EP1306521A1 - Ailette de rotor pour une turbine à gaz et turbine à gaz avec des ailettes de rotor - Google Patents

Ailette de rotor pour une turbine à gaz et turbine à gaz avec des ailettes de rotor Download PDF

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Publication number
EP1306521A1
EP1306521A1 EP01123797A EP01123797A EP1306521A1 EP 1306521 A1 EP1306521 A1 EP 1306521A1 EP 01123797 A EP01123797 A EP 01123797A EP 01123797 A EP01123797 A EP 01123797A EP 1306521 A1 EP1306521 A1 EP 1306521A1
Authority
EP
European Patent Office
Prior art keywords
blade
cooling air
turbine
blades
gas turbine
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
EP01123797A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP01123797A priority Critical patent/EP1306521A1/fr
Publication of EP1306521A1 publication Critical patent/EP1306521A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the invention relates to a blade for a Gas turbine with a connectable to a turbine shaft Blade base that carries a profiled blade. she further relates to a gas turbine with a number of each combined into rows of blades, on a turbine shaft arranged blades.
  • Gas turbines are used to drive generators in many areas or used by work machines.
  • the fuel will To do this, burned in a combustion chamber, using an air compressor compressed air is supplied. That in the combustion chamber generated by the combustion of the fuel, under high pressure and working medium at high temperature is via a turbine unit downstream of the combustion chamber managed where it relaxes while working.
  • the blades have usually for the appropriate management of the working medium a profiled one extending along a blade axis Airfoil on that of a connectable to the turbine shaft Bucket foot is worn.
  • For guiding the working medium in the turbine unit are usually between neighboring rows of blades with the turbine housing connected rows of vanes arranged.
  • the turbine blades are therefore usually designed to be coolable, being particularly effective and reliable Cooling seen in the flow direction of the working medium first rows of blades should be ensured.
  • the respective turbine blade usually has one integrated into the airfoil or the airfoil Coolant channel from which a coolant is targeted especially the thermally stressed zones of the turbine blade is feedable.
  • Cooling air is usually used as the coolant. This is usually the case for the respective turbine blade in the manner of open cooling via an integrated one Coolant channel supplied. Flowing through from this the cooling air in the branching ducts are provided Areas of the turbine blade. Are on the outlet side these channels left open so that the cooling air after the Flow through the turbine blade and exits with the working medium in the turbine unit mixed.
  • the invention is therefore based on the object of a moving blade for a gas turbine of the type mentioned above, which is reliable with a comparatively simple design Feeding also with comparatively large quantities of cooling air can be ensured. Furthermore, a Gas turbine can be specified with such a blade.
  • the stated object is achieved according to the invention solved by the blade in the blade root a plurality of inflow openings for cooling air are arranged are.
  • the invention is based on the consideration that just for rotor blades that are subject to comparatively high thermal loads adequate feeding with comparatively large quantities of cooling air among other things due to the constructive Boundary conditions usually the lack of space in the Area of the blade root is limited. Because of this Due to lack of space, reliable feeding of the Blade over the entire base cross section problematic his. This is especially true when the cooling air within the blade root via an integrated therein Channel system directed to all areas of the blade root shall be. Turning away from a commonly provided one is only a single inflow opening for cooling air hence a plurality of inflow openings for the cooling air provided, in the manner of a parallel flow an application of a comparatively large Cross-sectional area in the blade root with cooling air on simple Way is achievable.
  • the now provided plurality of inflow openings for the cooling air in the blade root of the blade also enables a management of the Total cooling air in the blade.
  • a number of inflow openings each separate, through the blade of the blade Assigned sub-channel for cooling air.
  • the subchannels are included preferably completely separated from one another on the cooling air side guided so that different areas of the blade completely independent of other areas of the blade are exposed to cooling air.
  • the rotor blade is expediently designed such that that individual areas of the blade in terms of their operating pressure different partial flows can be supplied by cooling air. This can be particularly simple and an inexpensive way to adapt the cooling air supply system to the by positioning the blade predetermined along the flow path of the working medium specific requirements.
