EP2540970A1 - Mit flüssigem Metall gekühlte Schaufel - Google Patents

Mit flüssigem Metall gekühlte Schaufel Download PDF

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Publication number
EP2540970A1
EP2540970A1 EP11172402A EP11172402A EP2540970A1 EP 2540970 A1 EP2540970 A1 EP 2540970A1 EP 11172402 A EP11172402 A EP 11172402A EP 11172402 A EP11172402 A EP 11172402A EP 2540970 A1 EP2540970 A1 EP 2540970A1
Authority
EP
European Patent Office
Prior art keywords
blade
cooling
cavity
leading edge
wall
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Withdrawn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
EP11172402A
Other languages
English (en)
French (fr)
Inventor
Mehdi Bahador
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 EP11172402A priority Critical patent/EP2540970A1/de
Priority to PCT/EP2012/062819 priority patent/WO2013004656A1/en
Publication of EP2540970A1 publication Critical patent/EP2540970A1/de
Withdrawn legal-status Critical Current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
    • F01D5/12—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
    • F01D5/181—Blades having a closed internal cavity containing a cooling medium, e.g. sodium
    • 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
    • F01D5/185—Liquid 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/207—Heat transfer, e.g. cooling using a phase changing mass, e.g. heat absorbing by melting or boiling
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/16—Other metals not provided for in groups F05D2300/11 - F05D2300/15
    • F05D2300/1616—Zinc

