EP2636846A1 - Hergestelltes Turbinenprofil - Google Patents

Hergestelltes Turbinenprofil Download PDF

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Publication number
EP2636846A1
EP2636846A1 EP13157726.4A EP13157726A EP2636846A1 EP 2636846 A1 EP2636846 A1 EP 2636846A1 EP 13157726 A EP13157726 A EP 13157726A EP 2636846 A1 EP2636846 A1 EP 2636846A1
Authority
EP
European Patent Office
Prior art keywords
section
airfoil
bucket
sections
attached
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Withdrawn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
EP13157726.4A
Other languages
English (en)
French (fr)
Inventor
Christopher Michael Prue
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 Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2636846A1 publication Critical patent/EP2636846A1/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Withdrawn legal-status Critical Current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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator

Definitions

  • the present invention relates generally to a turbine airfoil formed as a fabricated article; and, more particularly, to an apparatus and method for providing a fabricated gas turbine bucket; wherein the radially outermost portion is protected from exposure to elevated temperatures, high velocity gases, or an otherwise degrading environment.
  • pressurized air from a compressor is mixed with fuel and ignited in a combustor to generate hot pressurized gases.
  • the hot pressurized gases flow from the combustor to one or more fixed and rotating turbine stages.
  • Each rotating turbine stage includes a plurality of airfoils, or buckets, which are radially disposed about a rotating element, such as a disk.
  • a stationary element such as a shroud, is radially disposed about the rotating airfoils, thereby forming an annular flowpath.
  • Energy is imparted from the hot pressurized gases to the rotating airfoils, causing rotation of the rotating element, thereby converting the thermal and kinetic energy from the hot pressurized gases to mechanical torque.
  • Some of the mechanical torque is typically used to drive the compressor, and the remaining torque is typically used to drive a generator or other rotating machine.
  • Each gas turbine bucket generally includes an airfoil extending radially outwardly from a shank that is connected with and imparts mechanical energy to the rotating element.
  • the airfoil is typically hollow or contains a plurality of internal passages through which a pressurized fluid, such as compressed air, is caused to flow for the purpose of cooling the airfoil material.
  • a tip may be provided to protect and impart structural integrity to the radially outermost portion of the airfoil. The tip must be capable of withstanding highly degrading environmental conditions, including elevated temperatures and high velocity gases; as well as have sufficient mechanical strength and stiffness to maintain the aerodynamic shape of the airfoil, contain the pressurized internal cooling fluid, and withstand high speed rubbing in the event that the tip contacts the stationary shroud.
  • the tip It is often advantageous to form the tip from a different material than the remainder of the airfoil.
  • This combination may provide multiple benefits; including tailoring the thermal and mechanical properties of the tip to satisfy the particular requirements stated above, reducing the overall weight of the bucket, and facilitating repair of the bucket.
  • the thermal and mechanical loads acting on the airfoil may cause the material combination to be substantially weaker and less durable than a monolithic airfoil. This problem is particularly acute when materials having different thermal and mechanical properties; such as coefficient of thermal expansion, thermal conductivity, or modulus of elasticity; are combined.
  • a fabricated turbine airfoil includes a first section, a second section, and a third section; wherein the first section provides structural support for the remaining sections, the second section is integrally joined with the first section, and the third section connects the first and second sections.
  • a method of manufacturing a fabricated turbine airfoil includes the steps of forming a first section including a load bearing member, a first end, and a second end; forming a second section; forming a third section; attaching the third section to the second end of the first section; and attaching the second section to the third section in such a manner that the second section is integrally joined with the first section and the first section provides structural support for the remaining sections.
  • FIG. 1 illustrates an exemplary embodiment of a gas turbine bucket 10 formed as a fabricated article in accordance with aspects of the present invention.
  • the bucket 10 may include a dovetail 12 that attaches to a rotor disk (not shown).
  • a shank 14 extends radially outwardly from the dovetail 12 and terminates in a platform 16 that projects radially outwardly from and surrounds the shank 14.
  • a first section in the form of an airfoil 18 extends radially outwardly from the platform 16.
  • the airfoil 18 has a root 20 at the junction with the platform 16 and a tip 22 at its radially outer end.
