GB1467374A - Hollow turbomachinery blades - Google Patents

Hollow turbomachinery blades

Info

Publication number
GB1467374A
GB1467374A GB1120974A GB1120974A GB1467374A GB 1467374 A GB1467374 A GB 1467374A GB 1120974 A GB1120974 A GB 1120974A GB 1120974 A GB1120974 A GB 1120974A GB 1467374 A GB1467374 A GB 1467374A
Authority
GB
United Kingdom
Prior art keywords
bush
pin
hollow
insert
openings
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
GB1120974A
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 GB1467374A publication Critical patent/GB1467374A/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
    • F01D5/147—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
    • F01D5/12—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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Landscapes

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

Abstract

1467374 Turbine blades GENERAL ELECTRIC CO 13 March 1974 [30 March 1973] 11209/74 Heading F1T A hollow fluid-cooled blade 10 for a gas turbine engine includes two hollow inserts 36 each mounted in the interior of the blade mechanically by a pin 90 and a member formed with a hole in which the pin engages, e.g. a bush 68. As shown, the bush has end flanges 74 of circular shape welded in similar openings in the insert walls, the pin passing through the bush and openings in the blade root 12. The pin is brazed into the root openings as is the open end of the insert in the blade root. The bush may have external flats to increase the cross-section of the cooling fluid inlets to the inserts. Again, Figs. 5 and 6, (not shown), the bush end flanges may be tear-shaped, or, Figs. 9 and 10 (not shown), the flanges may be omitted and the ends of the cylindrical or tear-shaped bush webbed or brazed to the inner walls of the insert. Again, the bush is replaced by a hollow member (110), Fig. 7 and 8 (not shown), the hole being formed as a recess in which the pin engages.
GB1120974A 1973-03-30 1974-03-13 Hollow turbomachinery blades Expired GB1467374A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US346422A US3867068A (en) 1973-03-30 1973-03-30 Turbomachinery blade cooling insert retainers

Publications (1)

Publication Number Publication Date
GB1467374A true GB1467374A (en) 1977-03-16

Family

ID=23359308

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1120974A Expired GB1467374A (en) 1973-03-30 1974-03-13 Hollow turbomachinery blades

Country Status (10)

Country Link
US (1) US3867068A (en)
JP (1) JPS5026103A (en)
BE (1) BE813090A (en)
CA (1) CA994672A (en)
DE (1) DE2413292A1 (en)
FR (1) FR2223550B1 (en)
GB (1) GB1467374A (en)
IT (1) IT1003841B (en)
NL (1) NL7404257A (en)
SE (1) SE390433B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2121483A (en) * 1982-06-08 1983-12-21 Rolls Royce Cooled turbine blade for a gas turbine engine

Families Citing this family (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH582305A5 (en) * 1974-09-05 1976-11-30 Bbc Sulzer Turbomaschinen
US3966357A (en) * 1974-09-25 1976-06-29 General Electric Company Blade baffle damper
US3994622A (en) * 1975-11-24 1976-11-30 United Technologies Corporation Coolable turbine blade
GB1551678A (en) * 1978-03-20 1979-08-30 Rolls Royce Cooled rotor blade for a gas turbine engine
US4589824A (en) * 1977-10-21 1986-05-20 United Technologies Corporation Rotor blade having a tip cap end closure
GB2028928B (en) * 1978-08-17 1982-08-25 Ross Royce Ltd Aerofoil blade for a gas turbine engine
US4347037A (en) * 1979-02-05 1982-08-31 The Garrett Corporation Laminated airfoil and method for turbomachinery
FR2474095B1 (en) * 1980-01-17 1986-02-28 Rolls Royce VIBRATION DAMPING DEVICE FOR MOBILE BLADES OF A GAS TURBINE ENGINE
FR2476207A1 (en) * 1980-02-19 1981-08-21 Snecma IMPROVEMENT TO AUBES OF COOLED TURBINES
JPS5798387U (en) * 1980-12-10 1982-06-17
DE3110096C2 (en) * 1981-03-16 1983-05-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbine blades for gas turbine engines
US5125798A (en) * 1990-04-13 1992-06-30 General Electric Company Method and apparatus for cooling air flow at gas turbine bucket trailing edge tip
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
US5207556A (en) * 1992-04-27 1993-05-04 General Electric Company Airfoil having multi-passage baffle
EP0894558A1 (en) * 1997-07-29 1999-02-03 Siemens Aktiengesellschaft Turbine blade and method of fabrication of a turbine blade
US6193465B1 (en) 1998-09-28 2001-02-27 General Electric Company Trapped insert turbine airfoil
EP1006263B1 (en) 1998-11-30 2004-01-07 ALSTOM (Switzerland) Ltd Vane cooling
US6450759B1 (en) * 2001-02-16 2002-09-17 General Electric Company Gas turbine nozzle vane insert and methods of installation
US6752594B2 (en) 2002-02-07 2004-06-22 The Boeing Company Split blade frictional damper
US6699015B2 (en) 2002-02-19 2004-03-02 The Boeing Company Blades having coolant channels lined with a shape memory alloy and an associated fabrication method
GB2405186B (en) * 2003-08-20 2005-10-26 Rolls Royce Plc A component with internal damping
US7220103B2 (en) * 2004-10-18 2007-05-22 United Technologies Corporation Impingement cooling of large fillet of an airfoil
EP1847696A1 (en) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Component for a secondary combustion system in a gas turbine and corresponding gas turbine.
US8007242B1 (en) * 2009-03-16 2011-08-30 Florida Turbine Technologies, Inc. High temperature turbine rotor blade
US8052391B1 (en) * 2009-03-25 2011-11-08 Florida Turbine Technologies, Inc. High temperature turbine rotor blade
RU2543100C2 (en) * 2010-11-29 2015-02-27 Альстом Текнолоджи Лтд Working blade for gas turbine, manufacturing method for such blade and gas turbine with such blade
US20130223987A1 (en) * 2012-02-29 2013-08-29 Scott Stafford Turbine Nozzle Insert
SG11201506824PA (en) * 2013-04-03 2015-10-29 United Technologies Corp Variable thickness trailing edge cavity and method of making
JP6392342B2 (en) * 2013-07-19 2018-09-19 ゼネラル・エレクトリック・カンパニイ Turbine nozzle with impingement baffle
EP3044418B1 (en) 2013-09-06 2020-01-08 United Technologies Corporation Gas turbine engine airfoil with wishbone baffle cooling scheme
EP2957724A1 (en) * 2014-06-17 2015-12-23 Siemens Aktiengesellschaft Turbine blade and turbine
DE102014220787A1 (en) * 2014-10-14 2016-04-14 Siemens Aktiengesellschaft Gas turbine component with internal module and method for its production using Selective Laser Melting
US10626740B2 (en) 2016-12-08 2020-04-21 General Electric Company Airfoil trailing edge segment
US11220916B2 (en) 2020-01-22 2022-01-11 General Electric Company Turbine rotor blade with platform with non-linear cooling passages by additive manufacture
US11242760B2 (en) * 2020-01-22 2022-02-08 General Electric Company Turbine rotor blade with integral impingement sleeve by additive manufacture
US11492908B2 (en) 2020-01-22 2022-11-08 General Electric Company Turbine rotor blade root with hollow mount with lattice support structure by additive manufacture
US11248471B2 (en) 2020-01-22 2022-02-15 General Electric Company Turbine rotor blade with angel wing with coolant transfer passage between adjacent wheel space portions by additive manufacture

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2779565A (en) * 1948-01-05 1957-01-29 Bruno W Bruckmann Air cooling of turbine blades
US3700348A (en) * 1968-08-13 1972-10-24 Gen Electric Turbomachinery blade structure

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2121483A (en) * 1982-06-08 1983-12-21 Rolls Royce Cooled turbine blade for a gas turbine engine

Also Published As

Publication number Publication date
FR2223550A1 (en) 1974-10-25
CA994672A (en) 1976-08-10
US3867068A (en) 1975-02-18
IT1003841B (en) 1976-06-10
NL7404257A (en) 1974-10-02
FR2223550B1 (en) 1978-01-13
BE813090A (en) 1974-09-30
JPS5026103A (en) 1975-03-19
DE2413292A1 (en) 1974-10-10
SE390433B (en) 1976-12-20

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Legal Events

Date Code Title Description
CSNS Application of which complete specification have been accepted and published, but patent is not sealed