WO2013141937A1 - Commande de jeu d'extrémité de turbine à gaz - Google Patents

Commande de jeu d'extrémité de turbine à gaz Download PDF

Info

Publication number
WO2013141937A1
WO2013141937A1 PCT/US2012/072133 US2012072133W WO2013141937A1 WO 2013141937 A1 WO2013141937 A1 WO 2013141937A1 US 2012072133 W US2012072133 W US 2012072133W WO 2013141937 A1 WO2013141937 A1 WO 2013141937A1
Authority
WO
WIPO (PCT)
Prior art keywords
gas turbine
turbine engine
wall
tip clearance
thermoelectric device
Prior art date
Application number
PCT/US2012/072133
Other languages
English (en)
Inventor
Adam J. MORRISON
Original Assignee
Rolls-Royce North American Technologies, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls-Royce North American Technologies, Inc. filed Critical Rolls-Royce North American Technologies, Inc.
Priority to EP12872268.3A priority Critical patent/EP2805025B1/fr
Priority to CA2862644A priority patent/CA2862644C/fr
Publication of WO2013141937A1 publication Critical patent/WO2013141937A1/fr
Priority to US14/318,282 priority patent/US20140314567A1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/40—Type of control system
    • F05D2270/44—Type of control system active, predictive, or anticipative

