi Nanda Gopal
-
Publication number: 20110314835Abstract: A cooling system in an aircraft gas turbine engine includes a heat exchanger positioned within an annular nacelle space surrounding a bypass duct of the engine. The heat exchanger has a radial coolant passage extending between the bypass duct and ambient air surrounding the nacelle, and a flow passage extending substantially normal to the radial passage for direction of a fluid to be cooled therethrough. A configuration of this nature may assist in defining a no-flow length of the heat exchanger in a third direction normal to the other two mentioned directions, which may allow for improved performance within a given radial envelope.Type: ApplicationFiled: June 24, 2010Publication date: December 29, 2011Applicant: PRATT & WHITNEY CANADA CORP.Inventor: Xiaoliu LIU
-
Publication number: 20110302928Abstract: The heat exchanger includes a large number of small, closely-spaced modules. Within each module of one embodiment, the fuel flows through a series of parallel micro-channels, while the air flows externally over rows of short, straight fins perpendicular to the direction of fuel flow. A theoretical model was developed to predict the thermal performance of the module for various operating conditions. To confirm the accuracy of the model, a module was constructed and tested using water to simulate the aircraft fuel.Type: ApplicationFiled: March 1, 2010Publication date: December 15, 2011Applicant: PURDUE RESEARCH FOUNDATIONInventor: Issam Mudawar
-
Patent number: 8065022Abstract: Embodiments of the invention can include methods and systems for controlling clearances in a turbine. In one embodiment, a method can include applying at least one operating parameter as an input to at least one neural network model, modeling via the neural network model a thermal expansion of at least one turbine component, and taking a control action based at least in part on the modeled thermal expansion of the one or more turbine components. An example system can include a controller operable to determine and apply the operating parameters as inputs to the neural network model, model thermal expansion via the neural network model, and generate a control action based at least in part on the modeled thermal expansion.Type: GrantFiled: January 8, 2008Date of Patent: November 22, 2011Assignee: General Electric CompanyInventors: Karl Dean Minto, Jianbo Zhang, Erhan Karaca
-
System for delivering air from a multi-stage compressor to a turbine portion of a gas turbine engine
Patent number: 8057157Abstract: A system for providing air from a multi-stage to a turbine includes a turbine having a high pressure input port and a low pressure input port. The system also includes a compressor having at least one high pressure extraction air output and at least one low pressure extraction air output. A valve is fluidly connected to the at least one high pressure extraction air output, at least one low pressure extraction air output and low pressure input port of the turbine. The valve is selectively operated to fluidly connect the at least one low pressure extraction air output with the low pressure input port during normal operating conditions and fluidly connect the at least one high pressure extraction air output and the low pressure input port during a turn down condition or below design temperature operation to enhance turbine engine performance.Type: GrantFiled: October 22, 2007Date of Patent: November 15, 2011Assignee: General Electric CompanyInventors: Eric David Roush, William Andrew Parker -
Patent number: 8038412Abstract: A hydraulic pump system is provided that includes a pump driven by an electric motor. The electric motor includes windings that receive power from a power source. In one example, a temperature sensor is arranged in proximity to hydraulic fluid associated with the pump, such as at an input of the pump. In another example, the temperature sensor measures the ambient temperature to predict the viscosity of the pump based upon cool down rates of the system. A controller monitors a temperature at the temperature sensor and commands power to be provided to the windings to generate heat. Electric motor power consumption can be monitored to determine viscosity. The heat reduces the viscosity of the hydraulic fluid. Bleed air may be selectively provided to a casing associated with the hydraulic fluid in response to a command from the controller. The controller actuates a valve to regulate the flow of bleed air to the casing to provide supplemental heat to the heat provided by the windings.Type: GrantFiled: June 6, 2007Date of Patent: October 18, 2011Assignee: Hamilton Sundstrand CorporationInventor: William G. Durtschi
