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GB753224A - Improvements in or relating to blading for turbines or compressors - Google Patents

Improvements in or relating to blading for turbines or compressors

Info

Publication number
GB753224A
GB753224A GB10085/53A GB1008553A GB753224A GB 753224 A GB753224 A GB 753224A GB 10085/53 A GB10085/53 A GB 10085/53A GB 1008553 A GB1008553 A GB 1008553A GB 753224 A GB753224 A GB 753224A
Authority
GB
United Kingdom
Prior art keywords
cavity
ducts
outlets
guide vane
blade
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
GB10085/53A
Inventor
James Alexander Petrie
Charles William Robey
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB10085/53A priority Critical patent/GB753224A/en
Priority to US419476A priority patent/US2847185A/en
Priority to FR1097531D priority patent/FR1097531A/en
Priority to CH322022D priority patent/CH322022A/en
Publication of GB753224A publication Critical patent/GB753224A/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
    • 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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Landscapes

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

Abstract

753,224. Turbine and compressor blades. ROLLS-ROYCE, Ltd. March 30, 1954 [April 13, 1953], No. 10085/53. Class 110(3) [Also in Group XXII] A hollow blade for use in a turbine or compressor has a fluid-delivery duct extending through the cavity or bore of the blade substantially from end to end thereof with clearance from the wall of the cavity, the duct having an inlet thereto at least at one end of the blade and having an outlet to within the blade cavity, there being also outlets from the cavity. In Figs. 1, 2 and 4 the gas turbine inlet nozzle guide vanes comprise a sheet metal shell 18 mounted at its inner and outer ends in platforms 25, 26 and having two tubular ducts 19, 20 within its cavity. The ducts 19, 20 are closed at their inner ends but are formed with slots 24 at their edges adjacent the leading edges of the guide vanes. The ends of the vanes are flanged at 21 to engage the ducts, and the ducts are formed with blislers 23 which engage the wall of the cavity. Each inner platform 25 is flanged at 27 to receive the guide vane and is formed with a dog 28 which engages between castellations 29 of the ring 30 forming parts of the inner stator structure. The platform 25 is also formed with a hooked projection 31 which engages an axial projection 32 on the stator ring 30. The outer platform 26 is formed with dogs 37, 40 which engage in notches 38, 41 in the outer stator casing 12. The trailing edge of the guide vane is formed with outlets 22. Cooling air flows into the two ducts and out of the leading edges thereof and finally discharges through the outlets 22 into the working fluid stream. In. Fig. 8, a single tubular duct 50 is provided in the nozzle guide vane, the duct being flattened at 51 to form a pair of passages 53 having outlets 52 from which cooling air discharges as in the first embodiment. The inner end of the guide vane is mounted in an annular structure formed by parts 54, 55 and the outer end is mounted in an annular member 61. Cooling air is supplied to the annular spaces at the inner and outer ends of the vanes.
GB10085/53A 1953-04-13 1953-04-13 Improvements in or relating to blading for turbines or compressors Expired GB753224A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB10085/53A GB753224A (en) 1953-04-13 1953-04-13 Improvements in or relating to blading for turbines or compressors
US419476A US2847185A (en) 1953-04-13 1954-03-29 Hollow blading with means to supply fluid thereinto for turbines or compressors
FR1097531D FR1097531A (en) 1953-04-13 1954-04-02 Improvements to turbine or compressor blades
CH322022D CH322022A (en) 1953-04-13 1954-04-13 Hollow blade for turbo machines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB10085/53A GB753224A (en) 1953-04-13 1953-04-13 Improvements in or relating to blading for turbines or compressors

Publications (1)

Publication Number Publication Date
GB753224A true GB753224A (en) 1956-07-18

Family

ID=29726705

Family Applications (1)

Application Number Title Priority Date Filing Date
GB10085/53A Expired GB753224A (en) 1953-04-13 1953-04-13 Improvements in or relating to blading for turbines or compressors

Country Status (4)

Country Link
US (1) US2847185A (en)
CH (1) CH322022A (en)
FR (1) FR1097531A (en)
GB (1) GB753224A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1092255B (en) * 1957-05-28 1960-11-03 Snecma Method for cooling machine parts, in particular hollow gas turbine blades
DE1300349B (en) * 1964-07-06 1969-07-31 Rolls Royce Deicing device for a gas turbine jet engine