Definitions

  • the present invention generally relates to gas turbine engine thermal devices, and more particularly, but not exclusively, to tip clearance control of the gas turbine engine.
  • One embodiment of the present invention is a unique tip clearance control system.
  • Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for controlling tip clearance. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
  • FIG. 1 depicts an embodiment of a gas turbine engine having a tip clearance control system.
  • FIG. 2 depicts an embodiment of a tip clearance control system.
  • FIG. 3 depicts an embodiment of a tip clearance control system.
  • FIG. 4 depicts another embodiment of a tip clearance control system.
  • FIG. 5 depicts an embodiment of a tip clearance control system.
  • FIG. 6 depicts an arrangement of thermoelectric devices.
  • a gas turbine engine 50 having a number of turbomachinery components useful in the generation of power, such as but not limited to providing power for an aircraft 52.
  • aircraft includes, but is not limited to, helicopters, airplanes, unmanned space vehicles, fixed wing vehicles, variable wing vehicles, rotary wing vehicles, unmanned combat aerial vehicles, tailless aircraft, hover crafts, and other airborne and/or extraterrestrial (spacecraft) vehicles.
  • the present inventions are contemplated for utilization in other applications that may not be coupled with an aircraft such as, for example, industrial applications, power generation, pumping sets, naval propulsion, weapon systems, security systems, perimeter defense/security systems, and the like known to one of ordinary skill in the art.
  • the gas turbine engine 50 includes a compressor 54, combustor 56, and turbine 58 which together operate to produce the power. Air or other suitable working fluid enters to the compressor 54 whereupon it is compressed and routed to the combustor 56 to be mixed with a fuel.
  • the combustor 56 is capable of combusting the mixture of fuel and working fluid.
  • the turbine 58 extracts work from the products of combustion that result from the combustion of fuel and working fluid. In some forms the flow stream exiting the turbine can be routed to a nozzle to produce thrust.
  • the gas turbine engine 50 can take a variety of forms other than that depicted in the illustrated embodiment. For example, though the embodiment is shown as a single spool engine, other embodiments can include greater numbers of spools.
  • the gas turbine engine 50 can take the form of a turbojet, turboprop, turboshaft, or turbofan engine and can be a variable cycle and/or adaptive cycle engine.
  • the gas turbine engine 50 is also depicted in the illustrated embodiment as an axial flow engine, but in other embodiments it can be a radial flow engine and/or a mixed radial/axial flow engine. In short, any variety of forms are contemplated for the gas turbine engine 50.
  • the term blade and vane can be used interchangeably to identify an air flow member disposed within the turbomachinery component.
  • the tip clearance control system 60 can be used to regulate a temperature of the wall thus changing the thermal growth of the wall to affect a clearance between the airflow member and the wall.
  • the tip clearance control system 60 can be active during all or portions of operation of the gas turbine engine and in one form is capable of anticipating transient events to avoid and/or mitigate a clearance or contact between the blade and the wall.
  • the controller 60 can be comprised of digital circuitry, analog circuitry, or a hybrid combination of both of these types. Also, the controller 60 can be programmable, an integrated state machine, or a hybrid combination thereof.
  • the controller 60 can include one or more Arithmetic Logic Units (ALUs), Central Processing Units (CPUs), memories, limiters, conditioners, filters, format converters, or the like which are not shown to preserve clarity.
  • ALUs Arithmetic Logic Units
  • CPUs Central Processing Units
  • memories limiters, conditioners, filters, format converters, or the like which are not shown to preserve clarity.
  • the controller 60 is of a programmable variety that executes algorithms and processes data in accordance with operating logic that is defined by
  • controller 60 is configured to operate as a Full Authority Digital Engine Control (FADEC);
  • FADEC Full Authority Digital Engine Control
  • controller 60 can be exclusively dedicated to tip clearance control, or may further be used in the regulation/control/activation of one or more other subsystems or aspects of aircraft 52.
  • the aircraft 52 and/or gas turbine engine 50 can be capable of operating at a variety of conditions in which the tip clearance control system 60 may be exercised.
  • a sensor 62 is included that can be used to measure/estimate/assess/etc a number of conditions/states/etc.
  • the sensor 62 can be used to measure aircraft flight condition such as speed and altitude, to set forth just two non-limiting examples.
  • the sensor 62 can output any variety of data whether sensed or calculated.
  • the sensor 62 can sense and output conditions such as static temperature, static pressure, total temperature, and/or total pressure, among possible others.
  • the sensor 62 can output calculated values such as, but not limited to, equivalent airspeed, altitude, and Mach number. Any number of other sensed conditions or calculated values can also be output.
  • the sensor 62 can also take the form of a proximity sensor useful in providing information regarding a tip clearance between a blade of the
  • the turbomachinery component and an adjacent wall. Such information is used by the controller 60 in the regulation of the tip clearance between a moving blade and a wall of the turbomachinery component.
  • the sensor 62 provides real time signals of the distance such that a plurality of distance values as a function time are generated.
  • the sensor 62 can either provide raw sensed information, either analog or digital, or it can provide a computed value.
  • the senor 62 can output information in a variety of formats and can further be conditioned using additional electronics and/or software.
  • the sensor 62 can provide multiple useful signals to the controller 60 such as a minimum distance, maximum distance, time varying distance, historical information, etc. Alternatively and/or additionally such information can be computed in the controller 60 or other alternative and/or additional module. No matter the form, content, etc, the sensor 62 is capable of providing sufficient information that enables the controller 60 to regulate the temperature of the wall such that a clearance between the wall and the blade(s) is regulated.
  • the proximity sensor 62 can be a capacitive sensor or optical sensor, among potential others useful for detecting a tip clearance.
  • the sensor 62 can be configured to withstand elevated temperatures of a gas turbine engine 50, whether in rotating compressor equipment or turbine components, and can be resistant chemical attack as well as resistant to deposition of solids onto its exposed surfaces. Further, the sensor 62 can also be resistant to
  • thermoelectric device 64 for changing a temperature of a portion 66 of a turbomachinery component.
  • the thermoelectric device 64 can be powered by the engine 50 or a vehicle power system such as may be coupled with an airframe of an aircraft.
  • the temperature of the component can determine its relative size/orientation such that in one form at higher temperatures the component is relatively larger than at low
