GB1277280A - Improvements in turbomachinery blades - Google Patents

Improvements in turbomachinery blades

Info

Publication number
GB1277280A
GB1277280A GB61712/69A GB6171269A GB1277280A GB 1277280 A GB1277280 A GB 1277280A GB 61712/69 A GB61712/69 A GB 61712/69A GB 6171269 A GB6171269 A GB 6171269A GB 1277280 A GB1277280 A GB 1277280A
Authority
GB
United Kingdom
Prior art keywords
plate
hole
chamber
turbine
wall
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
GB61712/69A
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 GB1277280A publication Critical patent/GB1277280A/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
    • F01D5/18—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
    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1277280 Making turbine and compressor blades GENERAL ELECTRIC CO 18 Dec 1969 [23 Jan 1969] 61712/69 Heading B3A [Also in Division F1] A method of sealing the internal chamber 18 of a hollow, cast, turbine or compressor blade, having a tip end wall 22 with a hole 24 therethrough formed by a supporting core pin (30), Fig. 4 (not shown), during the casting operation, comprises coating a plate 26 with brazing metal, inserting the plate into the chamber 18 so as to overlie the hole 24 and applying heat so as to bond the plate 26 to wall 22. Ribs 32 assist location of the plate 26. The latter may be inserted into the chamber 18 through hole 24 or through ports 20 in the blade root 12.
GB61712/69A 1969-01-23 1969-12-18 Improvements in turbomachinery blades Expired GB1277280A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US79343469A 1969-01-23 1969-01-23

Publications (1)

Publication Number Publication Date
GB1277280A true GB1277280A (en) 1972-06-07

Family

ID=25159913

Family Applications (1)

Application Number Title Priority Date Filing Date
GB61712/69A Expired GB1277280A (en) 1969-01-23 1969-12-18 Improvements in turbomachinery blades

Country Status (5)

Country Link
US (1) US3574482A (en)
BE (1) BE744593A (en)
DE (1) DE2001983A1 (en)
FR (1) FR2028934A1 (en)
GB (1) GB1277280A (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3761201A (en) * 1969-04-23 1973-09-25 Avco Corp Hollow turbine blade having diffusion bonded therein
US3715170A (en) * 1970-12-11 1973-02-06 Gen Electric Cooled turbine blade
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
US4073599A (en) * 1976-08-26 1978-02-14 Westinghouse Electric Corporation Hollow turbine blade tip closure
US4589824A (en) * 1977-10-21 1986-05-20 United Technologies Corporation Rotor blade having a tip cap end closure
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
US6474946B2 (en) * 2001-02-26 2002-11-05 United Technologies Corporation Attachment air inlet configuration for highly loaded single crystal turbine blades
US6837417B2 (en) * 2002-09-19 2005-01-04 Siemens Westinghouse Power Corporation Method of sealing a hollow cast member
US8622702B1 (en) 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
US10982551B1 (en) 2012-09-14 2021-04-20 Raytheon Technologies Corporation Turbomachine blade
US9546554B2 (en) * 2012-09-27 2017-01-17 Honeywell International Inc. Gas turbine engine components with blade tip cooling
EP3059394B1 (en) * 2015-02-18 2019-10-30 Ansaldo Energia Switzerland AG Turbine blade and set of turbine blades
US20170234447A1 (en) * 2016-02-12 2017-08-17 United Technologies Corporation Methods and systems for modulating airflow
US11199096B1 (en) 2017-01-17 2021-12-14 Raytheon Technologies Corporation Turbomachine blade

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH269598A (en) * 1944-01-31 1950-07-15 Power Jets Res & Dev Ltd Rotor blade on turbomachine working with hot working fluid.
US2618120A (en) * 1946-06-07 1952-11-18 Papini Anthony Coaxial combustion products generator and turbine with cooling means
GB742477A (en) * 1952-10-31 1955-12-30 Rolls Royce Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors

Also Published As

Publication number Publication date
BE744593A (en) 1970-07-01
FR2028934A1 (en) 1970-10-16
DE2001983A1 (en) 1970-07-30
US3574482A (en) 1971-04-13

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee