IN2015DN03335A - - Google Patents

Info

Publication number
IN2015DN03335A
IN2015DN03335A IN3335DEN2015A IN2015DN03335A IN 2015DN03335 A IN2015DN03335 A IN 2015DN03335A IN 3335DEN2015 A IN3335DEN2015 A IN 3335DEN2015A IN 2015DN03335 A IN2015DN03335 A IN 2015DN03335A
Authority
IN
India
Prior art keywords
casting
wall
airfoil
main wall
tip
Prior art date
Application number
Inventor
Christian X Campbell
Dimitrios Thomaidis
Original Assignee
Siemens Energy Inc
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 Energy Inc filed Critical Siemens Energy Inc
Publication of IN2015DN03335A publication Critical patent/IN2015DN03335A/en

Links

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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D46/00—Controlling, supervising, not restricted to casting covered by a single main group, e.g. for safety reasons
    • 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
    • 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
    • F05D2230/10—Manufacture by removing material
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Analysing Materials By The Use Of Radiation (AREA)

Abstract

A process is provided for forming an airfoil for a gas turbine engine involving: forming a casting of a gas turbine engine airfoil having a main wall and an interior cavity , the main wall having a wall thickness extending from an external surface of the outer wall to the interior cavity, an outer section of the main wall extending from a location between a base and a tip of the airfoil casting to the tip having a wall thickness greater than a final thickness. The process may further involve effecting movement, using a computer system , of a material removal apparatus and the casting relative to one another such that a layer of material is removed from the casting at one or more radial portions along the main wall of the casting
IN3335DEN2015 2012-11-13 2013-11-12 IN2015DN03335A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/675,345 US8720526B1 (en) 2012-11-13 2012-11-13 Process for forming a long gas turbine engine blade having a main wall with a thin portion near a tip
PCT/US2013/069671 WO2014078305A1 (en) 2012-11-13 2013-11-12 Process for forming a long gas turbine engine blade having a main wall with a thin portion near a tip

Publications (1)

Publication Number Publication Date
IN2015DN03335A true IN2015DN03335A (en) 2015-10-23

Family

ID=49759538

Family Applications (1)

Application Number Title Priority Date Filing Date
IN3335DEN2015 IN2015DN03335A (en) 2012-11-13 2013-11-12

Country Status (8)

Country Link
US (1) US8720526B1 (en)
EP (1) EP2920425B1 (en)
JP (1) JP5973081B2 (en)
CN (1) CN104812994B (en)
IN (1) IN2015DN03335A (en)
RU (1) RU2015117767A (en)
SA (1) SA515360421B1 (en)
WO (1) WO2014078305A1 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10260352B2 (en) 2013-08-01 2019-04-16 Siemens Energy, Inc. Gas turbine blade with corrugated tip wall
CA2972764A1 (en) 2015-01-13 2016-07-21 General Electric Company A composite airfoil with fuse architecture
US10101577B2 (en) 2015-04-13 2018-10-16 Siemens Energy, Inc. System to prognose gas turbine remaining useful life
EP3433040B1 (en) 2016-04-27 2023-01-25 Siemens Energy, Inc. Gas turbine blade with corrugated tip wall and manufacturing method thereof
WO2018132629A1 (en) 2017-01-13 2018-07-19 Siemens Aktiengesellschaft Adaptive machining of cooled turbine airfoil
EP3511522A1 (en) * 2018-01-11 2019-07-17 Siemens Aktiengesellschaft Gas turbine blade and method for producing such blade
FR3103126B1 (en) * 2019-11-20 2022-03-25 Safran Aircraft Engines Improved device and method for machining an aeronautical part

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GB8508391D0 (en) * 1985-03-30 1985-05-09 Ae Plc Measurement of engineering components
US4959523A (en) 1988-11-18 1990-09-25 Hydro-Quebec Method and apparatus for automatically sensing the configuration of a surface area and effecting a work function thereon
US5446673A (en) 1993-03-30 1995-08-29 General Electric Company System and method for finish machining an in-process part having an inaccessible interior cavity
EP0894558A1 (en) * 1997-07-29 1999-02-03 Siemens Aktiengesellschaft Turbine blade and method of fabrication of a turbine blade
US6850874B1 (en) 1998-04-17 2005-02-01 United Technologies Corporation Method and apparatus for predicting a characteristic of a product attribute formed by a machining process using a model of the process
DE60026934T2 (en) 1999-06-02 2006-12-14 General Electric Co. Method for reducing the wall thickness after casting a turbine blade by means of EDM machining
DE10001516B4 (en) 2000-01-15 2014-05-08 Alstom Technology Ltd. Non-destructive method for determining the layer thickness of a metallic protective layer on a metallic base material
US6376801B1 (en) 2000-10-12 2002-04-23 General Electric Company Gas turbine component refurbishment apparatus and repair method
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GB0114503D0 (en) * 2001-06-14 2001-08-08 Rolls Royce Plc Air cooled aerofoil
US7204019B2 (en) 2001-08-23 2007-04-17 United Technologies Corporation Method for repairing an apertured gas turbine component
US6701615B2 (en) 2002-03-08 2004-03-09 General Electric Company Inspection and sorting system and method for part repair
JP2003344026A (en) * 2002-05-27 2003-12-03 Mitsubishi Heavy Ind Ltd Computer program and method for inspecting hollow vane
DE10255346A1 (en) * 2002-11-28 2004-06-09 Alstom Technology Ltd Method of making a turbine blade
US6969821B2 (en) * 2003-06-30 2005-11-29 General Electric Company Airfoil qualification system and method
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US7010982B2 (en) 2004-04-30 2006-03-14 General Electric Company Method of ultrasonically inspecting airfoils
EP1593445B1 (en) * 2004-05-03 2007-07-18 Siemens Aktiengesellschaft Process of making a hollow member having an internal coating
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DE102006050440A1 (en) * 2006-10-26 2008-04-30 Mtu Aero Engines Gmbh Lightweight structure-turbine blade manufacturing method, involves casting blade unit with blade wall and hollow space surrounding blade wall, where blade unit extends radially from floor area to head area
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Also Published As

Publication number Publication date
RU2015117767A (en) 2017-01-10
JP5973081B2 (en) 2016-08-23
CN104812994A (en) 2015-07-29
US20140130999A1 (en) 2014-05-15
US8720526B1 (en) 2014-05-13
WO2014078305A1 (en) 2014-05-22
SA515360421B1 (en) 2016-12-18
JP2015536404A (en) 2015-12-21
EP2920425A1 (en) 2015-09-23
CN104812994B (en) 2018-01-26
EP2920425B1 (en) 2016-11-02

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