Definitions

  • An airfoil such as a blade has a leading edge and a trailing edge. Cooling of the leading edge is very important since the largest thermal load occurs at the leading edge and the cooling flow affects the aerodynamics and heat transfer of the entire airfoil.
  • the leading edge of the airfoil portion of the blade is cooled by impingement cooling or by film cooling and the trailing edge by matrix arrangement of ribs, pin-fins and so forth.
  • US patent no. 5,348,446 describes an airfoil for a gas turbine engine which is constructed from a core body formed of a conventional nickel-based super alloy and leading and trailing edge components and squealer tip formed of a nickel aluminide alloy.
  • the nickel aluminide components exhibit a high degree of thermal conductivity and transfer heat from the leading edge and the trailing edge into the core body by direct conduction.
  • turbomachines as mentioned in these patents operate at high temperatures which may cause the material inside the blade to melt resulting in loss of stability.
  • the object is achieved by a blade for a turbomachine according to claim 1.
  • the invention is based on the idea to use both conduction and convection effects for cooling of the leading edge of the blade by including a material with special properties inside the blade.
  • the blade of the turbomachine includes a cavity at the leading edge.
  • the cavity is at least partly filled by a material which is liquid near the operating temperatures of the turbomachine.
  • a material which is liquid near the operating temperatures of the turbomachine allows the heat transfer from the leading edge to the other portions of the blade through conduction and convection.
  • the liquid material transfers the heat through convection to the core region, from where the heat is easily dissipated through a wall which is cooled via cooling medium.
  • the rotation of the blade during operation of the turbomachine also generates centrifugal force which aids in cooling by convection in the cavity at the leading edge because colder liquid material is forced in a radial direction towards the outer portions of the cavity which is hot.
  • the blade of the turbomachine has a root portion and an airfoil portion, wherein the airfoil portion has the leading edge and the trailing edge.
  • the material is zinc.
  • Zinc has a high degree of thermal conductivity of about 116 Watt/meter*Kelvin and is in liquid state near the operating temperatures of the turbomachine which aids in both the heat transfer through conduction and convection.
  • the material is aluminium.
  • Aluminium has a high thermal conductivity of about 240 Watt/meter*Kelvin. Furthermore, aluminium is liquid at operating temperatures of the turbomachine.
  • the cavity is defined by a wall inside the blade having one or more cooling means.
  • the one or more cooling means allow efficient cooling of the wall and thus dissipate the heat to the surroundings.
  • the cooling means include cooling channels, pins, and/or fins to allow efficient transfer of heat and cooling of the blade.
  • the cooling channels include a cooling medium such as a coolant or air to cool the inner portions of the blade.
  • the wall defines the cavity which extends into the core region from the leading edge of the blade. Heat is transferred via the material in the cavity to the wall from the leading edge to the core region of the blade, which prevents the leading edge from being over heated.
  • At least one of the leading edge, trailing edge, the core region and the wall defining the cavity are formed from a super alloy.
  • Super alloys have excellent mechanical strength and creep resistance at high temperatures.
  • the super alloys have good surface stability and are corrosion resistant.
  • Embodiments of the present invention described below relate to a blade component in a turbomachine.
  • the turbomachine may include a gas turbine, a steam turbine, a turbofan and the like.
  • FIG. 1 is a schematic diagram of an exemplary blade 1 of a rotor (not shown) of a turbomachine, such as a gas turbine.
  • the blade 1 includes an airfoil portion 2 and a root portion 3.
  • the airfoil portion 2 projects from the root portion 3 in a radial direction as depicted, wherein the radial direction means a direction perpendicular to the rotation axis of the rotor.
  • the airfoil portion 2 extends radially along a longitudinal direction of the blade 1.
  • the blade 1 is attached to a body of the rotor (not shown), in such a way that the root portion 3 is attached to the body of the rotor whereas the airfoil portion 2 is located at a radially outermost position.
  • the airfoil portion 2 has an outer wall including a pressure side 6, also called pressure surface, and a suction side 7, also called suction surface.
  • the pressure side 6 and the suction side 7 are joined together along an upstream leading edge 4 and a downstream trailing edge 5, wherein the leading edge 4 and the trailing edge 5 are spaced axially from each other as depicted in FIG. 1 .
  • one or more cooling holes 8 are present on the pressure side 6 and the suction side 7 of the blade as depicted in FIG. 1 .
  • the cooling holes 8 aid in film cooling of the blade 1 as will be described in more detail with reference to FIG. 2 .
  • the blade 1 may be cast as a single component or may alternatively be assembled from multiple components.
  • the multiple component blade may include a leading edge component, a trailing edge component and a core region component.
  • the components may be cast separately and thereafter joined together by bonding or brazing for example.
  • FIG. 2 a radial sectional view of the blade 1 of the gas turbine at the airfoil portion 2 along the lines II-II in FIG.1 is depicted.
  • the blade 1 includes an outer wall 21 extending from the leading edge 4 to the trailing edge 5. Additionally, the blade 1 includes an inner wall 22 adjacent the outer wall 21 extending from the leading edge 4 to the trailing edge 5 of the blade.
