ES425740A1 - Turbomachinery blade tip cap configuration - Google Patents

Turbomachinery blade tip cap configuration

Info

Publication number
ES425740A1
ES425740A1 ES425740A ES425740A ES425740A1 ES 425740 A1 ES425740 A1 ES 425740A1 ES 425740 A ES425740 A ES 425740A ES 425740 A ES425740 A ES 425740A ES 425740 A1 ES425740 A1 ES 425740A1
Authority
ES
Spain
Prior art keywords
blade
interior cavity
cap
defines
piece
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.)
Expired
Application number
ES425740A
Other languages
Spanish (es)
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 ES425740A1 publication Critical patent/ES425740A1/en
Expired legal-status Critical Current

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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Improvements to a turbo-machine blade of the type comprising a root part, an aerodynamic profile shape, a hollow body bumper with a pair of side walls defining an interior cavity between them, a platform defining an interior cavity between they include a blade platform that separates said root part and said hollow body part and that defines the interior limits of said aerodynamic profile and a tip cover that defines the exterior limits of said interior cavity, which comprises; each one of said side walls which is characterized by a simple point cap made of one piece with it, on the inner side thereof and at least one point cap retention member made of one piece with it, on the side inside thereof and radially spaced from said seat so as to be able to hold said spreader cap between said seats and said retaining members such that said spike cap is mechanically secured to said blade. (Machine-translation by Google Translate, not legally binding)
ES425740A 1973-04-27 1974-04-27 Turbomachinery blade tip cap configuration Expired ES425740A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US355150A US3899267A (en) 1973-04-27 1973-04-27 Turbomachinery blade tip cap configuration

Publications (1)

Publication Number Publication Date
ES425740A1 true ES425740A1 (en) 1976-12-16

Family

ID=23396414

Family Applications (2)

Application Number Title Priority Date Filing Date
ES425740A Expired ES425740A1 (en) 1973-04-27 1974-04-27 Turbomachinery blade tip cap configuration
ES446914A Expired ES446914A1 (en) 1973-04-27 1976-04-12 Turbomachinery blade tip cap configuration

Family Applications After (1)

Application Number Title Priority Date Filing Date
ES446914A Expired ES446914A1 (en) 1973-04-27 1976-04-12 Turbomachinery blade tip cap configuration

Country Status (12)

Country Link
US (1) US3899267A (en)
JP (1) JPS5031402A (en)
AU (1) AU471766B2 (en)
BE (1) BE814272A (en)
CA (1) CA996864A (en)
DE (1) DE2418888A1 (en)
ES (2) ES425740A1 (en)
FR (1) FR2227428B1 (en)
GB (1) GB1458734A (en)
IT (1) IT1007996B (en)
NL (1) NL7405529A (en)
SE (2) SE390434B (en)