  • the working medium flowing through the gas turbine relaxes namely, when flowing through the gas turbine continuously along its flow path.
  • the operating pressure of the working medium is therefore dependent on the position along the Longitudinal axis of the gas turbine. So with an open cooling a blade the pressure that the cooling air when leaving the rotor blade and when feeding into the have working medium flowing through the gas turbine or must exceed, depending on the position of the blade inside the gas turbine. Beyond that, too one and the same blade the pressure that the cooling air have at their exit from the blade or must exceed, depending on whether the cooling air at the front edge of the respective blade and thus against the Flow direction of the working medium or rather at the Trailing edge of the respective blade and thus in the direction of flow of the working medium emerges.
  • Subchannels for cooling air are arranged, one of which or some on the outlet side at the front edge of the respective blade discharge, and some or one of which is on the outlet side open at the rear edge of the respective blade.
  • the feeding of the rotor blade is possible with comparatively high quality, under high pressure standing cooling air only required for those sub-areas, their assigned subchannels at the front edge the rotor blade open.
  • those areas their assigned subchannels for cooling air on the outlet side open at the rear edge of the blade and thus comparatively lower pressure level requirements Cooling air points, a feed with comparatively lower quality Cooling air possible.
  • a gas turbine with a number of rows of blades each summarized, arranged on a turbine shaft Blades of the type mentioned above can be used with a the overall efficiency of the system is particularly favorable designed cooling system.
  • To keep the cooling air especially with regard to their operating conditions To be able to use it as needed is advantageous an action on the inflow openings of the rotor blades provided with cooling air, the operating pressure of which depends from the position of the respective blade along the Turbine shaft and depending on whether the selected assigned subchannel for cooling air on the outlet side at the front or opens at the rear edge of the respective blade.
  • a plurality of the inlet openings of a moving blade in each case a separate cooling air supply integrated into the turbine shaft assigned.
  • This can be one, for example have a suitable feed chamber integrated in the turbine shaft, the cooling air side expediently with the respective Inflow opening via a guided in the turbine shaft Hole is connected.
  • the reference chamber can then with regard their operating parameters, preferably with regard to their Operating pressure, to the specific requirements of the assigned inlet opening connected subchannel for Cooling air must be adjusted.
  • the reference chamber is expediently connected to one Provide a hole over which a cooling air side Established connection with the respectively assigned inflow opening is.
  • the hole can be directly in the blade root of the respective blade open; but is alternative also a coupling of the respective inflow opening on the cooling air side seen through a in the longitudinal direction of the turbine shaft staggered sealing washer - also as "mini disc" designated - possible.
  • the advantages achieved with the invention are in particular in that by a plurality of in the blade root the blade integrated inflow openings for cooling air a special one in the manner of a parallel flow enables the airfoil to be evenly supplied with cooling air is. In addition, it is just by the majority the inlet openings for cooling air also a targeted continuation from completely separated on the cooling air side Allows partial flows of the cooling air within the blade, whereby each partial flow is individually adapted to that of the adapted to the cooled space given the requirements can be.
  • the outflow side can also be particularly effective of the respective subchannel, where for a particular one with regard to the achievable efficiency Favorable coolant flow especially the operating pressure the cooling air to the boundary conditions specified on the outlet side can be specifically adapted.
  • the position of the moving blade can be along the turbine shaft and on the other hand the outflow direction of the Cooling air from the respective blade, namely either against the flow direction of the working medium or parallel to the direction of flow of the working medium his.
  • the use of comparatively high quality cooling air with comparatively high operating pressure is only required for those subchannels that are on the outlet side the leading edge of the respective blade open.
  • On the other hand can be used for those subchannels on the outlet side at the rear Edge of the respective blade open, comparatively inferior cooling air of comparatively lower Operating pressure are used.
  • the gas turbine 1 has a compressor 2 for Combustion air, a combustion chamber 4 and a turbine 6 for Drive the compressor 2 and a generator, not shown or a work machine. To do this are the turbine 6 and the compressor 2 on a common, also as a turbine rotor designated turbine shaft 8 arranged with the the generator or the working machine is also connected, and which is rotatably mounted about its central axis 9.