  • the blade 1 may have three regions, namely the leading region 29, the trailing region 31 and the core region 30 between the leading region 29 and the trailing region 31. Additionally, the blade 1 may also include a cavity 20 or webs which are structures cast inside the blade 1 extending from the pressure side 6 to the suction side 7 of the blade 1. These structures such as ribs, fins or pins may be casted or machined inside the components such as at the core region 30 or the trailing region 31 of the blade 1.
  • the blade 1 comprises the cavity 20 at the leading edge 4 which is defined by a wall 23.
  • the wall 23 separates the leading region and the core region of the blade 1.
  • the extent or boundary of the cavity 20 is defined by the wall 23.
  • the cavity 20 is at least partly filled with a material 19 which is liquid at the operating temperature of the turbomachine.
  • the material 19 is a metal with high thermal conductivity such as, but not limited to zinc or aluminium.
  • the material 19 may also include any other material with similar characteristics or properties such as turning into liquid state at the operating temperatures of the turbomachine.
  • a cooling passage 25 is located adjacent the wall 23.
  • the cooling passage 25 allows air from the surrounding to be directed inside the blade, the cool air dissipates the heat from the wall 23 and directs the air outside the blade via one or more cooling holes 8 located on both the pressure side and the suction side of the blade for film cooling. More particularly, the cooling holes 8 are present on the outer wall of the blade.
  • temperature at the leading edge 4 may exceed 900 degree centigrade and the temperature at the interior of the blade may be in the range of about 750 degree centigrade.
  • Metals such as aluminium and zinc have a low melting point and therefore melt at the operating temperatures.
  • zinc has a melting point of about 420 degree centigrade and aluminium has a melting point of about 660 degree centigrade.
  • these materials are in a liquid state and hence also transfer heat due to convection besides transferring the heat through conduction. More particularly, the heated material at the leading edge moves due to convection to the cooler portion that is near the wall 23, the heat from the material 19 is transferred to the wall 23, which is thereafter dissipated to the surroundings via the air passing through the cooling channels 26. Additionally, the centrifugal force created due to rotation of blade 1 during operation ameliorates the transfer of heat from the leading edge 4 to the wall 23 and subsequently to the cooling passage 25 of the blade 1.
  • aluminium has a high thermal conductivity of about 240 Watt/meter*Kelvin and zinc has thermal conductivity of about 116 Watt/meter*Kelvin.
  • the cavity 20 is completely filled with the material 19.
  • the cavity 20 is only partially filled with the material 19.
  • the material 19 while changing state from solid to liquid may expand; hence, partially filling the cavity 20 with the material 19 prevents stress on the wall 23 and the leading edge 4 to increase due to expansion of the material 19.
  • the wall 23 includes one or more cooling means such as cooling channels 26, which allow a cooling medium, such as but not limited to air to pass through.
  • the cooling medium may also include a coolant, oil or steam for example. The cooling medium passes through the cooling channels 26 and thereby dissipates heat from the wall 23 via the cooling holes 8. Thus, the temperature of the blade 1 is reduced.
  • the cooling passage 25 dissipates the heat from the wall 23 through the cool air passing through the cooling passage 25; the air is thereafter discharged from the blade through the cooling holes 8 (see also FIG. 1 ).
  • the blade 1 may also include an insert 24 located adjacent the wall 23 as depicted in FIG. 2 .
  • the insert 24 is formed of a material such as, but not limited to steel. The insert 24 aids in cooling of the wall 23 by causing impingement of cool air flowing through the cooling passage 25 along the surface of the wall 23.
  • the shape of the cavity 20 and of the wall 23, respectively, proximal to the core region 30 is such that the wall 23 has a greater surface area than at the leading edge 4, as illustrated in FIG. 2 .
  • the wall 23 may also include structures such as ribs, pin-fins and so forth, resulting in an enlarged surface area of the wall 23 to aid in cooling of the blade 1.
  • the wall 23 includes cooling channels 26 for cooling of the blade 1.
  • the cooling medium such as air after dissipating the heat from the wall 23 is exited to the surroundings through the cooling holes 8 as depicted.
  • the middle portion of the blade 1 which is also known as the core region 30 is defined by the inner wall 22 which extends throughout the extent of the blade 1.
  • the core region 30 of the blade 1 may include structures 36 such as fins, ribs for cooling.
  • an insert may also be present in the core region defining core cooling passages.
  • the insert present in the vane configuration aids in impingement cooling of the core region of the vane.
  • the insert may be formed of a material such as but not limited to steel.
  • the core cooling passages 33 allows air from the surrounding inside the core region 30 to cool the core region.
  • a matrix arrangement 32 of ribs is present at the trailing region 31 of the blade for allowing air to efficiently cool the trailing region 31.
  • the blade 1 may be formed of a superalloy such as but not limited to a nickel based superalloy.
  • the outer wall 21, the inner wall 22 and the wall 23 may be formed of a superalloy.
  • the leading edge 4, the trailing edge 5, the core region may be formed of a superalloy.
  • Super alloys have excellent mechanical strength and creep resistance at high temperatures.
  • the super alloys have good surface stability and are corrosion resistant.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11172402A 2011-07-01 2011-07-01 Mit flüssigem Metall gekühlte Schaufel Withdrawn EP2540970A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP11172402A EP2540970A1 (de) 2011-07-01 2011-07-01 Mit flüssigem Metall gekühlte Schaufel
PCT/EP2012/062819 WO2013004656A1 (en) 2011-07-01 2012-07-02 Liquid metal cooled blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11172402A EP2540970A1 (de) 2011-07-01 2011-07-01 Mit flüssigem Metall gekühlte Schaufel

