EP2354453B1 - Turbinenmotorkomponente zur adaptiven Kühlung - Google Patents

Turbinenmotorkomponente zur adaptiven Kühlung Download PDF

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Publication number
EP2354453B1
EP2354453B1 EP10152428.8A EP10152428A EP2354453B1 EP 2354453 B1 EP2354453 B1 EP 2354453B1 EP 10152428 A EP10152428 A EP 10152428A EP 2354453 B1 EP2354453 B1 EP 2354453B1
Authority
EP
European Patent Office
Prior art keywords
depression
turbine engine
body portion
back face
passage
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.)
Not-in-force
Application number
EP10152428.8A
Other languages
English (en)
French (fr)
Other versions
EP2354453A1 (de
Inventor
Andrew Shepherd
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 EP10152428.8A priority Critical patent/EP2354453B1/de
Priority to US13/017,350 priority patent/US20110189015A1/en
Publication of EP2354453A1 publication Critical patent/EP2354453A1/de
Application granted granted Critical
Publication of EP2354453B1 publication Critical patent/EP2354453B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/186—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
    • F01D5/14—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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • 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
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life

Definitions

  • the present invention seeks to find a solution in which the time of operation can be stretched further and downtime may be avoided even when oxidation of parts has already occurred, so that repair or replacement of parts can be performed at the next maintenance schedule and still providing a mode of operation with only marginal performance losses.
  • a turbine engine component having a body comprising a first surface exposed to a working fluid of high temperatures during operation, so that erosion and/or corrosion, e.g. particularly oxidation, may take place on the first surface.
  • the body is further comprising a second surface comprising at least one depression, the depression being exposed to a cooling fluid during operation, the depression being oriented such that, starting from the second surface, it deepens in direction of a back face of the first surface.
  • a depression may be in form of a blind hole or a trench.
  • the body also comprises a body portion between the back face and the first surface, wherein a diameter of the depression decreases from the second surface in direction of the back face.
  • the depression can be seen as to have a particularly V-shaped cross section.
  • the invention is not directed to oxidise surfaces of cooling passages. It is directed to scenarios in which a hot surface that is designed to guide the hot fluid - the first surface according to the invention - may oxidise.
  • the depression has a specific shape, so that the diameter of the depression decreases from the second surface in direction of the back face of the first surface.
  • this passage has an exit with a first diameter, as defined by the width of the depression, providing a first amount of cooling fluid. This will stop or slow down further oxidation in the future. Assuming, oxidation will not be prevented completely because the first amount of cooling fluid may not be sufficient to do so, the first surface including the rim of the newly built passage may oxidise further. This results in a further gradual reduction of surface material and also in enlarging the diameter of the cooling passage, due to the specific shape of the depression with its tilted walls.
  • the invention is advantageous because, if the heat will never reach an oxidising temperature, the depression will never become a cooling passage and therefore no performance losses will occur.
  • the aerofoil 1 for example a guide vane or a blade within a turbine section of a gas turbine engine, represents the turbine engine component as defined in the invention and will be present in a working fluid flow 30 during operation.
  • This working fluid flow 30 is indicated as a double arrow and may be a hot gas provided by a combustion chamber located upstream.
  • the aerofoil 1 has a circumferential wall 2 as a body of turbine engine component and a cavity to allow cooling fluid - a cooling fluid flow 31 is indicated via a further arrow - to cool the wall 2 from the inside and to supply cooling holes (not shown in the figure).
  • the depressions 20, 21 are being exposed to the cooling fluid during operation. At the time of installation, the depressions 20, 21 are blind holes and may not supply any cooling fluid to the first surface 10.
  • the first depression 20 has an opening of the first diameter d1 then narrows until the back face 12 is reached with a diameter of the second diameter d2.
  • the width of the material of the body portion 40 is indicated by the width w and may be a fraction of a width of a medium distance between the first surface 10 and the second surface 11.
  • the material degradation of the first surface 10 may continue at a slower pace. This result in further oxidisation, as indicated by a dashed line for a further oxidised first surface 14.
  • the height of the passages 50 will also decrease, which has a direct impact on the width of the passage 50, due to the tilted walls of the passage 50.
  • the throughput of cooling air will increase through the passage 50, because the second diameter d2 indicating the diameter of the passage exit will also increase. This has the consequence that the oxidisation of the first surface 10 will decrease further until a stable point of operation is reached, at which enough cooling air is provided via the passage 50.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (8)

