EP1219781A2 - Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine - Google Patents

Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine Download PDF

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Publication number
EP1219781A2
EP1219781A2 EP01128807A EP01128807A EP1219781A2 EP 1219781 A2 EP1219781 A2 EP 1219781A2 EP 01128807 A EP01128807 A EP 01128807A EP 01128807 A EP01128807 A EP 01128807A EP 1219781 A2 EP1219781 A2 EP 1219781A2
Authority
EP
European Patent Office
Prior art keywords
platform
cooling
blade
outlet
turbine blade
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.)
Granted
Application number
EP01128807A
Other languages
German (de)
English (en)
Other versions
EP1219781A3 (fr
EP1219781B1 (fr
Inventor
Alexander Dr. Beeck
Stefan Dr. Florjancic
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Alstom Power NV
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 Alstom Technology AG, Alstom Power NV filed Critical Alstom Technology AG
Publication of EP1219781A2 publication Critical patent/EP1219781A2/fr
Publication of EP1219781A3 publication Critical patent/EP1219781A3/fr
Application granted granted Critical
Publication of EP1219781B1 publication Critical patent/EP1219781B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F05B2240/801—Platforms for stationary or moving blades cooled platforms
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • the invention relates to a device and a method for cooling A platform of a turbine blade, which has a blade root, an airfoil a leading and trailing edge and a blade tip with a platform and which is at least partially penetrated radially by at least one cooling channel, the one with at least one emerging from the platform via an outlet opening Exit channel is connected.
  • Cooling problems of the type mentioned above occur in particular Turbine blades that are used in gas turbine plants.
  • the turbine blades are separated from the inside flows around the combustion chamber generated hot gases.
  • Avoiding existing turbine blades plays the aspect of targeted cooling of gas turbine blades in the conception and design of such systems a major role.
  • part of the cooling within the Compressor stage specifically derived and thus compressed air for cooling purposes withdrawn from the further combustion process. Rather, the cooling air passes over Cooling channel systems, both in rotating and stationary Plant components are provided in the area of the turbine stages around the there to cool the system components directly exposed to the hot gases.
  • Cooling of the rotor assembly in a variety of axially one behind the other arranged rows of moving blades, have the Blades radial cooling channels through which from the side of the rotor assembly Cooling air fed in is guided longitudinally to the turbine blades, which are passed through cooling air openings correspondingly provided on the blade surface emerge and mixes with the hot gases.
  • turbine blades point radially to the rotor assembly facing side platforms or so-called shrouds to Leakage flows between the turbine blade tips and the to train fixed system components.
  • platforms and shrouds contribute to vibrations that occur train along the turbine blades during operation of the gas turbine, dampen effectively.
  • a cooling duct system is used in US 5,482,435 for cooling such platforms described within a platform through which cooling air is conducted and thus effectively contributes to cooling the platform.
  • the cooling air passes through a central cooling channel oriented radially to the turbine blade in the area of the platform, in which the cooling air escapes through two sub-channels.
  • the one in the platform The partial cooling ducts provided extend in such a way that those from the platform emerging cooling air almost perpendicular to the main flow direction of the Gas turbine flowing hot gases is oriented. However, on the one hand, this causes that the flow behavior of the main flow is considerably irritated, causing the aerodynamic efficiency is permanently impaired.
  • the cooling air emerging from the platform makes no contribution to the energy gain or contribute to improved energy conversion within the gas turbine.
  • the invention has for its object a device and a method for Cooling a platform of a turbine blade according to the preamble of Claim 1 to develop such that, on the one hand, effective cooling of the Platform is ensured, but on the other hand it is ensured that the Main flow, which lies directly on the turbine blade, as little as possible is affected to the aerodynamic conditions within the Fluid machine not to deteriorate. Rather, it should be achieved that in addition to the above effective cooling effect, an additional energy gain can be achieved by the exit of the cooling air from the platform.
  • a device for cooling a platform is a Turbine blade, which has a blade root, a blade with an attachment and Trailing edge, as well as a blade tip with a platform and the radial is at least partially penetrated by at least one cooling channel, which with at least one exiting the platform via an outlet opening Outlet channel is connected, further developed in that the outlet channel has a longitudinal channel direction adjacent to the outlet opening, which is in projection along the turbine blade largely coparallel to the direction of flow of a Exit flow immediately overflowing local flow field of a relative mass flow flowing past the turbine blade.
  • the cooling device according to the invention is on all turbine blades applicable, which are provided with a platform.
  • the with the invention The advantages associated with the measure are shown below using the example of Turbine guide vane explained in more detail within a gas turbine system. Of course, however, it is possible to use the cooling device according to the invention also to be used on platforms of stationary guide vanes.
  • the Measure according to the invention is not based on the use of turbine blades limited within gas turbine stages of gas turbine plants, but can be used in all turbomachines in which corresponding Cooling problems occur, for example within compressors or the like Turbomachinery.
