EP2384393B1 - Gekühlte schaufel für eine gasturbine - Google Patents

Gekühlte schaufel für eine gasturbine Download PDF

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Publication number
EP2384393B1
EP2384393B1 EP10701389.8A EP10701389A EP2384393B1 EP 2384393 B1 EP2384393 B1 EP 2384393B1 EP 10701389 A EP10701389 A EP 10701389A EP 2384393 B1 EP2384393 B1 EP 2384393B1
Authority
EP
European Patent Office
Prior art keywords
flow
pressure
trailing edge
cooling
flow direction
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.)
Active
Application number
EP10701389.8A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2384393A1 (de
Inventor
Jörg KRÜCKELS
Thomas Heinz-Schwarzmaier
Brian Kenneth Wardle
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
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Publication date
Application filed by Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
Publication of EP2384393A1 publication Critical patent/EP2384393A1/de
Application granted granted Critical
Publication of EP2384393B1 publication Critical patent/EP2384393B1/de
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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
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence

Definitions

  • the present invention relates to the field of gas turbines. It relates to a cooled blade for a gas turbine according to the preamble of claim 1.
  • the invention aims to remedy this situation. It is therefore an object of the invention to provide a cooled blade for a gas turbine of the type mentioned, which avoids the disadvantages of previous blades and at the same time characterized by low aerodynamic losses and a significantly reduced consumption of cooling air.
  • the object is solved by the entirety of the features of claim 1. It is essential for the inventive solution that the pressure-side wall ends in the flow direction to form a pressure-side lip at a distance from the trailing edge, such that the cooling air exits the interior of the pressure side, that the interior at a distance from the trailing edge by a Variety of parallel to the flow direction oriented ribs is divided into a plurality of parallel cooling channels, which cause a high pressure drop, and in which turbulators are arranged to increase the cooling effect, and that shortly before the exit of the cooling air from the interior in the flow path of the cooling air across distributed to the flow direction, a plurality of flow barriers are provided.
  • the invention is characterized in that the linear density of the flow barriers is smaller than the linear density of the ribs.
  • the flow barriers each have a teardrop-shaped edge contour, wherein the pointed end points in the flow direction.
  • the invention is characterized in that between the cooling channels and the flow barriers in a two-dimensional grid arrangement, a plurality of pins is arranged, which extend transversely to the flow direction between the suction side and pressure side wall through the interior.
  • the Figures 1 and 2 show the internal structure of the airfoil 24 of a blade 10 for a gas turbine according to an embodiment of the invention.
  • the blade 10 has a (convex) suction side 15 and a (concave) pressure side 16, of which in Fig. 1 only the portions lying near the trailing edge 13 are shown.
  • On the suction side 15, the airfoil 24 is delimited by a first wall 11, on the pressure side 16 by a second wall 12.
  • the two walls 11, 12 enclose an interior space 14, which is flowed through by cooling air for cooling the airfoil 24.
  • the hot gas of the turbine flows on the airfoil 24 in one of the (in Fig. 1 not shown) leading edge to the trailing edge 13 pointing flow direction 25 over.
  • the cooling air flows in the same direction through the interior 14 and exits Bech the trailing edge 13 of the blade 10 from.
  • the trailing edge 13 is formed by the end of the suction-side wall 11.
  • the pressure-side wall 12 terminates at a distance in front of this trailing edge 13, so that the cooling air in the resulting gap on the pressure side 16 exits even before the trailing edge 13 and a film cooling the Trailing edge 13 causes.
  • the staggered arrangement of the edges of the two walls 11 and 12 creates a particularly thin cooled trailing edge 13, which significantly reduces the aerodynamic losses at the trailing edge 13.
  • the supplied inside the blade 10 cooling air is sent on its way to the trailing edge 13, first by a plurality of parallel, oriented in the flow direction 25 cooling channels 23, which are formed by axial ribs 17 between the two walls 11 and 12.
  • cooling channels 23 turbulators 18 are arranged in the form of oblique ribs on the inner sides of the walls 11, 12, through which the heat exchange with the walls 11, 12 is increased.
  • pins 19 On the cooling channels 23 follow distributed in a kind of lattice structure arranged pins 19 which, like the axial ribs 17, extend between the two walls 11, 12 and improve the cooling of the wall in this area.
  • the cooling air passes through a single row of drop-shaped flow barriers 20 and then exits from the blade 10 between the pressure side lip 21 and the trailing edge 13 on the pressure side 16.
  • the cross-sectional shape of these flow barriers 20 is not limited to a drop shape. Other forms of flow may be used on a case by case basis. If the flow in a certain direction or strength to be influenced, the flow barriers 20 are designed accordingly.
  • the linear density of the flow barriers 20 is less than the linear density of the axial ribs 17. However, this is again not necessarily understand, because depending on the design, the density of the flow barriers 20 may be equal to or greater than the linear density of the axial ribs 17 are selected ,
  • a series of film cooling holes 22 is additionally provided in front of the cooling channels 23, exits through the cooling air on the pressure side 16 and forms a cooling film there.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10701389.8A 2009-01-30 2010-01-29 Gekühlte schaufel für eine gasturbine Active EP2384393B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH00142/09A CH700321A1 (de) 2009-01-30 2009-01-30 Gekühlte schaufel für eine gasturbine.
PCT/EP2010/051112 WO2010086419A1 (de) 2009-01-30 2010-01-29 Gekühlte schaufel für eine gasturbine

