US3899267A - Turbomachinery blade tip cap configuration - Google Patents

Turbomachinery blade tip cap configuration Download PDF

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Publication number
US3899267A
US3899267A US355150A US35515073A US3899267A US 3899267 A US3899267 A US 3899267A US 355150 A US355150 A US 355150A US 35515073 A US35515073 A US 35515073A US 3899267 A US3899267 A US 3899267A
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US
United States
Prior art keywords
tip cap
blade
tip
turbomachinery blade
further characterized
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 - Lifetime
Application number
US355150A
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English (en)
Inventor
Ronald E Dennis
William D Treece
Robert J Corsmeier
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
Priority to US355150A priority Critical patent/US3899267A/en
Priority to CA195,905A priority patent/CA996864A/en
Priority to AU67501/74A priority patent/AU471766B2/en
Priority to DE2418888A priority patent/DE2418888A1/de
Priority to GB1729174A priority patent/GB1458734A/en
Priority to IT21729/74A priority patent/IT1007996B/it
Priority to NL7405529A priority patent/NL7405529A/xx
Priority to FR7414140A priority patent/FR2227428B1/fr
Priority to BE143692A priority patent/BE814272A/xx
Priority to SE7405664A priority patent/SE390434B/sv
Priority to JP49046721A priority patent/JPS5031402A/ja
Priority to ES425740A priority patent/ES425740A1/es
Priority to US05/530,720 priority patent/US4020538A/en
Application granted granted Critical
Publication of US3899267A publication Critical patent/US3899267A/en
Priority to ES446914A priority patent/ES446914A1/es
Priority to SE7607258A priority patent/SE7607258L/sv
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/20—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