  • the combustion chamber 4 is provided with a number of burners 10 Combustion of a liquid or gaseous fuel. It is still not closer to its inner wall provided heat shield elements.
  • the turbine 6 has a number of with the turbine shaft 8 connected, rotatable blades 12.
  • the blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rows of blades.
  • the turbine 6 comprises a number of fixed guide vanes 14, which is also ring-shaped with the formation of Guide vane rows attached to an inner housing 16 of the turbine 6 are.
  • the blades 12 serve to drive the turbine shaft 8 by transfer of momentum from the turbine 6 working medium flowing through M.
  • the guide vanes 14 serve in contrast to the flow of the working medium M between seen two in the flow direction of the working medium M. successive rows of blades or blade rings.
  • a successive pair from a wreath of Guide vanes 14 or a row of guide vanes and from one Wreath of blades 12 or a row of blades is also referred to as the turbine stage.
  • Each guide vane 14 has a vane root 19 which is also designated Platform 18 on which to fix the respective Guide vane 14 on the inner casing 16 of the turbine 6 as a wall element is arranged.
  • the platform 18 is a thermal comparatively heavily loaded component that the outer boundary a hot gas duct for the one flowing through the turbine 6 Working medium M forms.
  • Each blade 12 is in in an analogous manner via a platform 18 Blade root 19 attached to the turbine shaft 8, the Blade root 19 each extends along a blade axis profiled airfoil 20 carries.
  • each guide ring 21 is also hot, flowing through the turbine 6 Working medium M exposed and in the radial direction from the outer end 22 of the blade opposite to it 12 spaced by a gap.
  • the one between neighboring Guide rings 21 arranged guide vane rows serve in particular as cover elements that cover the inner wall 16 or other housing installation parts before a thermal Overuse by the flowing through the turbine 6 protects hot working medium M.
  • the gas turbine 1 for a comparatively high outlet temperature of the working medium emerging from the combustion chamber 4 M designed from about 1200 ° C to 1300 ° C.
  • the blades 12 and Guide vanes 14 designed to be coolable as cooling medium by cooling air K.
  • cooling air K is the area immediately following the combustion chamber 4
  • Gas turbine 1 in Figure 2 is shown enlarged in detail. It can be seen that that flowing out of the combustion chamber 4 Working medium M first on a number of guide vanes 14 meets the so-called first row of guide vanes form and via their respective platform 18 into the combustion chamber 4 are attached. In the direction of flow of the working medium Seen M then follow the first row of blades forming blades 12 which are the second row of blades forming guide vanes 14 and the second row of blades forming blades 12.
  • the blades 12 are for a particularly reliable feeding with cooling air K essentially over the whole Base cross section of their respective blade root 19 away educated.
  • the blade root 19 of the respective moving blade is 12 each with a plurality of inflow openings 24 provided for cooling air K.
  • the inflow openings 24 each Blade 12 are in the embodiment in the Seen in the longitudinal direction of the turbine shaft 8 arranged one behind the other.
  • Each inflow opening 24 is one through the Blade 20 of the respective blade 12 guided Subchannel 26 and 28 assigned for cooling air K.
  • the one in Direction of flow of the working medium M seen front inflow opening 24 assigned subchannel 26 of the respective moving blade 12 is here, starting from the assigned inflow opening 24, meandering through the front part of the respective blade 12 guided, like that in Figure 2 only is shown schematically.
  • the subchannel 26 opens on the outlet side in a number of outlet openings 30 for the cooling air K, which at the in Direction of flow of the working medium M seen front edge 32 of the respective blade 12 are arranged.
  • the communicates in the flow direction of the working medium M seen in each case rear inflow opening 24 of the respective Blade 12 with one in the rear part of each Blade 12 also meandering Subchannel 28.