  • thermoelectric device can be a fully reversible system that can either heat or cool the component.
  • the thermoelectric system can include or be supplemented with circuitry, software logic, electrical components, etc. that provide either a heating or a cooling, but not both. It will be understood that such a system will still include at its core a thermoelectric device that can be operated in both directions were it not for the additional or supplemental configuration.
  • the tip clearance control system can selectively heat and cool the component to affect a tip clearance between the component and the blade.
  • thermoelectric device shown in FIGS. 2 and 3 includes a configuration of alternating semiconductor materials, and specifically alternating p-type and n-type semiconductors.
  • the type of device depicted in these figures can also be used in any of the embodiments herein. Any variety of material types can be used to form the thermoelectric device.
  • thermoelectric devices described herein can take the form of a thermoelastic film which can have any variety of shapes and sizes. Any variety of thermoelectric effects, and accompanying configurations, can be employed by the
  • thermoelectric device to alter a temperature of the turbomachinery component to change a tip clearance between the wall 66 and the blade 70.
  • thermoelectric devices that rely the Seebeck effect, Peltier effect, and Thomson effect, are all contemplated within the scope of the application.
  • Thermoelectric heaters/coolers can be coupled with the controller 60 in a way that an electric state of the thermoelectric device 64 can be regulated to control a tip clearance.
  • embodiments include a radially inner substrate 78 and a radially outer substrate 80 to which the p-type semiconductor 74 and n-type 76 are coupled.
  • the radially inner substrate 78 is coupled with electrical leads 82 and 84 between which can be a potential difference.
  • the leads 82 and 84 are coupled to the substrate 78 in a way that creates a pathway for current flow through the thermoelectric device 64.
  • the potential difference between the leads 82 and 84 can be the result of a waste heat being captured by the thermoelectric device and in others a potential difference can be applied across the leads to encourage a heat transfer in a certain direction, such as whether to cool or heat the wall 66, to set forth just two non-limiting examples.
  • the potential difference applied across the leads can be the result of electric power provided by a thermoelectric device disposed elsewhere whether associated with the vehicle and/or gas turbine engine.
  • the electric power can originate from a battery that is charged using a thermoelectric device disposed elsewhere.
  • a waste heat can be captured by one thermoelectric device and the electric power stored using a storage device such as but not limited to a battery.
  • the waste heat can be used to directly regulate power across another thermoelectric device.
  • a waste heat can be stored for purposes other than strictly tip clearance.
  • thermoelectric device 64 Though a number of p-type 74 and n-type 76 are depicted in the illustrated embodiment, more or fewer can also be used.
  • the semiconductors are alternated along the flow stream direction in a pattern that alternates between the types of semiconductors, but any other pattern is also contemplated.
  • individual pairings of p-type 74 and n-type 76 semiconductors can be combined with other individual pairings in any number of combinations to be used in the thermoelectric device 64.
  • thermoelectric device 64 can extend over the entire periphery of the engine case in some embodiments, while in other embodiments the device 64 may only extend over part of the engine case. In some forms a number of thermoelectric devices 64 can be located about the engine case at the same or different axial stations. In still other alternative and/or additional embodiments, the thermoelectric devices 64 can be configured such that portions of the device distributed around the engine case can be selectively operated. For example, a portion in one circumferential region can be activated to provide one level of heat transfer, while a portion in another circumferential region can be activated to provide another level of heat transfer, whether the heat transfer is a heating or a cooling. Various modules can also be used, which in whole or in part can be operated similarly to provide localized heat transfer to the engine case, again whether that heat transfer is a heating or cooling.
  • Thermal transfer member 86 which in the illustrate embodiment is in the form of fins but other embodiments need not include fins, can be used to assist in transferring heat between a medium 88 and the wall 66.
  • the medium can be a flowing working fluid, such as a cooling air, to aid in heat transfer when the thermoelectric device 64 is in operation.
  • the thermal transfer fins 86 of the illustrated embodiment can take a variety of shapes and sizes whether generally referred to as a "fin" or other device useful in transferring heat with the medium 88.
  • the thermal transfer fins 86 can cover the entirety of the thermoelectric device 64 or only a portion thereof.
  • thermoelectric device 64 is shown located above a compressor blade 70 just upstream of a diffuser 90.
  • the thermoelectric device 64 can include a thermal mass 92 that assists in the transfer of heat between the thermoelectric device 64 and a medium in contact with the thermal mass 92.
  • the thermal mass can take a variety of forms such as a cold plate and/or fins. In any of the embodiments herein, any of the fins, cold plates,
  • FIG. 5 shows a view of an embodiment of the tip clearance control system 60 in which a number of thermoelectric devices in the form of modules 94 are spaced about the circumference of a gas turbine engine case 96.
  • the modules 94 are evenly distributed in a single row round the circumference of the case 96, but other arrangements are also contemplated. For example, a higher concentration of modules 94 can be located at certain circumference locations than other. Some modules 94 can be axially offset from others, while in other embodiments additional rows can also be added.
  • the modules 94 can be controlled individually, in clusters, or as a whole. Furthermore, the modules 94 can have different sizes, configurations, capabilities, etc even though the illustrated embodiment depicts similar modules. In sum, any variety of physical and control arrangements as well as size and capabilities are contemplated.
  • thermoelectric devices described herein can be affixed to a casing or other suitable gas turbine engine structure through a variety of techniques.
  • the thermoelectric devices can be affixed via a thermally conductive bond.
  • the thermoelectric devices can be affixed to the bond at discrete locations around the casing or other suitable structure, or for a full circumferential length around the casing, etc.
  • thermoelectric devices described herein can be powered using a variety of power sources.
  • the electrical power originates from a generator driven by the gas turbine engine 50.
  • the thermoelectric device can be powered by an energy storage device, such as a battery.
  • the thermoelectric devices can be powered by other thermoelectric devices, some of which can be in thermal communication with the gas turbine engine.