Definitions

  • An improved tip cap configuration for a turbomachinery blade includes tip cap seats formed integrally with and located on the inner sides of a hollow turbomachinery blade. Tip cap retaining members are also formed integrally with the inner wall of the blade and arespaced a short radial distance from the tip cap seats.
  • the blade is initially provided with a flared open end and the tip caps are positioned on the seats and the flared end is crimped so as to capture the tip cap between the seats and the retaining members.
  • the crimping operation is stopped at a point wherein a smooth outer contour is obtained for the blade in the region of the tip cap.
  • a method of making such a blade is also disclosed.
  • This invention relates primarily to tubomachinery blading and, more particularly, to an improved tip cap configuration for a hollow turbomachinery blade and a method of making such a configuration.
  • Coolant is delivered to the interiorof such an insert and is expelled through a multiplicity of small holes against an internal wall of the turbomachinery blade, thereby cooling that portion of the turbomachinery blade which is exposed to the hot gas stream.
  • turbomachinery blade tip cap configuration which overcomes the problems of the prior art configurations. It is a further object of this invention to provide such a tip cap configuration which is mechanically secured by the blade member and which provides an airfoilshaped tip which is free from distortion and which is capable of being cooled by coolant from the interior of the blade. Another object of this invention is to provide a new method for making a turbomachinery blade which includes the inventive tip cap configuration.
  • a hollow turbomachinery blade which is initially formed with a flared, open tip end.
  • the flared, open end is provided with tip cap seats which are formed integrally with and located along the inner walls of the hollow blade member.
  • Tip cap retainers are also formed integrally with the inner walls of the hollow blade member and are spaced a short distance from the tip cap seat.
  • the tip cap which may have a generally U-shaped cross section, is inserted into the flared, open end and is positioned upon the tip cap seats.
  • the flared end is then crimped into a nondistorted airfoil-shaped member such that the tip cap retainers are positioned above the tip cap, thereby capturing the tip cap between the seats and the retainers.
  • Coolant holes are positioned around the perimeter of the tip cap and are angled so as to impinge coolant against the inner sides of the tip portion of the airfoil-shaped member.
  • FIG. 1 is an axial, cross-sectional view of a prior art tip cap configuration
  • FIG. 2 is a top plan view of another prior art tip cap configuration
  • FIG. 3 is a sectional view, taken along line 33 of FIG. 2;
  • FIG. 4 is a partial sectional view of the inventive tip cap configuration showing an initial step of manufacture
  • FIG. 5 is a partial cross-sectional view, similar to FIG. 4, taken generally along line 55 of FIG. 6 and showing the completed tip cap configuration;
  • FIG. 6 is a top plan view of the inventive tip cap configuration.
  • FIGS. I through 3 wherein prior art attempts at tip cap retention are shown.
  • one initial attempt at retaining a tip cap 10 in the open end 12 of the airfoil-shaped blade consisted simply of brazing the tip cap end directly to the side walls 14 and 16 of the airfoil-shaped blade.
  • a suitable braze alloy 18 was placed at the joint between the tip cap 10 and the side walls 14 and 16, and the assembly was heated in an appropriate furnace. This type of configuration normally was adequately sealed but had poor mechanical integrity due to the inconsistency of the braze joint.
  • sepa rate retention members such as a pin 20
  • a pin 20 were occasionally inserted through holes 22 positioned in the side walls 14 and 16 of the blade.
  • the pins 20 were then brazed to the side walls 14 and 16 with a suitable braze alloy 24.
  • This configuration improved the mechanical integrity of the joint and kept the tip cap in place, but the configuration disrupted the external airfoil shape due to the projecting portion of the pins and the braze alloy 24 located on the outer side of the side walls 14 and 16.
  • the pins 20 also increased the tip stress and added weight and complexity to the design.
  • FIGS. 2 and 3 A further attempt at retaining the tip caps without adding complexity to the blade is shown in FIGS. 2 and 3 wherein a tip cap 26 is positioned between a pair of side walls 28 and 30, and tip portions 32 and 34 of the side walls 28 and 30, respectively, are crimped toward one another at certain locations along the airfoil as shown in FIGS. 2 and 3. By crimping the portions 32 and 34, the tip cap 26 was secured to the airfoil blade.
  • the design shown in FIGS. 2 and 3 distorts the desired airfoil shape at the blade tip thereby potentia l ly reducing the overall efficiency of such a blade.
  • a turbomachinery blade constructed in accordance with the present invention is designated by the general numeral 36.
  • the blade 36 is provided with a hollow airfoil section 38 which includes a pair of side walls 40 and 42 which define an internal cavity 44.
  • the turbomachinery blade 36 is formed initially with a flared, open end 46, which is provided by angled tip ends 48 and 50 of the side walls 40 and 42.
  • the side walls 40 and 42 are indented so as to provide tip cap seats 52 and 54, respectively.
  • the side walls 40 and 42 are provided with tip cap retaining members, which in the present case take the form of a plurality of rabbets 56 and 58 formed integrally with the angled tip ends 48 and 50 of the side walls 40 and 42.
  • the flared open end 46 of the turbomachinery blade is flared to a sufficient width such that a tip cap 60 may be inserted through the opening formed between the rabbets 56 and 58 and positioned on the tip cap seats 52 and 54.
  • the tip cap 60 may take the form of a casting or of a coined piece and, as shown in FIGS. 4 and 5, may be provided with a generally U-shaped cross section having a bight portion 62 and a pair of upstanding leg members 64 and 66.
  • the tip cap 60 provides a generally airfoil-shaped flat plate capable of sealing the entire opening formed between side walls 40 and 42 of the turbomachinery blade 36.
  • the tip cap 60 is provided with a plurality of coolant holes 68, which extend through the bight portion 62 thereof.
  • Each of the holes 68 is drilled or cast at an angle a (FIG. 5) with respect to the vertical so as to direct coolant fluid against the inner sides of the side walls 40 and 42 near the region of the rabbets 56 and 58.
  • the holes 68 are spaced around the entire perimeter of the tip cap 60.
  • the angled holes and the spacing around the entire perimeter of the tip cap provide two basic features, namely improved tip region cooling and improved aerodynamic sealing at the 'blade tip.
  • the hot gas stream air is further precluded from leaking over the blade tip into the cavity formed above the tip cap 60 even more than was true in the case of a smaller number of larger holes 70 provided in the tip cap shown in FIG. 2.
  • the angled ends 48 and of the side walls 40 and 42 are formed, such as by crimping, to the configuration shown in FIGS. 5 and 6, wherein the tip cap is captured between the seats 52 and 54 and the rabbets 56 and 58.
  • the side walls 40 and 42 are provided with smooth outer contours 72 and 74 which, in turn, provide a desired airfoil configuration along the entire radial height of the blade. In other words, no disruptions in the external airfoil shape are caused near the tip of the blade, while the tip cap 60 is mechanically secured theeto.
  • the smooth outer contour results in a straight radial line for the outer contour when a section is taken through the blade tip at any point between the leadingand trailing edge of the blade.
  • a suitable braze alloy may be positioned around the perimeter of the tip cap 60 before or after it is placed on the tip cap seats 52 and 54, as shown in FIG. 4.
  • the blade can thereafter be placed in a furnace in which the braze alloy is heated to form a seal and to further retain the tip cap 60 in place.
  • the upstanding leg portions 64 and 66 of the tip cap 60 are sized so as to fit between the tip cap seats 52 and 54 and the retaining members or rabbets 56 and 58. In this manner, the tip cap 60 is both mechanically secured and, if necessary, brazed to the turbomachinery blade in a desired location.
  • a turbomachinery blade of the type comprising an airfoil-shaped, hollow body portion having a pair of side walls defining an internal cavity therebetween, and an airfoil-shaped tip cap defining the outer bounds of said internal cavity, the improvement comprising:
  • eachof said side walls includes a tip cap seat formed integrally therewith on the inner side thereof and at least one tip cap retaining member formed integrally therewith on the inner side thereof and radially spaced from said seat so as to be capable of capturing said tip cap between said seats and said retaining members such that said tip cap is mechanically secured to said blade.
  • the improved turbomachinery blade of claim 1 further characterized in that said hollow body portion has a smooth radially extending outer contour in the region of said tip cap.
  • the improved turbomachinery blade of claim 1 further characterized in that said tip cap has a generally U-shaped cross section including a bight portion and a pair of leg members and each of said leg members is sized so as to fit between said seat and one of said retaining members.
  • the improved turbomachinery blade of claim 3 further characterized in that said bight portion is provided with a plurality of coolant holes.
  • the improved turbomachinery blade of claim 4 further characterized in that said holes are spaced around the circumference of said tip cap.
US355150A 1973-04-27 1973-04-27 Turbomachinery blade tip cap configuration Expired - Lifetime US3899267A (en)