Publications (2)

Publication Number Publication Date
EP2384393A1 EP2384393A1 (de) 2011-11-09
EP2384393B1 true EP2384393B1 (de) 2017-06-28

Family

ID=40602892

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10701389.8A Active EP2384393B1 (de) 2009-01-30 2010-01-29 Gekühlte schaufel für eine gasturbine

Country Status (6)

Country Link
US (1) US8721281B2 (ru)
EP (1) EP2384393B1 (ru)
CH (1) CH700321A1 (ru)
ES (1) ES2639735T3 (ru)
RU (1) RU2538978C2 (ru)
WO (1) WO2010086419A1 (ru)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8439628B2 (en) * 2010-01-06 2013-05-14 General Electric Company Heat transfer enhancement in internal cavities of turbine engine airfoils
EP2426317A1 (de) * 2010-09-03 2012-03-07 Siemens Aktiengesellschaft Turbinenschaufel für eine Gasturbine
US9249675B2 (en) * 2011-08-30 2016-02-02 General Electric Company Pin-fin array
US8840371B2 (en) * 2011-10-07 2014-09-23 General Electric Company Methods and systems for use in regulating a temperature of components
EP2682565B8 (en) 2012-07-02 2016-09-21 General Electric Technology GmbH Cooled blade for a gas turbine
GB201311333D0 (en) 2013-06-26 2013-08-14 Rolls Royce Plc Component for use in releasing a flow of material into an environment subject to periodic fluctuations in pressure
CN108349145B (zh) * 2015-11-03 2021-05-07 帝斯克玛股份有限公司 具有集成式密封销/伸展杆和多种密封几何结构的成型头
JP6671149B2 (ja) 2015-11-05 2020-03-25 三菱日立パワーシステムズ株式会社 タービン翼及びガスタービン、タービン翼の中間加工品、タービン翼の製造方法
RU171631U1 (ru) * 2016-09-14 2017-06-07 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Охлаждаемая лопатка турбины
RU2684355C1 (ru) * 2018-07-05 2019-04-08 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Ротор турбины низкого давления (ТНД) газотурбинного двигателя (варианты), узел соединения вала ротора с диском ТНД, тракт воздушного охлаждения ротора ТНД и аппарат подачи воздуха на охлаждение лопаток ротора ТНД
RU2691867C1 (ru) * 2018-07-05 2019-06-18 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Способ охлаждения лопатки ротора турбины низкого давления (ТНД) газотурбинного двигателя и лопатка ротора ТНД, охлаждаемая этим способом
CN109139128A (zh) * 2018-10-22 2019-01-04 中国船舶重工集团公司第七0三研究所 一种船用燃气轮机高压涡轮导叶冷却结构
CN114109515B (zh) * 2021-11-12 2024-01-30 中国航发沈阳发动机研究所 一种涡轮叶片吸力面冷却结构

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Publication number Priority date Publication date Assignee Title
US4303374A (en) * 1978-12-15 1981-12-01 General Electric Company Film cooled airfoil body
US5288207A (en) * 1992-11-24 1994-02-22 United Technologies Corporation Internally cooled turbine airfoil
RU2083851C1 (ru) * 1993-02-03 1997-07-10 Московский авиационный технологический институт им.К.Э.Циалковского Охлаждаемая лопатка газовой турбины
DE19963349A1 (de) 1999-12-27 2001-06-28 Abb Alstom Power Ch Ag Schaufel für Gasturbinen mit Drosselquerschnitt an Hinterkante
US6599092B1 (en) * 2002-01-04 2003-07-29 General Electric Company Methods and apparatus for cooling gas turbine nozzles
US6602047B1 (en) * 2002-02-28 2003-08-05 General Electric Company Methods and apparatus for cooling gas turbine nozzles
GB2411698A (en) * 2004-03-03 2005-09-07 Rolls Royce Plc Coolant flow control in gas turbine engine
US7121787B2 (en) * 2004-04-29 2006-10-17 General Electric Company Turbine nozzle trailing edge cooling configuration
RU2267616C1 (ru) * 2004-05-21 2006-01-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Охлаждаемая лопатка турбины
US7575414B2 (en) * 2005-04-01 2009-08-18 General Electric Company Turbine nozzle with trailing edge convection and film cooling
US7438527B2 (en) * 2005-04-22 2008-10-21 United Technologies Corporation Airfoil trailing edge cooling

Also Published As

Publication number Publication date
CH700321A1 (de) 2010-07-30
RU2011135948A (ru) 2013-03-10
US8721281B2 (en) 2014-05-13
EP2384393A1 (de) 2011-11-09
WO2010086419A1 (de) 2010-08-05
US20120020787A1 (en) 2012-01-26
ES2639735T3 (es) 2017-10-30
RU2538978C2 (ru) 2015-01-10

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