Families Citing this family (46)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4010531A (en) * 1975-09-02 1977-03-08 General Electric Company Tip cap apparatus and method of installation
US3982851A (en) * 1975-09-02 1976-09-28 General Electric Company Tip cap apparatus
US3994622A (en) * 1975-11-24 1976-11-30 United Technologies Corporation Coolable turbine blade
US4214355A (en) * 1977-12-21 1980-07-29 General Electric Company Method for repairing a turbomachinery blade tip
US4169020A (en) * 1977-12-21 1979-09-25 General Electric Company Method for making an improved gas seal
US4247254A (en) * 1978-12-22 1981-01-27 General Electric Company Turbomachinery blade with improved tip cap
US4390320A (en) * 1980-05-01 1983-06-28 General Electric Company Tip cap for a rotor blade and method of replacement
US4487550A (en) * 1983-01-27 1984-12-11 The United States Of America As Represented By The Secretary Of The Air Force Cooled turbine blade tip closure
US4589823A (en) * 1984-04-27 1986-05-20 General Electric Company Rotor blade tip
US4540339A (en) * 1984-06-01 1985-09-10 The United States Of America As Represented By The Secretary Of The Air Force One-piece HPTR blade squealer tip
US4608128A (en) * 1984-07-23 1986-08-26 General Electric Company Method for applying abrasive particles to a surface
US4712979A (en) * 1985-11-13 1987-12-15 The United States Of America As Represented By The Secretary Of The Air Force Self-retained platform cooling plate for turbine vane
US4893987A (en) * 1987-12-08 1990-01-16 General Electric Company Diffusion-cooled blade tip cap
US5667359A (en) * 1988-08-24 1997-09-16 United Technologies Corp. Clearance control for the turbine of a gas turbine engine
US5183385A (en) * 1990-11-19 1993-02-02 General Electric Company Turbine blade squealer tip having air cooling holes contiguous with tip interior wall surface
GB2256434A (en) * 1991-06-04 1992-12-09 Rolls Royce Plc Abrasive medium
US5660523A (en) * 1992-02-03 1997-08-26 General Electric Company Turbine blade squealer tip peripheral end wall with cooling passage arrangement
US5603603A (en) * 1993-12-08 1997-02-18 United Technologies Corporation Abrasive blade tip
JP3137527B2 (en) * 1994-04-21 2001-02-26 三菱重工業株式会社 Gas turbine blade tip cooling system
US5672261A (en) * 1996-08-09 1997-09-30 General Electric Company Method for brazing an end plate within an open body end, and brazed article
US5733102A (en) * 1996-12-17 1998-03-31 General Electric Company Slot cooled blade tip
JP3453268B2 (en) * 1997-03-04 2003-10-06 三菱重工業株式会社 Gas turbine blades
WO2000019065A1 (en) 1998-09-30 2000-04-06 Siemens Aktiengesellschaft Gas turbine moving blade and a method for producing a gas turbine moving blade
US6086328A (en) * 1998-12-21 2000-07-11 General Electric Company Tapered tip turbine blade
US6190129B1 (en) 1998-12-21 2001-02-20 General Electric Company Tapered tip-rib turbine blade
US6231307B1 (en) * 1999-06-01 2001-05-15 General Electric Company Impingement cooled airfoil tip
JP4649763B2 (en) * 2001-04-05 2011-03-16 株式会社Ihi Cooling air adjustment structure for turbine blades
US6558119B2 (en) 2001-05-29 2003-05-06 General Electric Company Turbine airfoil with separately formed tip and method for manufacture and repair thereof
US6634860B2 (en) 2001-12-20 2003-10-21 General Electric Company Foil formed structure for turbine airfoil tip
US7059834B2 (en) * 2003-01-24 2006-06-13 United Technologies Corporation Turbine blade
US20050091848A1 (en) * 2003-11-03 2005-05-05 Nenov Krassimir P. Turbine blade and a method of manufacturing and repairing a turbine blade
US7001151B2 (en) * 2004-03-02 2006-02-21 General Electric Company Gas turbine bucket tip cap
US7556477B2 (en) * 2005-10-04 2009-07-07 General Electric Company Bi-layer tip cap
EP1862640B1 (en) * 2006-05-31 2010-03-03 Siemens Aktiengesellschaft Turbine blade
US7726944B2 (en) * 2006-09-20 2010-06-01 United Technologies Corporation Turbine blade with improved durability tip cap
US7918642B2 (en) * 2007-01-10 2011-04-05 United Technologies Corporation Instrument port seal for RF measurement
US7722326B2 (en) * 2007-03-13 2010-05-25 Siemens Energy, Inc. Intensively cooled trailing edge of thin airfoils for turbine engines
US7922451B1 (en) 2007-09-07 2011-04-12 Florida Turbine Technologies, Inc. Turbine blade with blade tip cooling passages
FR2934008B1 (en) * 2008-07-21 2015-06-05 Turbomeca AUBE HOLLOW TURBINE WHEEL HAVING A RIB
DE102008047043A1 (en) * 2008-09-13 2010-03-18 Mtu Aero Engines Gmbh A gas turbine blade, gas turbine blade, gas turbine blade replacement, and gas turbine blade repair method
US8608443B2 (en) 2010-06-11 2013-12-17 Siemens Energy, Inc. Film cooled component wall in a turbine engine
US8734107B2 (en) * 2011-05-31 2014-05-27 General Electric Company Ceramic-based tip cap for a turbine bucket
FR2983517B1 (en) * 2011-12-06 2013-12-20 Snecma COLD TURBINE VANE FOR GAS TURBINE ENGINE.
US9470102B2 (en) 2012-05-09 2016-10-18 Siemens Energy, Inc. Crack resistant turbine vane and method for vane containment cap attachment
US9186757B2 (en) 2012-05-09 2015-11-17 Siemens Energy, Inc. Method of providing a turbine blade tip repair
JP6462332B2 (en) * 2014-11-20 2019-01-30 三菱重工業株式会社 Turbine blade and gas turbine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2213940A (en) * 1937-07-07 1940-09-03 Jendrassik George Rotor for gas turbines and rotary compressors
US3626568A (en) * 1969-04-23 1971-12-14 Avco Corp Method for bonding pins into holes in a hollow turbine blade
US3761201A (en) * 1969-04-23 1973-09-25 Avco Corp Hollow turbine blade having diffusion bonded therein
US3628885A (en) * 1969-10-01 1971-12-21 Gen Electric Fluid-cooled airfoil
US3635587A (en) * 1970-06-02 1972-01-18 Gen Motors Corp Blade cooling liner
US3732031A (en) * 1970-06-17 1973-05-08 Gen Motors Corp Cooled airfoil

Also Published As

Publication number Publication date
SE390434B (en) 1976-12-20
US3899267A (en) 1975-08-12
SE7607258L (en) 1976-06-23
CA996864A (en) 1976-09-14
NL7405529A (en) 1974-10-29
FR2227428A1 (en) 1974-11-22
FR2227428B1 (en) 1978-04-21
AU471766B2 (en) 1976-04-29
DE2418888A1 (en) 1974-11-07
AU6750174A (en) 1975-10-09
IT1007996B (en) 1976-10-30
GB1458734A (en) 1976-12-15
ES446914A1 (en) 1977-05-16
BE814272A (en) 1974-10-28
JPS5031402A (en) 1975-03-27

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