Priority Applications (15)

Application Number Priority Date Filing Date Title
US355150A US3899267A (en) 1973-04-27 1973-04-27 Turbomachinery blade tip cap configuration
CA195,905A CA996864A (en) 1973-04-27 1974-03-25 Turbomachinery blade tip cap configuration
AU67501/74A AU471766B2 (en) 1973-04-27 1974-04-03 Turbomachinery blade tip cap configuration
DE2418888A DE2418888A1 (de) 1973-04-27 1974-04-19 Turbomaschinenblatt mit spitzenkappe
GB1729174A GB1458734A (en) 1973-04-27 1974-04-19 Manufacture of hollow turbomachinery blades
IT21729/74A IT1007996B (it) 1973-04-27 1974-04-22 Configurazione di copertura per palette di turbina
FR7414140A FR2227428B1 (sv) 1973-04-27 1974-04-24
NL7405529A NL7405529A (sv) 1973-04-27 1974-04-24
BE143692A BE814272A (fr) 1973-04-27 1974-04-26 Aube de turbomachine
SE7405664A SE390434B (sv) 1973-04-27 1974-04-26 Anordning vid turbomaskinskovel samt sett for dess framstellning
JP49046721A JPS5031402A (sv) 1973-04-27 1974-04-26
ES425740A ES425740A1 (es) 1973-04-27 1974-04-27 Perfeccionamientos en un alabe de turbomaquina.
US05/530,720 US4020538A (en) 1973-04-27 1974-12-09 Turbomachinery blade tip cap configuration
ES446914A ES446914A1 (es) 1973-04-27 1976-04-12 Un metodo de fabricar un alabe de turbomaquina hueco.
SE7607258A SE7607258L (sv) 1973-04-27 1976-06-23 Anordning vid turbomaskinskovel

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

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US05/530,720 Division US4020538A (en) 1973-04-27 1974-12-09 Turbomachinery blade tip cap configuration

Publications (1)

Publication Number Publication Date
US3899267A true US3899267A (en) 1975-08-12

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US355150A Expired - Lifetime US3899267A (en) 1973-04-27 1973-04-27 Turbomachinery blade tip cap configuration

Country Status (12)