  1. Turbinenmotorkomponente (1), insbesondere Schaufelblatt, mit einem Körper (2), welcher umfasst:
    - eine erste Fläche (10), die während des Betriebs gegenüber einem Arbeitsfluid mit hohen Temperaturen exponiert ist;
    - eine zweite Fläche (11), die wenigstens eine Vertiefung (20, 21, 22, 23, 24, 25, 26) umfasst, wobei die Vertiefung (20, 21, ...) während des Betriebs gegenüber einem Kühlfluid exponiert ist, wobei die Vertiefung (20, 21, ...) derart ausgerichtet ist, dass sie sich, an der zweiten Fläche (11) beginnend, in Richtung einer Rückseite (12) der ersten Fläche (10) senkt;
    - einen Körperabschnitt (40) zwischen der Rückseite (12) und der ersten Fläche (10);
    wobei sich ein Durchmesser (d1, d2) der Vertiefung (20, 21, ...) von der zweiten Fläche (11) aus in Richtung der Rückseite (12) verringert,
    dadurch gekennzeichnet, dass
    der Körperabschnitt (40) aus einem solchen Material besteht und/oder eine solche Breite (w) zwischen der ersten Fläche (10) und der Rückseite (12) der ersten Fläche (10) aufweist, dass im Gebrauch, und wenn er gegenüber einer spezifischen Temperatur exponiert wird, Erosion und/oder Korrosion auf der Seite der ersten Fläche (10) des Körperabschnitts (40) einen Durchlass (50) zu der Vertiefung (20, 21, ...) freilegen,
    und dadurch, dass sich der Durchmesser (d1, d2) der Vertiefung (20, 21, ...) von der zweiten Fläche (11) aus in Richtung der Rückseite (12) derart verringert, dass im Gebrauch eine fortgesetzte Erosion und/oder Korrosion auf der Seite der ersten Fläche (10) des Körperabschnitts (40) eine Aufweitung des Durchlasses (50) zur Folge hat, um eine größere Menge an Kühlfluid hindurchströmen zu lassen.
  2. Turbinenmotorkomponente (1) nach Anspruch 1,
    dadurch gekennzeichnet, dass
    ein dem Körperabschnitt (40) benachbarter Teil des Körpers (2) aus einem weiteren Material besteht, welches weniger anfällig gegen Erosion und/oder Korrosion als der Körperabschnitt (40) ist.
  3. Turbinenmotorkomponente (1) nach Anspruch 2,
    dadurch gekennzeichnet, dass
    das weitere Material eine oxidationsbeständige Beschichtung (60) ist.
  4. Turbinenmotorkomponente (1) nach einem der Ansprüche 1 bis 3,
    dadurch gekennzeichnet, dass
    der freigelegte Durchlass (50) das Kühlfluid zuführt, um eine Kühlung, insbesondere Filmkühlung, einer Umgebung der ersten Fläche (10) zu bewirken.
  5. Turbinenmotorkomponente (1) nach Anspruch 4,
    dadurch gekennzeichnet, dass
    sich der Durchmesser (d1, d2) der Vertiefung (20, 21, ...) von der zweiten Fläche (11) aus in Richtung der Rückseite (12) derart verringert, dass im Gebrauch eine fortgesetzte Aufweitung des Durchlasses (50) aufgrund von Erosion und/oder Korrosion eine zunehmende Menge an hindurchgeströmtem Kühlfluid zur Verfügung stellt, so dass die Temperatur einer Umgebung der ersten Fläche (10) auf einen Wert verringert wird, bei welchem Erosion und/oder Korrosion auf der Seite der ersten Fläche (10) des Körperabschnitts (40) enden.
