EP2754857A1 - Ensemble de refroidissement, écran thermique statorique, aube mobile et aube statorique associés pour un moteur à turbine à gaz - Google Patents

Ensemble de refroidissement, écran thermique statorique, aube mobile et aube statorique associés pour un moteur à turbine à gaz Download PDF

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Publication number
EP2754857A1
EP2754857A1 EP13150882.2A EP13150882A EP2754857A1 EP 2754857 A1 EP2754857 A1 EP 2754857A1 EP 13150882 A EP13150882 A EP 13150882A EP 2754857 A1 EP2754857 A1 EP 2754857A1
Authority
EP
European Patent Office
Prior art keywords
wall
junction
cooling configuration
cooling
area
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Withdrawn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
EP13150882.2A
Other languages
German (de)
English (en)
Inventor
Herbert Brandl
Magali Cochet
Christoph Didion
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP13150882.2A priority Critical patent/EP2754857A1/fr
Publication of EP2754857A1 publication Critical patent/EP2754857A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Definitions

  • the present invention relates to an impingement cooling configuration for T-junctions between a first wall and a second wall, the second wall requiring cooling because it is subjected to high temperatures on one side, particularly in gas turbine applications, the configuration of the invention improving heat transfer and providing a longer lifetime of the cited T-junctions.
  • Components of gas turbines are subjected to very high temperature and pressure conditions, and sometimes also to a high vibration environment, which limit the lifetime of the mentioned components.
  • the blades of gas turbines are often the limiting component of gas turbines, as they are subjected to very strenuous environments inside the gas turbine, facing high temperatures, high stresses and potentially high vibration environments, which can lead to the blade failures.
  • the components that are particularly subjected to harsh conditions in gas turbines are made of high strength materials to withstand these conditions.
  • Another solution aside from the use of better materials, is to cool these components, thus decreasing their operating temperature, typically by convection cooling, passing cooling air through passages internal to the components to be cooled, so that heat is transferred by conduction first, and then by convection into the air flowing inside of the components.
  • Impingement cooling that works by hitting the inner surface of the component that has to be cooled with high velocity air that passes typically through an impingement sheet, allowing more heat to be transferred than regular convection cooling does.
  • Impingement cooling is often used in certain areas of the gas turbine, typically subjected to very strong conditions, such as T-junctions between a web and an airfoil.
  • T-junctions cannot be properly cooled even if using this known solution of impingement cooling, as cooling is effected mainly by heat conduction through the web part, such that temperature hot spots at T-junctions subjected to a high temperature and not being properly cooled are created, causing increased stresses and reduced lifetime of these parts.
  • US Patent 6,139,269 discloses a convectively cooled turbine blade having two distinct cooling air passage systems in order to improve heat transfer; however, T-junctions between the web and the airfoil still have hot spots with higher temperature, limiting lifetime of the parts.
  • the present invention is intended to solve the above-mentioned disadvantages and limitations in the prior art, as it will be further explained.
  • the present invention relates to an impingement cooling configuration for T-junctions between a first wall, for example a web or a hook, and a second wall, for example an airfoil, the second wall requiring cooling because it is subjected to high temperatures on one side, typically subjected to hot gas, particularly in gas turbines.
  • the cooling configuration of the invention improves heat transfer and provides a longer lifetime of the cited T-junctions.
  • the configuration of the invention comprises a plurality of longitudinally spaced reinforcing ribs, located at least on one of the areas where the first wall and the second wall are joined. According to another embodiment, these reinforcing ribs can be located on both areas where the first wall and the second wall are joined.
  • An impingement sheet with a plurality of impingement holes is located over the T-junction, on the side of the first wall (opposite to the side facing the high temperatures typically from hot gas), such that cooling air is blown through the impingement holes in the impingement sheet. With this configuration, the cooling air blown impacts into the cavities generated between the longitudinally spaced ribs into the T-junction.