  • the inventive arrangement of the outlet channel within the platform, by the cooling air exits through an outlet opening is oriented according to the invention in such a way so the cooling air that flows out of the platform is preferably the same Has flow direction with which the main flow of hot gases Turbine blade and thus also flows around the platform itself.
  • the Outlet opening of the outlet channel on the turbine blade radially provided facing away from the top of the platform preferably runs the Cooling duct inclined slightly to the top of the platform.
  • the Outlet opening attached to the downstream edge of the platform be so that the cooling air flowing out of the platform is coparallel to the die Hot gases flowing around the platform is oriented.
  • there is Outlet opening of the cooling channel on the platform preferably downstream Leading edge of the turbine blade so that it is guaranteed that one is possible long cooling channel section runs within the platform, so that one if possible effective cooling effect can be achieved.
  • Cooling arrangements within the platform which in the case of Turbine blades due to their radial spacing from the axis of rotation subjected to high centrifugal forces make an important contribution to the creep behavior of the blade material in the area of the platform increases positively influence, i.e. Material warping or deformation by softening the Materials under the influence of high centrifugal forces are effective cooling measures reduced or eliminated.
  • Through the Cooling measure according to the invention within the platform can creep material be significantly restricted.
  • the main advantage associated with this is the additional energy gain that comes with the targeted coparallel flow exit of the cooling air relative to the turbine blade mainstream flowing around, can be achieved. So it could be proven be that the cooling air coming from the cooling duct oriented according to the invention flows out through the outlet opening on the platform to a measurable Contributes to energy gain, which is characterized by the interaction of an additional Impulse contribution to the drive of the turbine blade and one comparatively negligible irritation or disturbance of the main flow of the Turbine blade flows around hot gases.
  • a plurality of appropriately oriented cooling channels are preferred introduced within a platform, whereby the above described beneficial effects in terms of cooling effect and additional energy contribution let increase. Further details regarding possible exemplary embodiments can be found can be found in detail in the following exemplary embodiments.
  • A are suitable for producing the platform designed according to the invention
  • a variety of known techniques around the cooling channel or a variety bring appropriately oriented cooling channels into the platform.
  • EDM processes Electro-Discharge Machining
  • laser beam laser beam
  • electrochemical Processes electrochemical Processes
  • water jet techniques water jet techniques
  • Figure 1 is a plan view of an axial arrangement consisting of a Guide vane row 1 and one downstream in the flow direction Blade row 2 shown.
  • the platforms 3 are one Guide vane 4 and a moving blade 5 can be seen, the guide vane 4 or blade 5 facing away from the viewer perpendicular to the plane of the drawing extends.
  • the main flow 6 through the turbine blades from the pure Redirected axial direction. So is the main flow 6 immediately after flowing through the guide vane row 1 directed upward in the circumferential direction, whereas the Main flow after flow around the blade row 2 against the direction of rotation is distracted.
  • the inclination of the flow direction in relation to the axial direction becomes immediately downstream of a turbine blade row essentially due to the inclination the turbine blades relative to the main flow and the Circumferential speed conditional.
  • the platforms 3 there are cooling channels 7, preferably in the region of the downstream end edge 8 of the platforms 3 arranged such that cooling air parallel to the main flow 6 from the Cooling channels 7 escapes.
  • the longitudinal axes of the cooling channels 7 are parallel to Turbine airfoil in the area immediately upstream of the trailing edge 9 arranged.
  • FIG 2 is the upper part of a longitudinal section through a turbine blade shown, which is designed for example as a rotor blade 5 and in its upper Area provides a platform 3.
  • the rotor blade 5 has a radial direction extending main cooling duct 10, in the cooling air on the part of the shown blade root in the area of the platform 3.
  • the main cooling channel 10 opens on one side a plurality of cooling channels 11, which are inclined run to the platform top 12 and there is an outlet opening 13 there provide. Cooling air through the outlet channels 11 through the respective Exit opening 13 on the platform top 3 exits is slightly oblique to Platform top 12, however, directed in the flow direction of the main flow 6.
  • Further cooling channels 14 open out via corresponding further outlet openings the platform top and are appropriately provided through additional Cooling air channels 15 supplied with cooling air.
  • the platform 3 of the moving blade 5 shown in FIG. 2 typically sees one trained labyrinth seal 16 before, directly below the cooling channel volume 17 with corresponding downstream outlet 18 is provided.
  • FIG. 3 shows a top view of a platform 3, under which, in Extending in the longitudinal direction, a moving blade 5 is provided.
  • the blade 5 has various hollow channels extending along the turbine blade, from which flows out of the hollow duct 10 cooling air in the direction of the platform.
  • Immediately at the hollow channel 10 formed as a cooling channel includes Cooling air system through which the individual cooling channels 13 and 14 with appropriate cooling air is supplied. The cooling air flows along the individual Channels indicated arrow directions and occurs at the corresponding Exit openings 13, 14 on the top 12 of the platform 3.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01128807A 2000-12-22 2001-12-04 Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine Expired - Lifetime EP1219781B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10064265 2000-12-22
DE10064265A DE10064265A1 (de) 2000-12-22 2000-12-22 Vorrichtung und Verfahren zur Kühlung einer Plattform einer Turbinenschaufel