Publications (1)

Publication Number Publication Date
EP2540970A1 true EP2540970A1 (de) 2013-01-02

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ID=46466501

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EP11172402A Withdrawn EP2540970A1 (de) 2011-07-01 2011-07-01 Mit flüssigem Metall gekühlte Schaufel

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EP (1) EP2540970A1 (de)
WO (1) WO2013004656A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015057288A1 (en) * 2013-10-18 2015-04-23 Florida Turbine Technologies, Inc. Gas turbine engine with liquid metal cooling
CN108825311A (zh) * 2018-06-14 2018-11-16 中国航空发动机研究院 具有液态金属主动冷却的航空发动机高压涡轮导叶

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB610737A (en) * 1946-03-19 1948-10-20 Power Jets Res & Dev Ltd Improvements relating to turbine and like blading
FR1102424A (fr) * 1953-06-16 1955-10-20 Parsons & Marine Eng Turbine Dispositif pour le refroidissement d'aubes de turbines et d'éléments similaires
FR1374906A (fr) * 1962-11-21 1964-10-09 Gen Electric Ailette de turbine à gaz
US3314650A (en) * 1965-07-20 1967-04-18 Gen Motors Corp Cooled blade
DE2350010A1 (de) * 1973-01-19 1974-07-25 Bergmann Borsig Veb Waermekraftturbine
GB2051964A (en) * 1979-06-30 1981-01-21 Rolls Royce Turbine blade
GB2087980A (en) * 1980-11-20 1982-06-03 Rolls Royce Liquid cooled aerofoil for a gas turbine engine and a method of making the aerofoil
GB2245660A (en) * 1981-06-23 1992-01-08 Rolls Royce Cooled aerofoil blade
US5348446A (en) 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
US6241469B1 (en) 1998-10-19 2001-06-05 Asea Brown Boveri Ag Turbine blade

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB610737A (en) * 1946-03-19 1948-10-20 Power Jets Res & Dev Ltd Improvements relating to turbine and like blading
FR1102424A (fr) * 1953-06-16 1955-10-20 Parsons & Marine Eng Turbine Dispositif pour le refroidissement d'aubes de turbines et d'éléments similaires
FR1374906A (fr) * 1962-11-21 1964-10-09 Gen Electric Ailette de turbine à gaz
US3314650A (en) * 1965-07-20 1967-04-18 Gen Motors Corp Cooled blade
DE2350010A1 (de) * 1973-01-19 1974-07-25 Bergmann Borsig Veb Waermekraftturbine
GB2051964A (en) * 1979-06-30 1981-01-21 Rolls Royce Turbine blade
GB2087980A (en) * 1980-11-20 1982-06-03 Rolls Royce Liquid cooled aerofoil for a gas turbine engine and a method of making the aerofoil
GB2245660A (en) * 1981-06-23 1992-01-08 Rolls Royce Cooled aerofoil blade
US5348446A (en) 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
US6241469B1 (en) 1998-10-19 2001-06-05 Asea Brown Boveri Ag Turbine blade

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015057288A1 (en) * 2013-10-18 2015-04-23 Florida Turbine Technologies, Inc. Gas turbine engine with liquid metal cooling
CN106414904A (zh) * 2013-10-18 2017-02-15 佛罗里达涡轮技术股份有限公司 具有液态金属冷却的燃气涡轮发动机
CN108825311A (zh) * 2018-06-14 2018-11-16 中国航空发动机研究院 具有液态金属主动冷却的航空发动机高压涡轮导叶
CN108825311B (zh) * 2018-06-14 2021-01-29 中国航空发动机研究院 具有液态金属主动冷却的航空发动机高压涡轮导叶

Also Published As

Publication number Publication date
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