  • FIG. 6 depicts an arrangement of thermoelectric devices used in the gas turbine engine 50 in which one device 98, or a set of devices is used to provide power to another device 100, or set of devices.
  • two separate rows of thermoelectric devices are shown in each of the compressor 54 and the turbine 58.
  • the devices 98 shown as thermally coupled with the turbine 58 in the illustrated embodiment can be used to generate power to drive the devices 100 shown as thermally coupled with the compressor 54.
  • the illustrated embodiment depicts flowing power from devices in a turbine area to devices in a compressor area, other locations and directions of power transfer are contemplated. In this way power generated using a thermoelectric devices in one location of the gas turbine engine can be used to power thermoelectric devices in another location.
  • one embodiment would be to coupe the tip clearance control system with a set of thermoelectric modules attached elsewhere to the engine or to hardware mounted on the engine such as a bleed air duct.
  • the tip clearance, or gap can be set during manufacture of the turbomachinery component and/or gas turbine engine to favor a certain flight condition, engine operating
  • the tip clearance can be set to accommodate a snap deceleration in which a tip clearance is typically the tightest owing to a faster cooling of the casing than the rotating disc and blades.
  • the gap can be manipulated during cruise by supplying power to the thermoelectric devices.
  • thermoelectric device is shown as being coupled at a radially outer portion of the flow path 68 but other locations are also contemplated to affect a change in a tip clearance between a blade 70 and wall 66.
  • One aspect of the present application includes an apparatus comprising a gas turbine engine flow path wall forming a boundary for the flow of a working fluid through a turbomachinery component having an airfoil shaped component during operation of a gas turbine engine, a thermoelectric device in thermal communication with the gas turbine engine flow path wall, and a control module structured to regulate the thermoelectric device to influence a thermally induced gap between the gas turbine engine flow path wall and the airfoil shaped component .
  • control module can regulate the thermoelectric device to selectively heat the gas turbine engine flow path wall in a first mode of operation and selectively cool the gas turbine engine flow path wall in a second mode of operation.
  • thermoelectric device is in thermal communication with protrusions that project into a cooling space.
  • Still another feature of the present application provides wherein the control module regulates the thermoelectric device on basis of a sensed clearance derived from a proximity sensor.
  • proximity sensor operates according to one of capacitive principles and optical principles.
  • thermoelectric device in a first mode of operation the thermoelectric device is used to generate a potential difference based upon a waste heat of the gas turbine engine.
  • thermoelectric device includes a plurality of P-Type and N-Type semiconductors.
  • a still further feature of the present application provides wherein a first P- Type semiconductor and a first N-Type semiconductors are located at different flow stream locations, wherein the plurality of semiconductors extend around the full circumference of the gas turbine engine flow path wall, and wherein a thermally conductive bond is used to coupled the thermoelectric device with the turbomachinery component.
  • Another aspect of the present application provides anapparatus
  • a gas turbine engine flow component having a flow path defined by a wall and in which is disposed a blade used to alter a direction of a flow through the component, and a tip clearance control system configured to change a distance between the wall and the blade, the clearance control system having an electrical device that includes a junction between dissimilar materials in thermal communication with the wall wherein a potential difference across the junction is related to a temperature difference across the junction.
  • tip clearance control system is structured to regulate a voltage across the electrical device to perform one of heating the gas turbine engine flow component and cooling the gas turbine engine flow component.
  • Yet still another feature of the present application further includes a sensor in feedback relation with the tip clearance control system, the sensor operable to provide a regulation variable such that the distance between the wall and the rotatable blade is controlled.
  • Still yet another feature of the present application provides wherein the sensor generates a signal representative of a distance between the wall and at least one of the blades.
  • a further feature of the present application provides wherein the proximity sensor includes one of a capacitor and an optical sensor.
  • a still further feature of the present application provides wherein during operation of the tip clearance control system, waste heat from the gas turbine engine is used to power the thermoelectric device.
  • a yet still further feature of the present application further includes an energy storage device to harvest potential difference generated by the waste heat.
  • Still another aspect of the present application provides an apparatus comprising a gas turbine engine having rotatable blade and an end wall, and means for thermoelectrically changing a distance between the blade and the end wall.
  • Yet still another aspect of the present application provides a method comprising operating a gas turbine engine to produce a flow stream through a turbomachinery component of the gas turbine engine, moving a bladed row of airflow members in the turbomachinery component, the flow stream traversing through the bladed row;, flowing an electrical current across a junction of two dissimilar materials to produce a heating response, changing a clearance between a wall and the tips of the bladed row in proximity with the wall.
  • a feature of the present application provides wherein the flowing occurs as a result of a thermoelectric phenomena, and the flowing results in a cooling of a wall member of the turbomachinery component.
  • Another feature of the present application further includes changing a tip clearance of the turbomachinery component.
  • Still another feature of the present application further includes determining a tip clearance to aid in the changing a tip clearance.
  • the determining includes sensing the tip clearance with a sensor that operates according to one of capacitive or optical principles.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne une turbine à gaz comportant un dispositif thermoélectrique capable de changer un jeu d'extrémité dans un composant de turbomachine. Dans une forme non limitative, le composant de turbomachine est un compresseur. Le dispositif thermoélectrique peut être utilisé sous différentes formes pour récolter la puissance provenant de la chaleur perdue. Le système de commande de jeu d'extrémité peut comprendre un capteur servant à déterminer le jeu entre une extrémité et une paroi du composant de turbomachine.
PCT/US2012/072133 2011-12-30 2012-12-28 Commande de jeu d'extrémité de turbine à gaz WO2013141937A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP12872268.3A EP2805025B1 (fr) 2011-12-30 2012-12-28 Commande de jeu d'extrémité de turbine à gaz
CA2862644A CA2862644C (fr) 2011-12-30 2012-12-28 Commande de jeu d'extremite de turbine a gaz
US14/318,282 US20140314567A1 (en) 2011-12-30 2014-06-27 Gas turbine engine tip clearance control