  • the airfoil 18 has a concave pressure sidewall 24 and a convex suction sidewall 26 joined together at a leading edge 28 and a trailing edge 30.
  • the airfoil 18 may take any configuration suitable for extracting energy from the hot gas stream and causing rotation of the rotor. This results in a substantial mechanical load on the airfoil caused by the difference in gas pressure between the pressure sidewall 24 and the suction sidewall 26.
  • the airfoil 18 may be hollow or contain a plurality of internal passages through which a pressurized fluid, such as compressed air, is caused to flow for the purpose of cooling the airfoil material.
  • the shank 14 and platform 16 may be similarly cooled.
  • the airfoil 18, shank 14, and platform 16 are typically formed from a cast high strength nickel-based superalloy, but may be formed using any suitable process and from any suitable material for performing the functions described herein.
  • FIG. 2 illustrates the tip 22 in greater detail.
  • a second section 100 is integrally joined to and closes off the tip 22 in a manner such that the aerodynamic and structural continuity of the airfoil pressure sidewall 24, suction sidewall 26, leading edge 28, and trailing edge 30 is maintained.
  • the second section 100 may take any configuration suitable for maintaining the aerodynamic shape and efficiency of the bucket 10, and may be formed using any suitable process and from any suitable material for imparting structural integrity to and providing environmental protection for the tip 22. It will be appreciated that the second section 100 may extend radially inwardly to any suitable location on the radial span of the airfoil 18, so long as the airfoil 18 structurally supports the second section 100 as the bucket 10 rotates or when it is stationary.
  • the second section 100 may be formed from a different material than the airfoil 18; such as a refractory metal or metallic composite, intermetallic compound, ceramic, or ceramic composite.
  • the second section 100 is formed from a ceramic material by first forming a near net "green" shape using an isostatic pressing process, followed by an intermediate firing step to strengthen the green shape, followed by a machining step to achieve the desired shape, followed by a firing step to achieve the final dimensions and properties of the second section 100. It will be appreciated that these process steps are not exhaustive, and that any suitable process and sequence of process steps may be used, depending upon the material forming the second section 100; and the final dimensional tolerance, surface finish, and mechanical properties desired.
  • FIG. 3 illustrates a cross-section of the tip 22 viewed along line 3-3.
  • the second section 100 includes a neck 120 forming a radially inward facing surface 140.
  • a third section in the form of a sleeve 160 is disposed between the radially inward facing surface 140 and a radially outward facing surface 180 of the airfoil 18 in such a manner that the sleeve 160 nests within the airfoil pressure sidewall 24 and suction sidewall 26 and the majority of centrifugal load is taken in the shear direction.
  • the radially inward facing surface 140 and the radially outward facing surface 180 may be disposed in any suitable manner for providing mechanical integrity to the assembly.
  • the sleeve 160 may be either continuous or discontinuous, and may be formed using any suitable process and from any suitable material for providing mechanical integrity to the assembly and resistance to thermal distortion.
  • the sleeve 160 is formed from a nickel-based superalloy using a stamping or extrusion process followed by machining to the final shape, dimensions, and surface finish desired.
  • the sleeve 160 may be bonded to the radially inward facing surface 140 using a brazing process.
  • a braze alloy such as PalniroTM-1 (50% gold, 25% nickel, 25% palladium) may be used with a suitable heat treatment to achieve high mechanical integrity of the resulting joint. It will be appreciated that mechanical features may be added to the sleeve 160 and the radially inward facing surface 140 in order to improve the mechanical strength of the bond, particularly in the shear direction.
  • the sleeve 160 may be attached to the radially outward facing surface 180 using any suitable method; such as brazing, welding, mechanical attachment, or a combination thereof; in order to achieve high mechanical integrity of the resulting joint, particularly in the shear direction, as well as provide means for removal of the sleeve 160 and second section 100 assembly during repair and refurbishment of the bucket 10.
  • various embodiments of the present invention contemplate a fabricated airfoil; wherein the radially outermost portion is protected from exposure to elevated temperatures, high velocity gases, or an otherwise degrading environment.
  • Exemplary embodiments of the fabricated airfoil are described in detail above.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13157726.4A 2012-03-06 2013-03-05 Hergestelltes Turbinenprofil Withdrawn EP2636846A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/412,686 US20130236318A1 (en) 2012-03-06 2012-03-06 Fabricated turbine airfoil