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

Cited By (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US4010531A (en) * 1975-09-02 1977-03-08 General Electric Company Tip cap apparatus and method of installation
DE2853959A1 (de) * 1977-12-21 1979-06-28 Gen Electric Gasdichtung und verfahren zu deren herstellung
US4214355A (en) * 1977-12-21 1980-07-29 General Electric Company Method for repairing a turbomachinery blade tip
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
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
DE3525079A1 (de) * 1984-07-23 1986-01-30 General Electric Co., Schenectady, N.Y. Verfahren sowie band- und teilchenteil zum aufbringen von vorgewaehlten schleifteilchen auf eine oberflaeche
US4589823A (en) * 1984-04-27 1986-05-20 General Electric Company Rotor blade tip
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
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
US5355637A (en) * 1991-06-04 1994-10-18 Rolls-Royce Plc Abrasive medium
US5551840A (en) * 1993-12-08 1996-09-03 United Technologies Corporation Abrasive blade tip
US5564902A (en) * 1994-04-21 1996-10-15 Mitsubishi Jukogyo Kabushiki Kaisha Gas turbine rotor blade tip cooling device
US5660523A (en) * 1992-02-03 1997-08-26 General Electric Company Turbine blade squealer tip peripheral end wall with cooling passage arrangement
US5667359A (en) * 1988-08-24 1997-09-16 United Technologies Corp. Clearance control for the turbine of a gas turbine engine
US5733102A (en) * 1996-12-17 1998-03-31 General Electric Company Slot cooled blade tip
WO2000019065A1 (de) 1998-09-30 2000-04-06 Siemens Aktiengesellschaft Gasturbinenlaufschaufel und verfahren zur herstellung einer gasturbinenlaufschaufel
US6056507A (en) * 1996-08-09 2000-05-02 General Electric Company Article with brazed end plate within an open body end
DE19809008C2 (de) * 1997-03-04 2000-06-08 Mitsubishi Heavy Ind Ltd Gasturbinenschaufel
US6086328A (en) * 1998-12-21 2000-07-11 General Electric Company Tapered tip turbine blade
EP1057970A2 (en) * 1999-06-01 2000-12-06 General Electric Company Impingement cooled airfoil tip
US6190129B1 (en) 1998-12-21 2001-02-20 General Electric Company Tapered tip-rib turbine blade
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
US20050091848A1 (en) * 2003-11-03 2005-05-05 Nenov Krassimir P. Turbine blade and a method of manufacturing and repairing a turbine blade
US20050196277A1 (en) * 2004-03-02 2005-09-08 General Electric Company Gas turbine bucket tip cap
US20070077143A1 (en) * 2005-10-04 2007-04-05 General Electric Company Bi-layer tip cap
EP1441107A3 (en) * 2003-01-24 2007-08-22 United Technologies Corporation Turbine blade
EP1862640A1 (de) 2006-05-31 2007-12-05 Siemens Aktiengesellschaft Turbinenschaufel
US20080187436A1 (en) * 2007-01-10 2008-08-07 Leogrande John A Instrument port seal for rf measurement
US20080226461A1 (en) * 2007-03-13 2008-09-18 Siemens Power Generation, Inc. Intensively cooled trailing edge of thin airfoils for turbine engines
US20100080711A1 (en) * 2006-09-20 2010-04-01 United Technologies Corporation Turbine blade with improved durability tip cap
US7922451B1 (en) 2007-09-07 2011-04-12 Florida Turbine Technologies, Inc. Turbine blade with blade tip cooling passages
US20110250072A1 (en) * 2008-09-13 2011-10-13 Mtu Aero Engines Gmbh Replacement part for a gas turbine blade of a gas turbine, gas turbine blade and method for repairing a gas turbine blade
WO2011156805A1 (en) * 2010-06-11 2011-12-15 Siemens Energy, Inc. Film cooled component wall in a turbine engine
CN102808655A (zh) * 2011-05-31 2012-12-05 通用电气公司 用于涡轮轮叶的基于陶瓷的尖部帽
US20130142668A1 (en) * 2011-12-06 2013-06-06 Snecma Cooled turbine blade for gas turbine engine
US9186757B2 (en) 2012-05-09 2015-11-17 Siemens Energy, Inc. Method of providing a turbine blade tip repair
US9470102B2 (en) 2012-05-09 2016-10-18 Siemens Energy, Inc. Crack resistant turbine vane and method for vane containment cap attachment
US20170226866A1 (en) * 2014-11-20 2017-08-10 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine

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JP4649763B2 (ja) * 2001-04-05 2011-03-16 株式会社Ｉｈｉ タービン翼の冷却空気調整構造
FR2934008B1 (fr) * 2008-07-21 2015-06-05 Turbomeca Aube creuse de roue de turbine comportant une nervure