  6. Gasturbinenmotor, umfassend:
    wenigstens eine Turbinenmotorkomponente (1) nach einem der vorhergehenden Ansprüche.
  7. Gasturbinenmotor nach Anspruch 6,
    dadurch gekennzeichnet, dass
    die wenigstens eine Turbinenmotorkomponente (1) enthalten ist in:
    - einem Leitschaufelblatt und/oder
    - einer Leitschaufelplattform und/oder
    - einem Laufschaufelblatt und/oder
    - einer Laufschaufelplattform und/oder
    - einem Laufschaufeldeckband und/oder
    - einem Übergangskanal zwischen einer Brennkammer und einem Turbinenabschnitt und/oder
    - einer Brennkammer und/oder
    - einem statischen Deckband und/oder
    - einem Hitzeschild und/oder
    - einem Diffusor und/oder
    - einer Abgasanlage.
  8. Verfahren zur adaptiven Kühlung einer Turbinenmotorkomponente (1), wobei das Verfahren die folgenden Schritte umfasst:
    - Zuführen von Kühlfluid zu der Turbinenmotorkomponente (1), die einen Körper aufweist, welcher eine erste Fläche (10), die während des Betriebs gegenüber einem Arbeitsfluid mit hohen Temperaturen exponiert ist, und eine zweite Fläche (11), die eine Vertiefung (20, 21, 22, 23, 24, 25, 26) umfasst, wobei die Vertiefung (20, 21, ...) während des Betriebs gegenüber dem Kühlfluid exponiert ist, wobei die Vertiefung (20, 21, ...) derart ausgerichtet ist, dass sie sich, an der zweiten Fläche (11) beginnend, in Richtung einer Rückseite (12) der ersten Fläche (10) senkt, umfasst, und außerdem einen Körperabschnitt (40) zwischen der Rückseite (12) und der ersten Fläche (10) umfasst, wobei sich ein Durchmesser (d1, d2) der Vertiefung (20, 21, ...) von der zweiten Fläche (11) aus in Richtung der Rückseite (12) verringert;
    - Zuführen von Wärme zu der ersten Fläche (10), so dass Material der ersten Fläche (10) auf der Seite der ersten Fläche (10) des Körperabschnitts (40) erodiert und/oder korrodiert wird, so dass ein Durchlass (50) zu der Vertiefung (20, 21, ...) freigelegt wird, um dem Kühlfluid zu ermöglichen hindurchzuströmen, und derart, dass eine fortgesetzte Erosion und/oder Korrosion auf der Seite der ersten Fläche (10) des Körperabschnitts (40) eine Aufweitung des Durchlasses (50) zur Folge hat, um eine größere Menge an Kühlfluid hindurchströmen zu lassen.
EP10152428.8A 2010-02-02 2010-02-02 Turbinenmotorkomponente zur adaptiven Kühlung Not-in-force EP2354453B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP10152428.8A EP2354453B1 (de) 2010-02-02 2010-02-02 Turbinenmotorkomponente zur adaptiven Kühlung
US13/017,350 US20110189015A1 (en) 2010-02-02 2011-01-31 turbine engine component for adaptive cooling

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10152428.8A EP2354453B1 (de) 2010-02-02 2010-02-02 Turbinenmotorkomponente zur adaptiven Kühlung

Publications (2)

Publication Number Publication Date
EP2354453A1 EP2354453A1 (de) 2011-08-10
EP2354453B1 true EP2354453B1 (de) 2018-03-28

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EP10152428.8A Not-in-force EP2354453B1 (de) 2010-02-02 2010-02-02 Turbinenmotorkomponente zur adaptiven Kühlung

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EP (1) EP2354453B1 (de)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9435208B2 (en) * 2012-04-17 2016-09-06 General Electric Company Components with microchannel cooling
US9617859B2 (en) 2012-10-05 2017-04-11 General Electric Company Turbine components with passive cooling pathways
US10006367B2 (en) * 2013-03-15 2018-06-26 United Technologies Corporation Self-opening cooling passages for a gas turbine engine
US9394798B2 (en) * 2013-04-02 2016-07-19 Honeywell International Inc. Gas turbine engines with turbine airfoil cooling
WO2015015859A1 (ja) * 2013-07-30 2015-02-05 三菱重工業株式会社 蒸気タービンの水分除去装置、及びスリット孔の形成方法
EP2857636A1 (de) * 2013-10-01 2015-04-08 Siemens Aktiengesellschaft Verbesserte Kühlanordnung für eine Turbomaschinenkomponente
EP2873806A1 (de) * 2013-11-14 2015-05-20 Siemens Aktiengesellschaft Durch Wärmedämmschicht verbesserte Kühlanordnung für eine Turbomaschinenkomponente
US9784123B2 (en) 2014-01-10 2017-10-10 Genearl Electric Company Turbine components with bi-material adaptive cooling pathways
EP2937512B1 (de) * 2014-04-23 2020-05-27 United Technologies Corporation Anordnung für ein gasturbinentriebwerk
DE102014207790A1 (de) * 2014-04-25 2015-10-29 Siemens Aktiengesellschaft Kühlfluidkanal
US9718735B2 (en) * 2015-02-03 2017-08-01 General Electric Company CMC turbine components and methods of forming CMC turbine components
US10738622B2 (en) 2016-08-09 2020-08-11 General Electric Company Components having outer wall recesses for impingement cooling
US10662779B2 (en) * 2016-11-17 2020-05-26 Raytheon Technologies Corporation Gas turbine engine component with degradation cooling scheme
US10508553B2 (en) 2016-12-02 2019-12-17 General Electric Company Components having separable outer wall plugs for modulated film cooling
US10927680B2 (en) * 2017-05-31 2021-02-23 General Electric Company Adaptive cover for cooling pathway by additive manufacture
US10760430B2 (en) 2017-05-31 2020-09-01 General Electric Company Adaptively opening backup cooling pathway
US10704399B2 (en) * 2017-05-31 2020-07-07 General Electric Company Adaptively opening cooling pathway
US20180347442A1 (en) * 2017-05-31 2018-12-06 General Electric Company Lattice structure in cooling pathway by additive manufacture
US11041389B2 (en) 2017-05-31 2021-06-22 General Electric Company Adaptive cover for cooling pathway by additive manufacture
KR102230700B1 (ko) * 2017-09-12 2021-03-23 한국기계연구원 가스 터빈용 블레이드
EP3695101A1 (de) 2017-10-13 2020-08-19 General Electric Company Beschichtete komponenten mit adaptiven kühlöffnungen und verfahren zu deren herstellung
US11634990B2 (en) 2018-07-31 2023-04-25 General Electric Company Component with mechanical locking features incorporating adaptive cooling and method of making
US11203939B2 (en) * 2018-12-12 2021-12-21 Raytheon Technologies Corporation Airfoil platform with cooling orifices
US11248790B2 (en) 2019-04-18 2022-02-15 Rolls-Royce Corporation Impingement cooling dust pocket
US11333037B2 (en) 2020-02-06 2022-05-17 Raytheon Technologies Corporation Vane arc segment load path

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090074576A1 (en) * 2006-04-20 2009-03-19 Florida Turbine Technologies, Inc. Turbine blade with cooling breakout passages

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1492049A (en) 1974-12-07 1977-11-16 Rolls Royce Combustion equipment for gas turbine engines
US4136516A (en) 1977-06-03 1979-01-30 General Electric Company Gas turbine with secondary cooling means
IE861475L (en) * 1985-07-03 1987-01-03 Tsnii Kozhevenno Obuvnoi Ptomy Improved coolant passage structure especially for cast rotor¹blades in a combustion turbine
DE3615226A1 (de) * 1986-05-06 1987-11-12 Mtu Muenchen Gmbh Heissgasueberhitzungsschutzeinrichtung fuer gasturbinentriebwerke
GB2259118B (en) 1991-08-24 1995-06-21 Rolls Royce Plc Aerofoil cooling
EP0925426A1 (de) * 1996-09-04 1999-06-30 Siemens Aktiengesellschaft Turbinenschaufel, welche einem heissen gasstrom aussetzbar ist
EP1160352B1 (de) * 2000-05-31 2009-04-22 ALSTOM Technology Ltd Verfahren zum Einstellen der Grösse von Kühllöchern eines Bauteils einer Gasturbine
US6749396B2 (en) * 2002-06-17 2004-06-15 General Electric Company Failsafe film cooled wall
DE10250779A1 (de) 2002-10-30 2004-05-19 Alstom (Switzerland) Ltd. Notkühlsystem für ein hitzebelastetes Bauteil
FR2870560B1 (fr) * 2004-05-18 2006-08-25 Snecma Moteurs Sa Circuit de refroidissement a cavite a rapport de forme eleve pour aube de turbine a gaz
US7186091B2 (en) * 2004-11-09 2007-03-06 General Electric Company Methods and apparatus for cooling gas turbine engine components
US7241107B2 (en) * 2005-05-19 2007-07-10 Spanks Jr William A Gas turbine airfoil with adjustable cooling air flow passages
GB2429515B (en) 2005-08-11 2008-06-25 Rolls Royce Plc Cooling method and apparatus

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090074576A1 (en) * 2006-04-20 2009-03-19 Florida Turbine Technologies, Inc. Turbine blade with cooling breakout passages

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EP2354453A1 (de) 2011-08-10

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