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201161581793P 2011-12-30 2011-12-30
US61/581,793 2011-12-30

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US14/318,282 Continuation US20140314567A1 (en) 2011-12-30 2014-06-27 Gas turbine engine tip clearance control

Publications (1)

Publication Number Publication Date
WO2013141937A1 true WO2013141937A1 (fr) 2013-09-26

Family

ID=49223148

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2012/072133 WO2013141937A1 (fr) 2011-12-30 2012-12-28 Commande de jeu d'extrémité de turbine à gaz

Country Status (4)

Country Link
US (1) US20140314567A1 (fr)
EP (1) EP2805025B1 (fr)
CA (1) CA2862644C (fr)
WO (1) WO2013141937A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015156872A3 (fr) * 2014-01-24 2016-01-14 United Technologies Corporation Systèmes de refroidissement thermoélectrique pour systèmes de propulsion d'avion à réaction

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PL225446B1 (pl) * 2013-04-30 2017-04-28 Gen Electric Zespół sterowania cieplnego dla turbiny, zespół wytwarzania energii elektrycznej zawierający turbinę oraz turbina zawierająca zespół sterowania cieplnego
US10938328B2 (en) 2016-06-22 2021-03-02 General Electric Company Harvesting energy from composite aircraft engine components

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2994472A (en) 1958-12-29 1961-08-01 Gen Electric Tip clearance control system for turbomachines
JP2008157340A (ja) * 2006-12-22 2008-07-10 Ntn Corp 転がり軸受
US20090159110A1 (en) * 2007-12-21 2009-06-25 Kwok David W Thermoelectric generation system
FR2943717A1 (fr) * 2009-03-27 2010-10-01 Snecma Stator de compresseur ou turbine de turbomachine permettant un controle du jeu en sommet d'aubes d'un rotor en regard
EP2664746A2 (fr) 2012-05-16 2013-11-20 General Electric Company Systèmes et procédés permettant de régler des dégagements dans des turbines