  • the subchannel 28 opens into an outlet Number of at the rear edge 36 of the respective blade 12 arranged outlet openings 38th
  • each subchannel 26, 28 of each rotor blade 12 are on the cooling air side completely decoupled from each other. So that is Feeding of each subchannel 26, 28 with regard to their operating parameters adapted to the respective requirements Cooling air K enables.
  • this can be taken into account be that the pressure level that the cooling air K in the range of Have outlet openings 30 or 38 or must exceed them, depends on the position of the respective moving blade 12 along the turbine shaft 8 and whether the exit of the Cooling air K against the flow direction of the working medium M or in the direction of flow of the working medium M. Therefore must in particular the supplied to the outlet openings 30 Cooling air K have a higher operating pressure than that Exhaust openings 38 supplied cooling air K.
  • the cooling air supply system includes a first integrated in the turbine shaft 8 Presentation chamber 40, which in the exemplary embodiment according to FIG via a bore 42 guided in the turbine shaft 8 with the seen in the longitudinal direction of the turbine shaft 8 first inflow opening 24 each of the first row of blades Blades 12 is connected.
  • This also includes Cooling air supply system, a second storage chamber 44 for cooling air K. This is seen in the longitudinal direction of the turbine shaft 8 arranged behind the first plenum 40 and also integrated into the turbine shaft 8.
  • the second presentation chamber 44 is on the cooling air side via a bore 46 with the in Seen longitudinal direction of the turbine shaft 8 rear inflow 24 each of the first row of blades Blades 12 connected. Furthermore, the second reference chamber 44 via a bore 48 with the in the longitudinal direction of the Turbine shaft 8 seen front inflow opening 24 of each the blades 12 forming the second row of blades.
  • Presentation chambers can be provided, which by the in the longitudinal direction the turbine shaft 8 seen rear inflow 24 of the blades forming the second row of blades 12 associated bore 50 is indicated.
  • Cooling air routing ensures that each inflow opening 24 each blade 12 has a separate one in the turbine shaft integrated cooling air supply is assigned. Every inflow opening 24 and with it the downstream one Subchannel 26, 28 is thus independent of the other Subchannel 28 or 26 can be supplied with cooling air K. The thus Partial flows of cooling air K formed can therefore be related to the individual adapted conditions specified on the outlet side his.
  • the subchannel 26 is also compared to the Subchannel 28 can be acted upon by cooling air K under higher pressure.
  • the first plenum chamber 40 is used accordingly high-quality, under comparatively high pressure Cooling air K fed.
  • the second submission chamber 44 from which the second subchannel 28 is the first Moving blades row forming blades 12 with cooling air K is supplied, with comparatively inferior, under cooling air K fed at a lower pressure.
  • the total amount of high quality, under particularly high pressure Cooling air K can thus be kept relatively low and only on those areas of the respective blade 12, for which the supply with such high quality cooling air K is actually necessary is.
  • the inflow openings are 24 of the blades 12 in the bottom area of the respective Blade root 19 arranged.