  • the wall thickness in both junction areas where the first wall and the second wall are joined forming a junction having a cross-section with a T-shape is reduced longitudinally, all along the second wall.
  • Another possible embodiment of the invention contemplates the reduction of the thickness in both junction areas where the first wall and the second wall are joined forming a junction having a cross-section with a T-shape, longitudinally, all along the second wall, and vertically, all along the first wall.
  • the T-junction areas formed between the first wall and the second wall are provided with improved heat transfer, thus allowing a longer lifetime of these parts.
  • the present invention discloses an impingement cooling configuration for a T-junction 100 between a first wall 1 (e.g. web) and a second wall 2 (e.g. airfoil), the second wall 2 requiring cooling as it is subjected to high temperatures on one side.
  • the cooling configuration of the invention is particularly used in gas turbines, and the side of the second wall 2 requiring cooling is a hot gas surface 3.
  • the cooling configuration of the invention improves heat transfer and provides a longer lifetime of the cited T-junction 100.
  • cooling of both first 101 and second 102 areas of the T-junction 100 is made by means of an air flow 400 passing through a plurality of holes 40 in an impingement sheet 4.
  • cooling of the first and second areas 101 and 102 of the T-junction 100 is not properly done, such that hot spots 6 appear, as shown in Figure 2 .
  • the joint of a first wall 1 and a second wall 2 forms a T-junction 100 having two areas, a first area 101 and a second area 102, located opposite the hot gas surface 3.
  • the configuration of the invention comprises a plurality of longitudinally spaced reinforcing ribs 5, located at least on one of the first area 101 or the second area 102, these plurality of longitudinally spaced reinforcing ribs 5 being preferably located on both first area 101 and second area 102.
  • An impingement sheet 4 with a plurality of impingement holes 40 is located over the T-junction 100, on the side opposite to the side facing the hot gas (hot gas surface 3), such that a cooling air flow 400 is blown through the impingement holes 40 in the impingement sheet 4.
  • the cooling air flow 400 impinges into the cavities 7 generated between the longitudinally spaced ribs 5 on the first area 101, on the second area 102 or on both areas, 101 and 102. Therefore, into the cavities 7 created between the T-junction 100 and the reinforcing ribs 5, the impingement cooling air flow 400 is much better utilized because the cooling surface area is increased.
  • the configuration of the invention shown in Figures 3a, 3b and 4 reduces the wall thickness in both junction first and second areas 101 and 102, compared to the wall thickness in the prior art configuration shown in Figure 1 .
  • the wall thickness is reduced longitudinally, preferably all along the second wall 2, as shown in Figure 4 .
  • the wall thickness can be reduced longitudinally, all along the second wall 2, and also vertically, all along the first wall 1.
  • the cooling air flow 400 impinges on a reduced wall thickness area (101, 102) of the T-junction 100, impinging into the cavities 7 generated between the longitudinally spaced ribs 5, first wall 1 and second wall 2.
  • the impingement cooling air flow 400 is much better utilized in both the first area 101 and the second area 102 thanks to the plurality of cavities 7, as the cooling surface area is increased.
  • the reinforcing ribs 5 recover some of the stiffness sacrificed by the wall thickness reduction.
  • the temperature hot spot 8 at the middle of the web 1 is significantly reduced (in special cases even more than 30°C), as shown in the graph of Figure 2 . Furthermore, this configuration allows lifetime at the T-junction 100 to be increased by around 50%, compared to its lifetime in the prior art, as shown in Figure 1 .
  • T-junction 100 of the present invention has been described with reference to stator heat shields in a gas turbine, as shown in Figures 3a and 3b , the configuration of the invention can be applied to any T-junction design, for example to gas turbine vanes (shown in Figure 5 ) or to gas turbine blades (shown in Figure 6 ).
EP13150882.2A 2013-01-10 2013-01-10 Ensemble de refroidissement, écran thermique statorique, aube mobile et aube statorique associés pour un moteur à turbine à gaz Withdrawn EP2754857A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13150882.2A EP2754857A1 (fr) 2013-01-10 2013-01-10 Ensemble de refroidissement, écran thermique statorique, aube mobile et aube statorique associés pour un moteur à turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13150882.2A EP2754857A1 (fr) 2013-01-10 2013-01-10 Ensemble de refroidissement, écran thermique statorique, aube mobile et aube statorique associés pour un moteur à turbine à gaz