-
Publication number: 20110247344Abstract: In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.Type: ApplicationFiled: April 9, 2010Publication date: October 13, 2011Inventors: Jorn A. Glahn, Peter M. Munsell, Steven B. Johnson
-
Patent number: 8033118Abstract: A simplified air bleed balancing control system for a pair of aircraft gas turbine engines reduces the number of pressure transducers and differential pressure transducers. Advantages include lower weight, less expensive system, better total system MTBF (mean time before failure), acceptable differential pressure transducer drift identification and compensation by the digital controller, and fewer maintenance tasks.Type: GrantFiled: January 31, 2008Date of Patent: October 11, 2011Assignee: EMBRAER—Empresa Brasileira de Aeronautica S.A.Inventors: Oswaldo Barthel Monteiro, Vinicius Jorge Tin, Bernardo Campos da Silva Franco, Ricardo Jose Barbosa
-
Patent number: 8015826Abstract: Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the T_PZ above a lower T_PZ limit. A method for operating a turbine engine assembly is also disclosed.Type: GrantFiled: April 5, 2007Date of Patent: September 13, 2011Assignee: Siemens Energy, Inc.Inventors: Gerald A. Myers, David A. Little
-
Patent number: 8015795Abstract: An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being a plurality of air transfer ducts each extending from a different location in the gas turbine engine so as to be capable to provide air in each of those air transfer ducts at one end thereof at pressures differing from one another and connected at the other end of each to the air intake to transfer air thereto.Type: GrantFiled: May 18, 2007Date of Patent: September 13, 2011Assignee: United Technologies CorporationInventors: Frederick M. Schwarz, Brian M. Fentress
-
Patent number: 8015824Abstract: A method and system for regulating a cooling fluid within a turbomachine in real time. The system may an external flow conditioning system for adjusting at least one property of the cooling fluid, wherein the external flow conditioning system comprises an inlet portion and an outlet portion. The system may also include at least one heat exchanger; at least one control valve; at least one bypass orifice; at least one stop valve; and a control system.Type: GrantFiled: May 1, 2007Date of Patent: September 13, 2011Assignee: General Electric CompanyInventors: Sivaraman Vedhagiri, Ravi Meenaksh, Jesse E. Trout, Jun Yang
-
Patent number: 8001789Abstract: An improved inlet bleed heat system for a gas turbine engine is disclosed. The inlet bleed heat system provides improved mixing in an inlet region while permitting the engine to be operated at lower power settings. The inlet bleed heat system comprises a supply conduit, a plurality of feed tubes extending from the supply conduit, and a guide tube for receiving opposing ends of the feed tubes. The plurality of feed tubes each have a plurality of injection orifices and the feed tubes are oriented such that the injection orifices generally face into a flow of oncoming air with the feed tubes being positioned forward of a plurality of sound attenuating baffles.Type: GrantFiled: March 26, 2008Date of Patent: August 23, 2011Assignee: Alstom Technologies Ltd., LLCInventors: Santiago Vega, Charlie Ellis, Roger Kastelic, James Leahy, Janak Raguraman
-
Patent number: 7997084Abstract: A gasifying furnace gasifies solid fuel or liquid fuel. A gas turbine drives a turbine to generate power by using combustion gas generated by burning mixed gas of compressed air compressed in a compressor and gas generated in the gasifying furnace in a combustor. A booster boosts compressed air bled from the compressor, and feed the compressed air to the gasifying furnace. A bleed source valve is provided in a bleed line between the compressor and the booster. An abnormality stop controller stops the booster and the gas turbine, based on an opening angle of the bleed source valve or a bleed pressure on an upstream side of the bleed source valve.Type: GrantFiled: December 14, 2006Date of Patent: August 16, 2011Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Satoru Kamohara, Akihiko Saito, Takashi Sonada, Yasuhiro Takashima, Satoko Fujii
-
