GB666536A - Stator blades for a gas turbine - Google Patents

Stator blades for a gas turbine

Info

Publication number
GB666536A
GB666536A GB22326/49A GB2232649A GB666536A GB 666536 A GB666536 A GB 666536A GB 22326/49 A GB22326/49 A GB 22326/49A GB 2232649 A GB2232649 A GB 2232649A GB 666536 A GB666536 A GB 666536A
Authority
GB
United Kingdom
Prior art keywords
blade
core
cooling air
blades
secured
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
GB22326/49A
Inventor
Horace Sinclair Rainbow
Donald Paul
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.)
Armstrong Siddeley Motors Ltd
Original Assignee
Armstrong Siddeley Motors 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 Armstrong Siddeley Motors Ltd filed Critical Armstrong Siddeley Motors Ltd
Publication of GB666536A publication Critical patent/GB666536A/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
    • 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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Landscapes

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

Abstract

666,536. Gas - turbine blades. ARMSTRONG SIDDELEY MOTORS, Ltd. June 19, 1950. [Aug. 27, 1949] No. 22326/49. Class 110(iii). A hollow stator blade through which cooling air flows longitudinally has a core 11 therein with a small clearance between the core and the blade to provide a continuous, narrow annular cooling passage adjacent the internal surface of the blade, the core, if hollow, having a closed end 16 at the cooling air inlet of the blade. Spaced projections 13 are formed at the ends of the core to locate it within the blade. The radially outer ends of the blades are secured in rhomboidal-shaped platforms 19 which together form a ring surface which is secured between inner and outer clamping rings 20, 21, cooling air being led from the compressor to the annular passage 24 and then flowing through the blades and being discharged therefrom through holes 17 in an axial direction on to a part of the rotor. Cooling air may also be discharged at intervals through apertures 17a spaced along the trailing edge of the blade. Specification 666,537 is referred to.
GB22326/49A 1949-08-27 1949-08-27 Stator blades for a gas turbine Expired GB666536A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB288549X 1949-08-27

Publications (1)

Publication Number Publication Date
GB666536A true GB666536A (en) 1952-02-13

Family

ID=10282240

Family Applications (1)

Application Number Title Priority Date Filing Date
GB22326/49A Expired GB666536A (en) 1949-08-27 1949-08-27 Stator blades for a gas turbine

Country Status (4)

Country Link
BE (1) BE498667A (en)
CH (1) CH288549A (en)
FR (1) FR1021265A (en)
GB (1) GB666536A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2847185A (en) * 1953-04-13 1958-08-12 Rolls Royce Hollow blading with means to supply fluid thereinto for turbines or compressors
US3166295A (en) * 1959-08-24 1965-01-19 Zakl Mech Im Gen K S Guide wheel for condensing turbines of great and greatest power
US3301527A (en) * 1965-05-03 1967-01-31 Gen Electric Turbine diaphragm structure
US3341114A (en) * 1966-03-04 1967-09-12 Gen Electric Anti-icing means
US4162136A (en) * 1974-04-05 1979-07-24 Rolls-Royce Limited Cooled blade for a gas turbine engine

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2709893A (en) * 1949-08-06 1955-06-07 Laval Steam Turbine Co Gas turbine power plant with heat exchanger and cooling means
NL81262C (en) * 1952-02-13
GB723505A (en) * 1952-11-18 1955-02-09 Parsons & Marine Eng Turbine Improvements in or relating to turbine nozzles
BE529252A (en) * 1953-06-01
DE1055884B (en) * 1954-03-02 1959-04-23 Bristol Aero Engines Ltd Flame tube for a combustion chamber of a gas turbine engine
US2956772A (en) * 1955-08-19 1960-10-18 John C Freche Liquid-spray cooling method
FR1177035A (en) * 1957-05-28 1959-04-20 Snecma Method and device for cooling machine parts
DE1210254B (en) * 1962-03-26 1966-02-03 Rolls Royce Gas turbine engine with cooled turbine blades
US3346235A (en) * 1963-12-23 1967-10-10 Papst Hermann Boundary layer control
US3365125A (en) * 1966-08-03 1968-01-23 Gen Motors Corp Turbomachinery
FR2654463A1 (en) * 1989-11-15 1991-05-17 Snecma TURBOMACHINE STATOR ELEMENT.
US5690469A (en) * 1996-06-06 1997-11-25 United Technologies Corporation Method and apparatus for replacing a vane assembly in a turbine engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2847185A (en) * 1953-04-13 1958-08-12 Rolls Royce Hollow blading with means to supply fluid thereinto for turbines or compressors
US3166295A (en) * 1959-08-24 1965-01-19 Zakl Mech Im Gen K S Guide wheel for condensing turbines of great and greatest power
US3301527A (en) * 1965-05-03 1967-01-31 Gen Electric Turbine diaphragm structure
US3341114A (en) * 1966-03-04 1967-09-12 Gen Electric Anti-icing means
US4162136A (en) * 1974-04-05 1979-07-24 Rolls-Royce Limited Cooled blade for a gas turbine engine

Also Published As

Publication number Publication date
FR1021265A (en) 1953-02-17
CH288549A (en) 1953-01-31
BE498667A (en)

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