EP2286938A2 - Feuerfester Metallkern für in einem Stück gegossene Ausgangsrinne - Google Patents

Feuerfester Metallkern für in einem Stück gegossene Ausgangsrinne Download PDF

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Publication number
EP2286938A2
EP2286938A2 EP10251009A EP10251009A EP2286938A2 EP 2286938 A2 EP2286938 A2 EP 2286938A2 EP 10251009 A EP10251009 A EP 10251009A EP 10251009 A EP10251009 A EP 10251009A EP 2286938 A2 EP2286938 A2 EP 2286938A2
Authority
EP
European Patent Office
Prior art keywords
refractory metal
metal core
tabs
main portion
turbine engine
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Withdrawn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
EP10251009A
Other languages
English (en)
French (fr)
Other versions
EP2286938A3 (de
Inventor
Eric A. Hudson
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.)
RTX Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP2286938A2 publication Critical patent/EP2286938A2/de
Publication of EP2286938A3 publication Critical patent/EP2286938A3/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Withdrawn legal-status Critical Current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
    • F01D5/187—Convection cooling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • 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
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • 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
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W

Definitions

  • the present disclosure relates to a refractory metal core having separate exit tabs which are ganged together within the exterior boundary of a finished cast part and to a turbine engine part formed using the refractory metal core.
  • Refractory metal cores have been used to form cooling passages in turbine engine components such as blades and vanes.
  • the main portion of the refractory metal core may be configured to create a cooling air passage internal to the component.
  • Small tabs extending from the refractory metal core are used to form exit holes associated with the cooling air passage. These individual exit tabs are sometimes connected together outside the envelope of the finished casting to improve the casting process.
  • exit holes formed in this manner can restrict the types of coatings that can be subsequently applied or significantly increase the cost of forming the coatings since very thick coatings will cover the holes.
  • the cast holes are subject to occasional partial clogging or bending over of edges from handling or contamination, leading to an undesirable decrease in passage cooling flow.
  • the present disclosure relates to a refractory metal core for use in casting turbine engine part.
  • the refractory metal core broadly comprises a main portion, a plurality of tabs extending from said main portion, and an end portion which at one end joins together some or all of said plurality of tabs.
  • the end portion has an opposite edge located prior to an exterior boundary of the part.
  • the present disclosure also relates to a turbine engine part having an airfoil portion with a cooling passage formed therein or a part without an airfoil portion which forms the inner or outer gaspath endwalls.
  • the cooling passage has a plurality of exit holes and an exit trench which receives cooling fluid from said exit holes.
  • the disclosure also covers a turbine engine part having a core of the disclosure therein and a method of forming a cast part comprising placing a core of the disclosure in a mold or die, forming the cast part from a molten metal and removing the core.
  • a refractory metal core 10 which may be used to form a cooling passage in a cast part 12, such as a turbine engine component, is illustrated.
  • the cast part 12 has a boundary 14.
  • the refractory metal core 10 has a main portion 16 with a plurality of tabs 18 extending therefrom.
  • the tabs 18 are used to form a series of discrete cast exit holes 20 in the finished casting of the part.
  • the tabs 18 extend beyond the boundary 14.
  • the tabs 18 may have unjoined ends or one or more sets of joined or ganged ends.
  • the tabs 18 may be joined together by a piece 22 of refractory metal material which is located outside the boundary 14.
  • the refractory metal core 10' of FIG. 2 may be used to form the cast part 12'.
  • the cast part 12' has an exterior boundary 14'.
  • the refractory metal core 10' has a main portion 16' which may be configured to form at least one desired cooling passage in the cast part 12'.
  • the main portion 16' may be machined so as to form a cooling passage with heat transfer ribs or pedestals, or make a joint to connect to a ceramic core with a serpentine cooling passage.
  • a plurality of tabs 18' extend from the main portion 16' and are used to form an array of exit holes 104 for the cooling fluid which exits the cooling passage. As can be seen from FIG.
  • the tabs 18' do not extend beyond an exterior or outer boundary 14'.
  • the outer boundary 14' could be an exterior surface of the part, such as a pressure sidewall or a suction side wall.
  • the outer boundary 14' could also be a trailing edge of an airfoil portion of the part.
  • the outer boundary 14' could be the intersegment edge of an endwall in a blade outer air seal or shroud.
  • the tabs 18' are joined together by a piece 22' of refractory metal material.
  • the piece 22' of refractory metal material forms an exit trench 106 in the final cast part.
  • the main portion 16', the tabs 18', and the piece 22' may be integrally formed from a refractory metal material such as molybdenum or a molybdenum alloy.
  • the exit trench 106 protects the exit holes 104 from external contamination and handling damage by keeping the terminus of each exit hole 104 inboard of the exterior boundary or edge 14' of the cast part.
  • the exit trench 106 creates enough flow area to be much more tolerant of any contaminant buildup in the corners of the opening 26' of the exit trench 106 than individual holes such as those created by the refractory metal core of FIG. 1 would be.
  • the slot in the cast part which forms the opening 26' is usefully a single long opening that can be masked in one step for subsequent application of thick external coatings. It can also be more than one long opening formed by ganging together groups of exit tabs. Benefits include reduced variability in actual part flow, reduced cost of coating, and expansion of the variety of coatings that are feasible to use.
  • the refractory metal core 10' is placed into a mold or die. After the part 12' has been formed from a molten metal material, the refractory metal core 10' may be removed using any suitable leaching technique known in the art. After the refractory metal core 10' is removed, as shown in FIG. 3 , the cast part 100, such as a vane, is left with at least one cast cooling passage 102, a plurality of cast exit holes 104 cooperating with said at least one cooling passage, and an exit trench 106 for receiving cooling fluid from the exit holes 104.
  • the exit holes 104 may be positioned within the trench 106 so that the terminal end of each hole is spaced from an exterior boundary of the part.
  • the exit trench 106 may be on an outer endwall edge 108.
  • the trench 106 can also be on the forward or aft edge of the platform.
  • the exit trench 106 has at least one slot 110 through which cooling fluid is discharged over an exterior section of part 100.
  • Turbine engine components which could take advantage of the geometry created by the refractory metal core of FIG. 2 include vane platforms and blade outer air seals or shrouds.
  • FIG. 5 illustrates another embodiment of a refractory metal core 10" which may be used to form a cast part with a trench.
  • the refractory metal core 10" has main portion 16" with a plurality of tabs 18" connected to the main portion 16" by arms 30". Each tab 18" is called a hammerhead tab because the tab 18" has a width greater than the width of the arm 30" to which it is attached.
  • the main portion 16" may be configured to form at least one cooling passage in the cast part 12".
  • the main portion 16", the arms 30" and the tabs 18" may be integrally formed for a refractory metal or metal alloy using any suitable technique known in the art. As can be seen in FIG.
  • each of the tabs 18" has a length which causes it to extend beyond the exterior or outer boundary 14".
  • the arms 30" form cooling passages in the cast part 12" which allows cooling fluid to flow from the cooling passage(s) formed by the main portion 16" and the trenches formed by the tabs 18".
  • the cast part will have one hole per short trench segment.
  • integral cast cooling flow exit trench there has been described an integral cast cooling flow exit trench. While the integral cast cooling flow exit trench has been described in the context of specific embodiments thereof, other unforeseeable alternatives, modifications and variations may become apparent to those skilled in the art having read the foregoing description. Accordingly, it is intended to embrace those alternatives, modifications, and variations as fall within the broad scope of the appended claims.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10251009.6A 2009-07-27 2010-05-26 Feuerfester Metallkern für in einem Stück gegossene Ausgangsrinne Withdrawn EP2286938A3 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/509,608 US20110020115A1 (en) 2009-07-27 2009-07-27 Refractory metal core integrally cast exit trench