Publication number: 20110162383Abstract: An inlet bleed heat system in a gas turbine includes a compressor discharge extraction manifold that extracts compressor discharge air, an inlet bleed heat manifold receiving the compressor discharge air, and a plurality of acoustic dispersion nozzles disposed at an output end of the inlet bleed heat manifold that reduce a velocity of the compressor discharge air in the inlet bleed heat manifold. Noise is generated from the shearing action between the surrounding atmosphere and air jets from orifices. When the air jet velocity is slowed using, for example, a multi-stage ejector/mixer, noise can be abated.Type: ApplicationFiled: January 4, 2010Publication date: July 7, 2011Inventors: Hua Zhang, David Wesley Ball
-
Publication number: 20110162384Abstract: A system for modulating the amount of air supplied through a pressure boundary in a gas turbine is disclosed that includes a passageway located on the pressure boundary. Additionally, a temperature activated valve is mounted within the passageway and is configured to activate at a predetermined temperature threshold. Specifically, the temperature activated valve activates from a closed position to an open position when the local temperature at the temperature activated valve reaches or exceeds the predetermined temperature threshold to allow air to flow through the passageway.Type: ApplicationFiled: January 7, 2010Publication date: July 7, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: RICHARD HENRY LANGDON, II, GARY CHARLES LIOTTA
-
Patent number: 7972105Abstract: A method of starting up a turbine with a compressor have an inlet guide vane, a number of bleed valves, and a number of blades so as to limit the duration in a rotating stall window. The method may include starting rotation of the blades, increasing the speed of the rotation of the blades, closing one or more bleed valves so as to shift the rotating stall window to a higher rotational speed, partially opening the inlet guide vane to a position outside the rotating stall window, and opening the bleed valves while partially closing the inlet guide vane such that the number of blades pass through the rotating stall window.Type: GrantFiled: May 10, 2007Date of Patent: July 5, 2011Assignee: General Electric CompanyInventors: Timothy Dejoris, Michael J. Dutka, Nick Martin, Steven M. Schirle
-
Publication number: 20110138818Abstract: Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine.Type: ApplicationFiled: September 24, 2009Publication date: June 16, 2011Applicants: MITSUBISHI HEAVY INDUSTRIES, LTD., TOHOKU ELECTRIC POWER COMPANY, INC.Inventors: Satoshi Mizukami, Tatsuo Ishiguro, Junichiro Masada, Kazumasa Takata, Yuya Fukunaga, Hiroki Takahashi, Masaki Satoh, Yoshiaki Nishimura, Norio Oogai, Souji Hasegawa, Masato Hayashi
-
Publication number: 20110131999Abstract: A device for producing electrical power. A thermoelectric device is coupled to an aircraft bleed system for generating electrical power using temperature differentials between ram air and bleed air.Type: ApplicationFiled: December 7, 2009Publication date: June 9, 2011Inventors: LIJUN GAO, Shengyi Liu, Chin-Hsi Chien
-
Patent number: 7942009Abstract: A small gas turbine engine with a compressor, a combustor, and a turbine located downstream of the combustor. The compressor and turbine are supported on a rotary shaft, and a main bearing is support on the rotary shaft, the main bearing being located in a hot zone of the combustor. The main bearing includes cooling air passages within the races to provide cooling for the bearing. A cooling air is diverted from the compressor and passed through the bearing cooling passages for cooling the bearing, and then the cooling air is directed into the combustor. The cooling air is also passed through a guide nozzle before being passed through the bearing to cool both the guide nozzle and the bearing. A swirl cup injector is sued to deliver the compressed air from the compressor and the cooling air from the bearing into the combustor, the swirl cup injector also acting to draw the cooling air through the bearing.Type: GrantFiled: June 15, 2009Date of Patent: May 17, 2011Assignee: Florida Turbine Technologies, Inc.Inventors: Mark M Harris, Wesley D Brown, Angel M Garcia
-
Publication number: 20110088405Abstract: A gas turbine engine cooling system includes a heat exchanger in fluid communication with a source of cooling air, a first cooling circuit including a first heat exchanger circuit in the heat exchanger and a first bypass circuit with a first bypass valve for selectively bypassing at least a portion of first airflow around the first heat exchanger circuit. A second cooling circuit may be used having a second heat exchanger circuit in the heat exchanger and a shutoff control valve operably disposed in the second cooling circuit upstream of the second heat exchanger circuit and the heat exchanger. A circuit inlet of the first cooling circuit may be used to bleed a portion of compressor discharge bleed air for the first airflow to cool turbine blades mounted on a rotor disk using an annular flow inducer downstream of the first bypass valve and the heat exchanger.Type: ApplicationFiled: October 15, 2009Publication date: April 21, 2011Inventor: John Biagio Turco