  • the inflow openings 24, as shown in Figure 3, but also in lateral region of the respective blade root 19 is arranged his.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01123797A 2001-10-24 2001-10-24 Ailette de rotor pour une turbine à gaz et turbine à gaz avec des ailettes de rotor Withdrawn EP1306521A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01123797A EP1306521A1 (fr) 2001-10-24 2001-10-24 Ailette de rotor pour une turbine à gaz et turbine à gaz avec des ailettes de rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01123797A EP1306521A1 (fr) 2001-10-24 2001-10-24 Ailette de rotor pour une turbine à gaz et turbine à gaz avec des ailettes de rotor

Publications (1)

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EP1306521A1 true EP1306521A1 (fr) 2003-05-02

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EP01123797A Withdrawn EP1306521A1 (fr) 2001-10-24 2001-10-24 Ailette de rotor pour une turbine à gaz et turbine à gaz avec des ailettes de rotor

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EP (1) EP1306521A1 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1921255A2 (fr) * 2006-11-10 2008-05-14 General Electric Company Moteur de turbine refroidi interétage
EP1921292A2 (fr) * 2006-11-10 2008-05-14 General Electric Company Moteur refroidi de turbine combinée
EP1921256A2 (fr) * 2006-11-10 2008-05-14 General Electric Company Moteur refroidi interétage double
US7870743B2 (en) 2006-11-10 2011-01-18 General Electric Company Compound nozzle cooled engine
EP2358978A1 (fr) * 2008-11-17 2011-08-24 Rolls-Royce Corporation Appareil et procédé de refroidissement d un agencement de partie profilée de turbine dans une turbine à gaz
GR20100100340A (el) * 2010-06-07 2012-01-31 Ανδρεας Ανδριανος Στροβιλοαντιδραστηρας διπλης ροης, μεταβλητου κυκλου, με στροβιλους αντιστροφων φορων, με θαλαμο καυσης χωρις περιοχη διαλυσης, με ψυχομενο στροβιλο υψηλης πιεσης χωρις πτερυγια σταθερου περιβληματος,με θερμοδυναμικο κυκλο πολυ υψηλης θερμοκρασιας και με θερμικο καταλυτη διασπασης υδρογονανθρακων η/και υδατος σε υδρογονο
JP2012507652A (ja) * 2008-11-05 2012-03-29 シーメンス アクティエンゲゼルシャフト ガスタービン用の軸方向に区分化されたガイドベーンマウント
US8668437B1 (en) 2006-09-22 2014-03-11 Siemens Energy, Inc. Turbine engine cooling fluid feed system
JP2015040566A (ja) * 2013-08-21 2015-03-02 ゼネラル・エレクトリック・カンパニイ 動翼エンジェルウイングを冷却する方法およびシステム
WO2016163977A1 (fr) * 2015-04-06 2016-10-13 Siemens Energy, Inc. Communication de fluides de refroidissement entre des profils aérodynamiques de turbine
WO2016163975A1 (fr) * 2015-04-06 2016-10-13 Siemens Energy, Inc. Refroidissement à deux pressions de profils aérodynamiques de turbine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4265590A (en) * 1978-05-20 1981-05-05 Rolls-Royce Limited Cooling air supply arrangement for a gas turbine engine
EP0414028A1 (fr) * 1989-08-25 1991-02-27 Hitachi, Ltd. Turbine à gaz
GB2250548A (en) * 1990-12-06 1992-06-10 Rolls Royce Plc Cooled turbine aerofoil blade
US5387086A (en) * 1993-07-19 1995-02-07 General Electric Company Gas turbine blade with improved cooling
EP0860586A2 (fr) * 1997-02-21 1998-08-26 Mitsubishi Heavy Industries, Ltd. Tubulure de connexion pour le transfert d'un fluide de réfroidissement d'un disque de rotor à une aube d'une turbomachine
JPH10266802A (ja) * 1997-03-21 1998-10-06 Toshiba Corp ガスタービンロータ
EP1013879A1 (fr) * 1998-12-24 2000-06-28 Asea Brown Boveri AG Arbre de turbomachine à refroidssement par liquide
US6094905A (en) * 1996-09-25 2000-08-01 Kabushiki Kaisha Toshiba Cooling apparatus for gas turbine moving blade and gas turbine equipped with same

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4265590A (en) * 1978-05-20 1981-05-05 Rolls-Royce Limited Cooling air supply arrangement for a gas turbine engine