Publications (3)

Publication Number Publication Date
EP1219781A2 true EP1219781A2 (fr) 2002-07-03
EP1219781A3 EP1219781A3 (fr) 2004-01-21
EP1219781B1 EP1219781B1 (fr) 2007-05-02

Family

ID=7668438

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01128807A Expired - Lifetime EP1219781B1 (fr) 2000-12-22 2001-12-04 Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine

Country Status (3)

Country Link
US (1) US6641360B2 (fr)
EP (1) EP1219781B1 (fr)
DE (2) DE10064265A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1630354A2 (fr) 2004-08-25 2006-03-01 Rolls-Royce Plc Aube refroidie de turbine à gaz
CN101482032A (zh) * 2008-01-10 2009-07-15 通用电气公司 涡轮叶片叶冠
WO2012007250A1 (fr) * 2010-07-15 2012-01-19 Siemens Aktiengesellschaft Aube directrice pour turbine à gaz à plate-forme refroidie
EP2607629A1 (fr) * 2011-12-22 2013-06-26 Alstom Technology Ltd Aube de turbine caréné dotée d'un port de sortie d'air de refroidissement en bout d'aube et procédé associé de fabrication
RU2575260C2 (ru) * 2010-07-15 2016-02-20 Сименс Акциенгезелльшафт Сопловая лопатка с охлаждаемой платформой для газовой турбины
EP3163025A1 (fr) * 2015-10-27 2017-05-03 General Electric Company Aube de turbine avec fenêtre des soufflage dans le voile