-
Patent number: 7926289Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to provide thereto pressurized primary air. A second interstage bleed circuit is joined in flow communication between a second preultimate stage of the compressor and the turbine blades to provide thereto pressurized secondary air at a lower pressure than the primary air.Type: GrantFiled: November 10, 2006Date of Patent: April 19, 2011Assignee: General Electric CompanyInventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
-
Patent number: 7926290Abstract: A gas turbine engine includes a turbomachinery core operable to generating a flow of pressurized combustion gases; a rotating fan adapted to extract energy from the core and generate a first flow of pressurized air; a fan stator assembly connected in flow communication with the fan and operable to vary the first flow of pressurized air while the fan operates at a substantially constant speed; a fan outer duct surrounding the core; and a flade stage comprising a supplementary fan disposed in the fan outer duct and driven by the fan for generating a pressurized bleed air flow.Type: GrantFiled: December 18, 2006Date of Patent: April 19, 2011Assignee: General Electric CompanyInventor: James E. Johnson
-
Patent number: 7926261Abstract: The invention is a turbofan provided with a pre-cooler. In order to evacuate the heated cool air stream, at least one discharge pipe is arranged in a chamber and connects the pre-cooler to at least one discharge orifice provided in the inner fairing, in output of an exhaust nozzle and at least more or less opposite the wing.Type: GrantFiled: September 13, 2006Date of Patent: April 19, 2011Assignee: Airbus FranceInventor: Alain Porte
-
Patent number: 7921652Abstract: A bleed valve (30) for a gas turbine engine (10) comprises a diffuser (50), through which heated compressor bleed air flows (54) into a bypass duct (22) air stream (B), has a plurality of small holes (40). The plurality of holes (40) is divided into two or more arrays of holes (52p,q,r), each array of holes (52p,q,r) is angled (?) away from one another so that their respective bleed flows (54p,q,r) do not coalesce. This separation improves mixing with the air stream (B) and helps prevent hot bleed air damaging nacelle and other engine components.Type: GrantFiled: June 22, 2007Date of Patent: April 12, 2011Assignee: Rolls-Royce PLCInventor: Stuart James Kirby
-
Patent number: 7921653Abstract: A combustor for a turbine including a combustor liner; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween, the first flow sleeve having at least one cooling aperture formed about a circumference thereof for directing compressor discharge air as cooling air into the first flow annulus; a casing surrounding first flow sleeve with a second flow annulus therebetween, the first flow sleeve having at least one air extraction opening formed about a circumference thereof for directing compressor discharge air from the first flow annulus as extraction air into the second flow annulus; and an extraction port operatively coupled to the casing for extracting the extraction air from the second flow annulus.Type: GrantFiled: November 26, 2007Date of Patent: April 12, 2011Assignee: General Electric CompanyInventors: Abhijit Som, Jonathan Dwight Berry
-
Publication number: 20110067413Abstract: A passive pressurizing air system for a gas turbine engine includes a flow path for directing an air flow having a low temperature and low pressure, extending through a cavity to a pressurized area of the engine. The cavity contains pressurized air having a high temperature and high pressure. An air flow mixing apparatus is provided for adding the pressurized air from the cavity into the flow path to provide a mixed air flow having an intermediate temperature and intermediate pressure.Type: ApplicationFiled: November 23, 2010Publication date: March 24, 2011Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Daniel T. ALECU, Dean CARPENTER
-