Publications (1)

Publication Number Publication Date
EP2636846A1 true EP2636846A1 (de) 2013-09-11

Family

ID=47826985

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13157726.4A Withdrawn EP2636846A1 (de) 2012-03-06 2013-03-05 Hergestelltes Turbinenprofil

Country Status (5)

Country Link
US (1) US20130236318A1 (de)
EP (1) EP2636846A1 (de)
JP (1) JP2013185586A (de)
CN (1) CN103306743A (de)
RU (1) RU2013109759A (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2963244A1 (de) * 2014-07-02 2016-01-06 Rolls-Royce plc Spitzeneinsatz, zugehörige Laufschaufel und Gasturbinentriebwerk
EP3323994A1 (de) * 2016-11-17 2018-05-23 United Technologies Corporation Schaufelblatt mit dichtung zwischen stirnwand und schaufelblattsektion
EP3323991A1 (de) * 2016-11-17 2018-05-23 United Technologies Corporation Schaufelblatt mit schaufelstück mit radialdichtung
WO2020097146A1 (en) 2018-11-08 2020-05-14 General Electric Company Turbomachine blade tip attachment

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160245095A1 (en) * 2015-02-25 2016-08-25 General Electric Company Turbine rotor blade
US11203938B2 (en) 2018-11-08 2021-12-21 General Electric Company Airfoil coupon attachment

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2115882A (en) * 1981-03-20 1983-09-14 Gen Electric Replaceable tip cap for a rotor blade
GB2378733A (en) * 2001-08-16 2003-02-19 Rolls Royce Plc Blade tips for turbines
US20070077143A1 (en) * 2005-10-04 2007-04-05 General Electric Company Bi-layer tip cap
EP2570594A2 (de) * 2011-05-31 2013-03-20 General Electric Company Turbinenschaufel mit metallischem Profil und keramischem Spitzendeckel und zugehöriges Gasturbinentriebwerk

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8444389B1 (en) * 2010-03-30 2013-05-21 Florida Turbine Technologies, Inc. Multiple piece turbine rotor blade

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2115882A (en) * 1981-03-20 1983-09-14 Gen Electric Replaceable tip cap for a rotor blade
GB2378733A (en) * 2001-08-16 2003-02-19 Rolls Royce Plc Blade tips for turbines
US20070077143A1 (en) * 2005-10-04 2007-04-05 General Electric Company Bi-layer tip cap
EP2570594A2 (de) * 2011-05-31 2013-03-20 General Electric Company Turbinenschaufel mit metallischem Profil und keramischem Spitzendeckel und zugehöriges Gasturbinentriebwerk

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2963244A1 (de) * 2014-07-02 2016-01-06 Rolls-Royce plc Spitzeneinsatz, zugehörige Laufschaufel und Gasturbinentriebwerk
US9670786B2 (en) 2014-07-02 2017-06-06 Rolls-Royce Plc Rotary blade with tip insert
EP3323994A1 (de) * 2016-11-17 2018-05-23 United Technologies Corporation Schaufelblatt mit dichtung zwischen stirnwand und schaufelblattsektion
EP3323991A1 (de) * 2016-11-17 2018-05-23 United Technologies Corporation Schaufelblatt mit schaufelstück mit radialdichtung
US10458262B2 (en) 2016-11-17 2019-10-29 United Technologies Corporation Airfoil with seal between endwall and airfoil section
US10746038B2 (en) 2016-11-17 2020-08-18 Raytheon Technologies Corporation Airfoil with airfoil piece having radial seal
US11149573B2 (en) 2016-11-17 2021-10-19 Raytheon Technologies Corporation Airfoil with seal between end wall and airfoil section
WO2020097146A1 (en) 2018-11-08 2020-05-14 General Electric Company Turbomachine blade tip attachment
EP3877629A4 (de) * 2018-11-08 2022-06-08 General Electric Company Schaufelspitzenbefestigung einer turbomaschine

Also Published As

Publication number Publication date
JP2013185586A (ja) 2013-09-19
CN103306743A (zh) 2013-09-18
RU2013109759A (ru) 2014-09-10
US20130236318A1 (en) 2013-09-12

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