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GB0228443D0 (en) * 2002-12-06 2003-01-08 Rolls Royce Plc Blade cooling
US6945749B2 (en) * 2003-09-12 2005-09-20 Siemens Westinghouse Power Corporation Turbine blade platform cooling system
US7114339B2 (en) * 2004-03-30 2006-10-03 United Technologies Corporation Cavity on-board injection for leakage flows
EP1591626A1 (fr) * 2004-04-30 2005-11-02 Alstom Technology Ltd Aube de turbine à gaz
DE102004037331A1 (de) * 2004-07-28 2006-03-23 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenrotor
US7131817B2 (en) * 2004-07-30 2006-11-07 General Electric Company Method and apparatus for cooling gas turbine engine rotor blades
US7144215B2 (en) * 2004-07-30 2006-12-05 General Electric Company Method and apparatus for cooling gas turbine engine rotor blades
US7198467B2 (en) * 2004-07-30 2007-04-03 General Electric Company Method and apparatus for cooling gas turbine engine rotor blades
AU2005284134B2 (en) * 2004-09-16 2008-10-09 General Electric Technology Gmbh Turbine engine vane with fluid cooled shroud
US7186089B2 (en) * 2004-11-04 2007-03-06 Siemens Power Generation, Inc. Cooling system for a platform of a turbine blade
US7708525B2 (en) * 2005-02-17 2010-05-04 United Technologies Corporation Industrial gas turbine blade assembly
US7309212B2 (en) * 2005-11-21 2007-12-18 General Electric Company Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge
US7416391B2 (en) * 2006-02-24 2008-08-26 General Electric Company Bucket platform cooling circuit and method
CN100513630C (zh) * 2006-03-24 2009-07-15 统宝光电股份有限公司 蒸镀系统
US7686581B2 (en) * 2006-06-07 2010-03-30 General Electric Company Serpentine cooling circuit and method for cooling tip shroud
US7534088B1 (en) 2006-06-19 2009-05-19 United Technologies Corporation Fluid injection system
US7946816B2 (en) * 2008-01-10 2011-05-24 General Electric Company Turbine blade tip shroud
US8147197B2 (en) * 2009-03-10 2012-04-03 Honeywell International, Inc. Turbine blade platform
US8079814B1 (en) * 2009-04-04 2011-12-20 Florida Turbine Technologies, Inc. Turbine blade with serpentine flow cooling
US8356978B2 (en) * 2009-11-23 2013-01-22 United Technologies Corporation Turbine airfoil platform cooling core
US9630277B2 (en) * 2010-03-15 2017-04-25 Siemens Energy, Inc. Airfoil having built-up surface with embedded cooling passage
US8356975B2 (en) * 2010-03-23 2013-01-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured vane platform
US9976433B2 (en) 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
US8636470B2 (en) 2010-10-13 2014-01-28 Honeywell International Inc. Turbine blades and turbine rotor assemblies
JP5916294B2 (ja) * 2011-04-18 2016-05-11 三菱重工業株式会社 ガスタービン動翼及びその製造方法
EP2959130B1 (fr) 2013-02-19 2019-10-09 United Technologies Corporation Aube d'une turbine à gaz, noyau pour la fabrication de l'aube, et méthode de fabrication du noyau
US10001013B2 (en) 2014-03-06 2018-06-19 General Electric Company Turbine rotor blades with platform cooling arrangements
US10184342B2 (en) * 2016-04-14 2019-01-22 General Electric Company System for cooling seal rails of tip shroud of turbine blade
EP3351341A1 (fr) * 2017-01-23 2018-07-25 Siemens Aktiengesellschaft Procédé de fabrication d'un espace creux dans une plate-forme d'aube

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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1630354A2 (fr) 2004-08-25 2006-03-01 Rolls-Royce Plc Aube refroidie de turbine à gaz
EP1630354A3 (fr) * 2004-08-25 2009-10-28 Rolls-Royce Plc Aube refroidie de turbine à gaz
CN101482032A (zh) * 2008-01-10 2009-07-15 通用电气公司 涡轮叶片叶冠
WO2012007250A1 (fr) * 2010-07-15 2012-01-19 Siemens Aktiengesellschaft Aube directrice pour turbine à gaz à plate-forme refroidie
RU2575260C2 (ru) * 2010-07-15 2016-02-20 Сименс Акциенгезелльшафт Сопловая лопатка с охлаждаемой платформой для газовой турбины
US9856747B2 (en) 2010-07-15 2018-01-02 Siemens Aktiengesellschaft Nozzle guide vane with cooled platform for a gas turbine
EP2607629A1 (fr) * 2011-12-22 2013-06-26 Alstom Technology Ltd Aube de turbine caréné dotée d'un port de sortie d'air de refroidissement en bout d'aube et procédé associé de fabrication
EP3163025A1 (fr) * 2015-10-27 2017-05-03 General Electric Company Aube de turbine avec fenêtre des soufflage dans le voile
CN106968718A (zh) * 2015-10-27 2017-07-21 通用电气公司 具有护罩中的出口路径的涡轮轮叶
US10508554B2 (en) 2015-10-27 2019-12-17 General Electric Company Turbine bucket having outlet path in shroud
US11078797B2 (en) 2015-10-27 2021-08-03 General Electric Company Turbine bucket having outlet path in shroud

Also Published As

Publication number Publication date
US6641360B2 (en) 2003-11-04
EP1219781A3 (fr) 2004-01-21
DE10064265A1 (de) 2002-07-04
DE50112433D1 (de) 2007-06-14
US20020098078A1 (en) 2002-07-25
EP1219781B1 (fr) 2007-05-02

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