Publications (2)

Publication Number Publication Date
EP2286938A2 true EP2286938A2 (de) 2011-02-23
EP2286938A3 EP2286938A3 (de) 2015-02-25

Family

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EP10251009.6A Withdrawn EP2286938A3 (de) 2009-07-27 2010-05-26 Feuerfester Metallkern für in einem Stück gegossene Ausgangsrinne

Country Status (2)

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US (1) US20110020115A1 (de)
EP (1) EP2286938A3 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10329916B2 (en) 2014-05-01 2019-06-25 United Technologies Corporation Splayed tip features for gas turbine engine airfoil

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8347945B1 (en) 2011-07-29 2013-01-08 United Technologies Corporation Platform interconnected with mid-body core interface for molding airfoil platforms
US20140064984A1 (en) * 2012-08-31 2014-03-06 General Electric Company Cooling arrangement for platform region of turbine rotor blade

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1634665A2 (de) * 2004-09-09 2006-03-15 United Technologies Corporation Verbundkern zur Verwendung beim Feingiessen
EP2243930A2 (de) * 2009-04-17 2010-10-27 General Electric Company Spitze einer Turbinenrotorschaufel

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2163218B (en) * 1981-07-07 1986-07-16 Rolls Royce Cooled vane or blade for a gas turbine engine
US6612811B2 (en) * 2001-12-12 2003-09-02 General Electric Company Airfoil for a turbine nozzle of a gas turbine engine and method of making same
US20080131285A1 (en) * 2006-11-30 2008-06-05 United Technologies Corporation RMC-defined tip blowing slots for turbine blades

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1634665A2 (de) * 2004-09-09 2006-03-15 United Technologies Corporation Verbundkern zur Verwendung beim Feingiessen
EP2243930A2 (de) * 2009-04-17 2010-10-27 General Electric Company Spitze einer Turbinenrotorschaufel

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10329916B2 (en) 2014-05-01 2019-06-25 United Technologies Corporation Splayed tip features for gas turbine engine airfoil
US11268387B2 (en) 2014-05-01 2022-03-08 Raytheon Technologies Corporation Splayed tip features for gas turbine engine airfoil

Also Published As

Publication number Publication date
EP2286938A3 (de) 2015-02-25
US20110020115A1 (en) 2011-01-27

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