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4326804A (en) * 1980-02-11 1982-04-27 General Electric Company Apparatus and method for optical clearance determination
GB2117450B (en) * 1981-03-20 1984-06-27 Rolls Royce Casing support for a gas turbine engine
US5216887A (en) * 1987-06-30 1993-06-08 Kabushiki Kaisha Komatsu Seisakusho Radiative-type air-conditioning unit
US5667358A (en) * 1995-11-30 1997-09-16 Westinghouse Electric Corporation Method for reducing steady state rotor blade tip clearance in a land-based gas turbine to improve efficiency
GB2388407B (en) * 2002-05-10 2005-10-26 Rolls Royce Plc Gas turbine blade tip clearance control structure
US20090145105A1 (en) * 2004-12-01 2009-06-11 Suciu Gabriel L Remote engine fuel control and electronic engine control for turbine engine
US20070277866A1 (en) * 2006-05-31 2007-12-06 General Electric Company Thermoelectric nanotube arrays
FR2942077B1 (fr) * 2009-02-06 2013-08-16 Turbomeca Generation thermoelectrique pour turbine a gaz
FR2943093B1 (fr) * 2009-03-16 2015-04-24 Snecma Dispositif de reglage de la position radiale et/ou axiale d'une virole de stator de turbomachine
US8578696B2 (en) * 2010-08-03 2013-11-12 General Electric Company Turbulated arrangement of thermoelectric elements for utilizing waste heat generated from turbine engine
US20120118345A1 (en) * 2010-11-15 2012-05-17 The Boeing Company Thermal integration of thermoelectronic device
US9151176B2 (en) * 2011-11-22 2015-10-06 General Electric Company Systems and methods for adjusting clearances in turbines
US9057282B2 (en) * 2011-11-22 2015-06-16 General Electric Company Systems and methods for adjusting clearances in turbines
US8776530B2 (en) * 2011-11-23 2014-07-15 General Electric Company Gas turbine engine lockout reduction
WO2013141938A1 (fr) * 2011-12-30 2013-09-26 Rolls-Royce North American Technologies, Inc. Commande de jeu d'extrémité de turbine à gaz
PL225446B1 (pl) * 2013-04-30 2017-04-28 Gen Electric Zespół sterowania cieplnego dla turbiny, zespół wytwarzania energii elektrycznej zawierający turbinę oraz turbina zawierająca zespół sterowania cieplnego

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2994472A (en) 1958-12-29 1961-08-01 Gen Electric Tip clearance control system for turbomachines
JP2008157340A (ja) * 2006-12-22 2008-07-10 Ntn Corp 転がり軸受
US20090159110A1 (en) * 2007-12-21 2009-06-25 Kwok David W Thermoelectric generation system
FR2943717A1 (fr) * 2009-03-27 2010-10-01 Snecma Stator de compresseur ou turbine de turbomachine permettant un controle du jeu en sommet d'aubes d'un rotor en regard
EP2664746A2 (fr) 2012-05-16 2013-11-20 General Electric Company Systèmes et procédés permettant de régler des dégagements dans des turbines

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP2805025A4

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015156872A3 (fr) * 2014-01-24 2016-01-14 United Technologies Corporation Systèmes de refroidissement thermoélectrique pour systèmes de propulsion d'avion à réaction
US20160319697A1 (en) * 2014-01-24 2016-11-03 United Technologies Corporation Systems for thermoelectric cooling for jet aircraft propulsion systems
US10472986B2 (en) 2014-01-24 2019-11-12 United Technologies Corporation Systems for thermoelectric cooling for jet aircraft propulsion systems

Also Published As

Publication number Publication date
EP2805025A4 (fr) 2015-11-11
CA2862644A1 (fr) 2013-09-26
EP2805025A1 (fr) 2014-11-26
CA2862644C (fr) 2019-08-27
EP2805025B1 (fr) 2018-05-02
US20140314567A1 (en) 2014-10-23

Similar Documents

Publication Publication Date Title
US9890640B2 (en) Gas turbine engine tip clearance control
EP3205841B1 (fr) Système de prévention de déformation de rotor au moyen de la chaleur perdue et le procédé correspondant
US9581025B2 (en) Aircraft power plant
US9957830B2 (en) Hybrid passive and active tip clearance system
US9714609B2 (en) Gas turbine engine and electric machine
US10752375B2 (en) Aircraft system
US7140832B2 (en) Method and system for rotating a turbine stator ring
US9482156B2 (en) Vehicle recuperator
US10801359B2 (en) Method and system for identifying rub events
US20170159563A1 (en) Method and system for pre-cooler exhaust energy recovery
CA2862644C (fr) Commande de jeu d'extremite de turbine a gaz
EP3208444B1 (fr) Moteur à turbine à gaz avec refroidisseur intermédiaire thermoélectrique
EP2971704B1 (fr) Interface de configuration de moteur à turbine à gaz

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 12872268

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase

Ref document number: 2862644

Country of ref document: CA

NENP Non-entry into the national phase

Ref country code: DE

WWE Wipo information: entry into national phase

Ref document number: 2012872268

Country of ref document: EP