EP0414028A1 (fr) * 1989-08-25 1991-02-27 Hitachi, Ltd. Turbine à gaz
GB2250548A (en) * 1990-12-06 1992-06-10 Rolls Royce Plc Cooled turbine aerofoil blade
US5387086A (en) * 1993-07-19 1995-02-07 General Electric Company Gas turbine blade with improved cooling
US6094905A (en) * 1996-09-25 2000-08-01 Kabushiki Kaisha Toshiba Cooling apparatus for gas turbine moving blade and gas turbine equipped with same
EP0860586A2 (fr) * 1997-02-21 1998-08-26 Mitsubishi Heavy Industries, Ltd. Tubulure de connexion pour le transfert d'un fluide de réfroidissement d'un disque de rotor à une aube d'une turbomachine
JPH10266802A (ja) * 1997-03-21 1998-10-06 Toshiba Corp ガスタービンロータ
EP1013879A1 (fr) * 1998-12-24 2000-06-28 Asea Brown Boveri AG Arbre de turbomachine à refroidssement par liquide

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 1999, no. 01 29 January 1999 (1999-01-29) *

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8668437B1 (en) 2006-09-22 2014-03-11 Siemens Energy, Inc. Turbine engine cooling fluid feed system
US7870743B2 (en) 2006-11-10 2011-01-18 General Electric Company Compound nozzle cooled engine
US7926289B2 (en) 2006-11-10 2011-04-19 General Electric Company Dual interstage cooled engine
EP1921255A3 (fr) * 2006-11-10 2010-10-20 General Electric Company Moteur de turbine refroidi interétage
EP1921256A3 (fr) * 2006-11-10 2010-11-03 General Electric Company Moteur refroidi interétage double
EP1921292A3 (fr) * 2006-11-10 2010-11-03 General Electric Company Moteur refroidi de turbine combinée
EP1921292A2 (fr) * 2006-11-10 2008-05-14 General Electric Company Moteur refroidi de turbine combinée
US7870742B2 (en) 2006-11-10 2011-01-18 General Electric Company Interstage cooled turbine engine
EP1921256A2 (fr) * 2006-11-10 2008-05-14 General Electric Company Moteur refroidi interétage double
EP1921255A2 (fr) * 2006-11-10 2008-05-14 General Electric Company Moteur de turbine refroidi interétage
JP2012507652A (ja) * 2008-11-05 2012-03-29 シーメンス アクティエンゲゼルシャフト ガスタービン用の軸方向に区分化されたガイドベーンマウント
EP2358978A1 (fr) * 2008-11-17 2011-08-24 Rolls-Royce Corporation Appareil et procédé de refroidissement d un agencement de partie profilée de turbine dans une turbine à gaz
EP2358978A4 (fr) * 2008-11-17 2012-06-27 Rolls Royce Corp Appareil et procédé de refroidissement d un agencement de partie profilée de turbine dans une turbine à gaz
US8408866B2 (en) 2008-11-17 2013-04-02 Rolls-Royce Corporation Apparatus and method for cooling a turbine airfoil arrangement in a gas turbine engine
EP2358978B1 (fr) 2008-11-17 2017-06-28 Rolls-Royce Corporation Appareil et procédé de refroidissement d un agencement de partie profilée de turbine dans une turbine à gaz
GR20100100340A (el) * 2010-06-07 2012-01-31 Ανδρεας Ανδριανος Στροβιλοαντιδραστηρας διπλης ροης, μεταβλητου κυκλου, με στροβιλους αντιστροφων φορων, με θαλαμο καυσης χωρις περιοχη διαλυσης, με ψυχομενο στροβιλο υψηλης πιεσης χωρις πτερυγια σταθερου περιβληματος,με θερμοδυναμικο κυκλο πολυ υψηλης θερμοκρασιας και με θερμικο καταλυτη διασπασης υδρογονανθρακων η/και υδατος σε υδρογονο
JP2015040566A (ja) * 2013-08-21 2015-03-02 ゼネラル・エレクトリック・カンパニイ 動翼エンジェルウイングを冷却する方法およびシステム
WO2016163977A1 (fr) * 2015-04-06 2016-10-13 Siemens Energy, Inc. Communication de fluides de refroidissement entre des profils aérodynamiques de turbine
WO2016163975A1 (fr) * 2015-04-06 2016-10-13 Siemens Energy, Inc. Refroidissement à deux pressions de profils aérodynamiques de turbine
CN107438701A (zh) * 2015-04-06 2017-12-05 西门子能源有限公司 涡轮机翼型件的在两个压力下的冷却
JP2018514685A (ja) * 2015-04-06 2018-06-07 シーメンス エナジー インコーポレイテッド タービン翼の二圧力冷却

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