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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
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
US3761201A (en) * 1969-04-23 1973-09-25 Avco Corp Hollow turbine blade having diffusion bonded therein

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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

Cited By (67)

* 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
DE2853959A1 (de) * 1977-12-21 1979-06-28 Gen Electric Gasdichtung und verfahren zu deren herstellung
US4214355A (en) * 1977-12-21 1980-07-29 General Electric Company Method for repairing a turbomachinery blade tip
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
DE3525079A1 (de) * 1984-07-23 1986-01-30 General Electric Co., Schenectady, N.Y. Verfahren sowie band- und teilchenteil zum aufbringen von vorgewaehlten schleifteilchen auf eine oberflaeche
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
US5355637A (en) * 1991-06-04 1994-10-18 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
US5551840A (en) * 1993-12-08 1996-09-03 United Technologies Corporation Abrasive blade tip
US5603603A (en) * 1993-12-08 1997-02-18 United Technologies Corporation Abrasive blade tip
US5564902A (en) * 1994-04-21 1996-10-15 Mitsubishi Jukogyo Kabushiki Kaisha Gas turbine rotor blade tip cooling device
US6056507A (en) * 1996-08-09 2000-05-02 General Electric Company Article with brazed end plate within an open body end
US5733102A (en) * 1996-12-17 1998-03-31 General Electric Company Slot cooled blade tip
DE19809008C2 (de) * 1997-03-04 2000-06-08 Mitsubishi Heavy Ind Ltd Gasturbinenschaufel
WO2000019065A1 (de) 1998-09-30 2000-04-06 Siemens Aktiengesellschaft Gasturbinenlaufschaufel und verfahren zur herstellung einer gasturbinenlaufschaufel
US6190129B1 (en) 1998-12-21 2001-02-20 General Electric Company Tapered tip-rib turbine blade
US6086328A (en) * 1998-12-21 2000-07-11 General Electric Company Tapered tip turbine blade
EP1057970A2 (en) * 1999-06-01 2000-12-06 General Electric Company Impingement cooled airfoil tip
US6231307B1 (en) * 1999-06-01 2001-05-15 General Electric Company Impingement cooled airfoil tip
EP1057970A3 (en) * 1999-06-01 2002-10-30 General Electric Company Impingement cooled airfoil tip
US6558119B2 (en) 2001-05-29 2003-05-06 General Electric Company Turbine airfoil with separately formed tip and method for manufacture and repair thereof
US6595749B2 (en) 2001-05-29 2003-07-22 General Electric Company Turbine airfoil 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
EP1441107A3 (en) * 2003-01-24 2007-08-22 United Technologies Corporation Turbine blade
EP2302168A1 (en) * 2003-01-24 2011-03-30 United Technologies Corporation Turbine blade
EP1950380A1 (en) * 2003-01-24 2008-07-30 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
CN100404793C (zh) * 2004-03-02 2008-07-23 通用电气公司 燃气涡轮叶片梢帽
US7001151B2 (en) 2004-03-02 2006-02-21 General Electric Company Gas turbine bucket tip cap
US20050196277A1 (en) * 2004-03-02 2005-09-08 General Electric Company Gas turbine bucket tip cap
US20070077143A1 (en) * 2005-10-04 2007-04-05 General Electric Company Bi-layer tip cap
US7556477B2 (en) * 2005-10-04 2009-07-07 General Electric Company Bi-layer tip cap
EP1862640A1 (de) 2006-05-31 2007-12-05 Siemens Aktiengesellschaft Turbinenschaufel
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Also Published As

Publication number Publication date
ES425740A1 (es) 1976-12-16
GB1458734A (en) 1976-12-15
CA996864A (en) 1976-09-14
SE390434B (sv) 1976-12-20
JPS5031402A (sv) 1975-03-27
AU6750174A (en) 1975-10-09
NL7405529A (sv) 1974-10-29
SE7607258L (sv) 1976-06-23
ES446914A1 (es) 1977-05-16
FR2227428B1 (sv) 1978-04-21
AU471766B2 (en) 1976-04-29
IT1007996B (it) 1976-10-30
BE814272A (fr) 1974-10-28
FR2227428A1 (sv) 1974-11-22
DE2418888A1 (de) 1974-11-07

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