GB851306A - Improvements in or relating to turbine blades - Google Patents

Improvements in or relating to turbine blades

Info

Publication number
GB851306A
GB851306A GB364558A GB364558A GB851306A GB 851306 A GB851306 A GB 851306A GB 364558 A GB364558 A GB 364558A GB 364558 A GB364558 A GB 364558A GB 851306 A GB851306 A GB 851306A
Authority
GB
United Kingdom
Prior art keywords
blade
rotor
cooling
zig
coolant
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
GB364558A
Inventor
Leonard James Dennis
Michael Joseph French
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son Ltd
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 D Napier and Son Ltd filed Critical D Napier and Son Ltd
Priority to GB364558A priority Critical patent/GB851306A/en
Publication of GB851306A publication Critical patent/GB851306A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/14Form or construction
    • F01D5/18Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/181Blades having a closed internal cavity containing a cooling medium, e.g. sodium
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02Blade-carrying members, e.g. rotors
    • F01D5/08Heating, heat-insulating or cooling means
    • F01D5/081Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/14Form or construction
    • F01D5/18Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades

Landscapes

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

Abstract

851,306. Turbine blades. NAPIER & SON Ltd., D. Jan. 19, 1959 (Feb. 4, 1958], No. 3645/58. Class 110 (3). In a turbine having blades 31, 32 on axiallyspaced rotor discs 25, 26 and wherein each blade is formed with at least one sealed internal cavity passage 14 extending through a major part of the blade length and into a blade root 12 and is partly filled with a coolant, having a melting point below 650‹ C., guides are porvided which in conjunction with cooling fins 20 on the blade roots direct a flow of cooling air over the blade roots on two rotor discs in turn, the air flowing in a zig-zag path over each blade root. The coolant is preferably sodium or an alloy which is solid at room temperature, but is liquid at 650‹ C. Between the rotor discs 25, 26 is an intermediate disc 27 rotating with them and co-operating with a labyrinth seal 28 on a stator blade ring 29. Cover-plates 34, 35 are secured to the outer faces of the turbine discs to co-operate with the fins 20 to form the zig-zag cooling flow passages. Cooling air is admitted between the rotor disc 25 and an end-plate 36 and flows through the zig-zag fin system, Fig. 1, through passages 33 in the intermediate disc 27, and then through the fin cooling system of the rotor blades 32. The plates 34, 35, 36, the walls of the passages 33 and the flanges 41 comprise the guides for the air. The coolant is circulated by convection and thermo-syphoning, the rate of circulation being multiplied by the high centrifugal effect when running.
GB364558A 1958-02-04 1958-02-04 Improvements in or relating to turbine blades Expired GB851306A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB364558A GB851306A (en) 1958-02-04 1958-02-04 Improvements in or relating to turbine blades

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB364558A GB851306A (en) 1958-02-04 1958-02-04 Improvements in or relating to turbine blades

Publications (1)

Publication Number Publication Date
GB851306A true GB851306A (en) 1960-10-12

Family

ID=9762234

Family Applications (1)

Application Number Title Priority Date Filing Date
GB364558A Expired GB851306A (en) 1958-02-04 1958-02-04 Improvements in or relating to turbine blades

Country Status (1)

Country Link
GB (1) GB851306A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4035102A (en) * 1975-04-01 1977-07-12 Kraftwerk Union Aktiengesellschaft Gas turbine of disc-type construction
US4484858A (en) * 1981-12-03 1984-11-27 Hitachi, Ltd. Turbine rotor with means for preventing air leaks through outward end of spacer
FR2557206A1 (en) * 1983-12-22 1985-06-28 United Technologies Corp TWO-STAGE ROTOR ARRANGEMENT WITH IMPROVED CIRCULATION OF THE COOLING AGENT
FR2557205A1 (en) * 1983-12-22 1985-06-28 United Technologies Corp ROTOR WITH DOUBLE PASS COOLING OF THE HEELS OF THE AUBES
JP2014163386A (en) * 2013-02-25 2014-09-08 General Electric Co <Ge> Drum rotor dovetail component and related drum rotor system
US20150157515A1 (en) * 2013-12-10 2015-06-11 Derek Amanatullah Cool Cut Cast Saw Blade

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4035102A (en) * 1975-04-01 1977-07-12 Kraftwerk Union Aktiengesellschaft Gas turbine of disc-type construction
US4484858A (en) * 1981-12-03 1984-11-27 Hitachi, Ltd. Turbine rotor with means for preventing air leaks through outward end of spacer
FR2557206A1 (en) * 1983-12-22 1985-06-28 United Technologies Corp TWO-STAGE ROTOR ARRANGEMENT WITH IMPROVED CIRCULATION OF THE COOLING AGENT
FR2557205A1 (en) * 1983-12-22 1985-06-28 United Technologies Corp ROTOR WITH DOUBLE PASS COOLING OF THE HEELS OF THE AUBES
GB2151715A (en) * 1983-12-22 1985-07-24 United Technologies Corp Two stage rotor assembly with improved coolant flow
GB2151714A (en) * 1983-12-22 1985-07-24 United Technologies Corp Rotor with double pass root blade root cooling
TR23227A (en) * 1983-12-22 1989-06-23 United Technologies Corp BREAKERED REFRIGERANT FLOW TWO-STAGE MOTOR HARDWARE
JP2014163386A (en) * 2013-02-25 2014-09-08 General Electric Co <Ge> Drum rotor dovetail component and related drum rotor system
US20150157515A1 (en) * 2013-12-10 2015-06-11 Derek Amanatullah Cool Cut Cast Saw Blade
US9468570B2 (en) * 2013-12-10 2016-10-18 Derek Amanatullah Cool cut cast saw blade

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