GB1472570A - Gas turbines - Google Patents

Gas turbines

Info

Publication number
GB1472570A
GB1472570A GB3212574A GB3212574A GB1472570A GB 1472570 A GB1472570 A GB 1472570A GB 3212574 A GB3212574 A GB 3212574A GB 3212574 A GB3212574 A GB 3212574A GB 1472570 A GB1472570 A GB 1472570A
Authority
GB
United Kingdom
Prior art keywords
recess
coolant
blades
passages
rotor
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
GB3212574A
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 GB1472570A publication Critical patent/GB1472570A/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the 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
    • F01D5/185—Liquid 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Abstract

1472570 Gas turbine blades rotor-cooling GENERAL ELECTRIC CO 19 July 1974 [2 Aug 1973] 32125/74 Headings F1G and F1T The invention relates to a gas turbine bladed rotor assembly in which means are provided for supplying liquid coolant on to the rim of the rotor disc for flow through passages extending through the blades. The rotor disc is formed at its periphery 12 with axial slots 11 in which the blades 10 are mounted by their roots. A ring member 13 is secured at each side of the rotor disc for example by shrinking to retain the blades in position, each ring member being formed with an annular recess 16 into which liquid coolant is supplied through a nozzle 14. The coolant passes from the recess through a plurality of openings 17 into a recess 18 formed at the underside of each blade platform 19. The liquid then passes over the lip 22 to a further recess 23 from which it discharges through passages 26 and then through passages 27 extending through the aerofoil portion 29. The coolant collects in a manifold recess 31 at the blade tip from which it discharges through outlet 33; a similar flow of coolant is provided for at each blade face, the two flows discharging through a common outlet 33.
GB3212574A 1973-08-02 1974-07-19 Gas turbines Expired GB1472570A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US38509673A 1973-08-02 1973-08-02

Publications (1)

Publication Number Publication Date
GB1472570A true GB1472570A (en) 1977-05-04

Family

ID=23519984

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3212574A Expired GB1472570A (en) 1973-08-02 1974-07-19 Gas turbines

Country Status (7)

Country Link
JP (1) JPS5070709A (en)
CA (1) CA1005344A (en)
FR (1) FR2239590A1 (en)
GB (1) GB1472570A (en)
IT (1) IT1017694B (en)
NL (1) NL7410063A (en)
NO (1) NO742784L (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2825801A1 (en) * 1977-06-15 1979-01-04 Gen Electric LIQUID-COOLED TURBINE SHOVEL WITH IMPROVED HEAT TRANSFER CAPACITY
GB2413598A (en) * 2004-05-01 2005-11-02 Rolls Royce Plc Providing cooling gas to turbine blade and disc in gas turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2825801A1 (en) * 1977-06-15 1979-01-04 Gen Electric LIQUID-COOLED TURBINE SHOVEL WITH IMPROVED HEAT TRANSFER CAPACITY
GB2413598A (en) * 2004-05-01 2005-11-02 Rolls Royce Plc Providing cooling gas to turbine blade and disc in gas turbine engine

Also Published As

Publication number Publication date
IT1017694B (en) 1977-08-10
JPS5070709A (en) 1975-06-12
CA1005344A (en) 1977-02-15
NO742784L (en) 1975-03-03
NL7410063A (en) 1975-02-04
FR2239590A1 (en) 1975-02-28

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]