Publications (1)

Publication Number Publication Date
EP2754857A1 true EP2754857A1 (fr) 2014-07-16

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13150882.2A Withdrawn EP2754857A1 (fr) 2013-01-10 2013-01-10 Ensemble de refroidissement, écran thermique statorique, aube mobile et aube statorique associés pour un moteur à turbine à gaz

Country Status (1)

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EP (1) EP2754857A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3048262A1 (fr) 2015-01-20 2016-07-27 Alstom Technology Ltd Paroi pour un canal de gaz chaud dans une turbine à gaz

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3628880A (en) * 1969-12-01 1971-12-21 Gen Electric Vane assembly and temperature control arrangement
EP0541207A1 (fr) * 1991-11-04 1993-05-12 General Electric Company Aube de turbine réfroidi par des jets d'air comportant une pièce d'insertion liant les deux moitiés
US6139269A (en) 1997-12-17 2000-10-31 United Technologies Corporation Turbine blade with multi-pass cooling and cooling air addition
US6142734A (en) * 1999-04-06 2000-11-07 General Electric Company Internally grooved turbine wall
US6340285B1 (en) * 2000-06-08 2002-01-22 General Electric Company End rail cooling for combined high and low pressure turbine shroud
EP1225305A2 (fr) * 2001-01-19 2002-07-24 Mitsubishi Heavy Industries, Ltd. Segment de virole pour turbine à gaz
US7220103B2 (en) 2004-10-18 2007-05-22 United Technologies Corporation Impingement cooling of large fillet of an airfoil
US20090202358A1 (en) * 2008-02-07 2009-08-13 Snecma Blade with a cooling groove for a bladed wheel of a turbomachine
US20090285675A1 (en) * 2008-05-16 2009-11-19 General Electric Company Systems and Methods for Modifying Modal Vibration Associated with a Turbine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3628880A (en) * 1969-12-01 1971-12-21 Gen Electric Vane assembly and temperature control arrangement
EP0541207A1 (fr) * 1991-11-04 1993-05-12 General Electric Company Aube de turbine réfroidi par des jets d'air comportant une pièce d'insertion liant les deux moitiés
US6139269A (en) 1997-12-17 2000-10-31 United Technologies Corporation Turbine blade with multi-pass cooling and cooling air addition
US6142734A (en) * 1999-04-06 2000-11-07 General Electric Company Internally grooved turbine wall
US6340285B1 (en) * 2000-06-08 2002-01-22 General Electric Company End rail cooling for combined high and low pressure turbine shroud
EP1225305A2 (fr) * 2001-01-19 2002-07-24 Mitsubishi Heavy Industries, Ltd. Segment de virole pour turbine à gaz
US20020098079A1 (en) * 2001-01-19 2002-07-25 Mitsubishi Heavy Industries, Ltd. Gas turbine split ring
US7220103B2 (en) 2004-10-18 2007-05-22 United Technologies Corporation Impingement cooling of large fillet of an airfoil
US20090202358A1 (en) * 2008-02-07 2009-08-13 Snecma Blade with a cooling groove for a bladed wheel of a turbomachine
US20090285675A1 (en) * 2008-05-16 2009-11-19 General Electric Company Systems and Methods for Modifying Modal Vibration Associated with a Turbine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3048262A1 (fr) 2015-01-20 2016-07-27 Alstom Technology Ltd Paroi pour un canal de gaz chaud dans une turbine à gaz
US10087778B2 (en) 2015-01-20 2018-10-02 Ansaldo Energia Switzerland AG Wall for a hot gas channel in a gas turbine

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