Publication number: 20110067412Abstract: There is disclosed an aircraft propulsion arrangement including a gas turbine aircraft engine having a compressor, an oil system configured to route engine oil through a heat exchanger mounted so as to define part of an aerodynamic surface to the flow of ambient air, and a duct arrangement fluidly connecting the compressor to the heat exchanger. There is also proposed a method of operating the engine, the method involving the steps of: (a) flowing engine oil through the heat exchanger and thus into heat-exchange relationship with said ambient air; and (b) directing a bleed flow of compressor gas drawn from the compressor along said duct arrangement and into heat-exchange relationship with said oil in said heat exchanger, wherein said directing step (h) is performed selectively.Type: ApplicationFiled: September 8, 2010Publication date: March 24, 2011Applicant: ROLLS-ROYCE PLCInventor: Richard G. STRETTON
-
Patent number: 7886520Abstract: Within a turbine engine a heat exchanger may be provided to cool compressor air flows to be utilized for cabin ventilation or other functions. A fluid flow acting as a coolant for the heat exchanger is generally drawn from the by-pass duct of the engine and a dedicated outlet duct is provided such that the exhausted fluid flow from the heat exchanger is delivered along the conduit duct to a low pressure region. In such circumstances, an appropriate pressure differential across the heat exchanger is maintained for operational efficiency when required, whilst the exhausted fluid flow is isolated and does not compromise the usual engine ventilation vent exit area sizing. Over-sized ventilation vents would create an aerodynamic step and therefore drag upon the thrust of the engine.Type: GrantFiled: April 19, 2007Date of Patent: February 15, 2011Assignee: Rolls-Royce plcInventors: Richard G Stretton, Pawel R Zakrzewski
-
Patent number: 7870743Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.Type: GrantFiled: November 10, 2006Date of Patent: January 18, 2011Assignee: General Electric CompanyInventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
-
Patent number: 7870742Abstract: A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.Type: GrantFiled: November 10, 2006Date of Patent: January 18, 2011Assignee: General Electric CompanyInventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
-
Patent number: 7861513Abstract: A gas turbine engine comprising a ventilation zone defined between a core engine casing and a core fairing and having a discharge nozzle, the engine further comprises a pre-cooler having a flow of coolant therethrough and which coolant being ducted into the ventilation zone wherein an additional ventilation zone outlet system is provided and comprises a variable area outlet.Type: GrantFiled: April 13, 2007Date of Patent: January 4, 2011Assignee: Rolls-Royce PLCInventor: Richard G. Stretton
-
Publication number: 20100326088Abstract: To include a cooling passage leading from a latter stage of a compressor, via an external cooler, to a hollow part provided in a load coupling that couples a rotor of the compressor and a rotor of a turbine to each other, and also leading from the hollow part to the latter stage of the compressor, and a centrifugal compressor that raises air pressure in the hollow part with rotation of the load coupling, in the hollow part. Therefore, pressure of the air in the hollow part is raised by the centrifugal compressor by using a centrifugal force resulting from the rotation of the load coupling at the time of operating the gas turbine. Cooled air flows from the hollow part to between compressor rotor blades and compressor vanes at the latter stage, and then flows into the hollow part, thereby enabling to efficiently reduce temperature in the hollow part.Type: ApplicationFiled: January 8, 2009Publication date: December 30, 2010Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Shinya Hashimoto, Kenichi Arase
-
Publication number: 20100319359Abstract: In certain embodiments, a system includes a fuel heater. The fuel heater includes a first heat exchanger configured to receive compressed air from a compressor and to transfer heat from the compressed air to a cooled intermediate heat transfer media to generate a heated intermediate heat transfer media. The fuel heater also includes a second heat exchanger configured to receive the heated intermediate heat transfer media from the first heat exchanger and to transfer heat from the heated intermediate heat transfer media to a fuel. The first heat exchanger is configured to receive the cooled intermediate heat transfer media from the second heat exchanger.Type: ApplicationFiled: June 19, 2009Publication date: December 23, 2010Applicant: General Electric CompanyInventors: Joel Donnell Holt, Devkinandan Madhukar Tokekar