Families Citing this family (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2955800A (en) * 1957-05-28 1960-10-11 Gen Motors Corp Turbomachine stator assembly
DE1204021B (en) * 1959-04-27 1965-10-28 Rolls Royce Blade for axial flow machines, especially gas turbines
GB895077A (en) * 1959-12-09 1962-05-02 Rolls Royce Blades for fluid flow machines such as axial flow turbines
US3062499A (en) * 1960-05-18 1962-11-06 United Aircraft Corp Vane mounting and seal
DE1210253B (en) * 1961-05-02 1966-02-03 Rolls Royce Blade for flow machines, especially for gas turbines
GB960071A (en) * 1961-08-30 1964-06-10 Rolls Royce Improvements relating to cooled blades such as axial flow gas turbine blades
US3314648A (en) * 1961-12-19 1967-04-18 Gen Electric Stator vane assembly
US3420502A (en) * 1962-09-04 1969-01-07 Gen Electric Fluid-cooled airfoil
US3435654A (en) * 1962-12-24 1969-04-01 Hermann Papst Boundary layer control
US3220697A (en) * 1963-08-30 1965-11-30 Gen Electric Hollow turbine or compressor vane
US3346235A (en) * 1963-12-23 1967-10-10 Papst Hermann Boundary layer control
GB1034260A (en) * 1964-12-02 1966-06-29 Rolls Royce Aerofoil-shaped blade for use in a fluid flow machine
US3301527A (en) * 1965-05-03 1967-01-31 Gen Electric Turbine diaphragm structure
US3528751A (en) * 1966-02-26 1970-09-15 Gen Electric Cooled vane structure for high temperature turbine
US3540810A (en) * 1966-03-17 1970-11-17 Gen Electric Slanted partition for hollow airfoil vane insert
DE2065334C3 (en) * 1969-12-01 1982-11-25 General Electric Co., Schenectady, N.Y. Cooling system for the inner and outer massive platforms of a hollow guide vane
US3807891A (en) * 1972-09-15 1974-04-30 United Aircraft Corp Thermal response turbine shroud
US3864058A (en) * 1973-02-05 1975-02-04 Garrett Corp Cooled aerodynamic device
US4025226A (en) * 1975-10-03 1977-05-24 United Technologies Corporation Air cooled turbine vane
US4126405A (en) * 1976-12-16 1978-11-21 General Electric Company Turbine nozzle
US4288201A (en) * 1979-09-14 1981-09-08 United Technologies Corporation Vane cooling structure
FR2485632B1 (en) * 1980-06-30 1985-07-05 Snecma IMPROVEMENT IN VENTILATION SYSTEMS OF BLADES AND TURBINE DISCS
GB2115883B (en) * 1982-02-26 1986-04-30 Gen Electric Turbomachine airfoil mounting assembly
US4639189A (en) * 1984-02-27 1987-01-27 Rockwell International Corporation Hollow, thermally-conditioned, turbine stator nozzle
US4650394A (en) * 1984-11-13 1987-03-17 United Technologies Corporation Coolable seal assembly for a gas turbine engine
US4642024A (en) * 1984-12-05 1987-02-10 United Technologies Corporation Coolable stator assembly for a rotary machine
US4650395A (en) * 1984-12-21 1987-03-17 United Technologies Corporation Coolable seal segment for a rotary machine
US4668164A (en) * 1984-12-21 1987-05-26 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US4767260A (en) * 1986-11-07 1988-08-30 United Technologies Corporation Stator vane platform cooling means
US4902198A (en) * 1988-08-31 1990-02-20 Westinghouse Electric Corp. Apparatus for film cooling of turbine van shrouds
FR2659689B1 (en) * 1990-03-14 1992-06-05 Snecma INTERNAL COOLING CIRCUIT OF A TURBINE STEERING BLADE.
US5494402A (en) * 1994-05-16 1996-02-27 Solar Turbines Incorporated Low thermal stress ceramic turbine nozzle
US5516260A (en) * 1994-10-07 1996-05-14 General Electric Company Bonded turbine airfuel with floating wall cooling insert
US5813827A (en) * 1997-04-15 1998-09-29 Westinghouse Electric Corporation Apparatus for cooling a gas turbine airfoil
EP1191189A1 (en) * 2000-09-26 2002-03-27 Siemens Aktiengesellschaft Gas turbine blades
US6543993B2 (en) * 2000-12-28 2003-04-08 General Electric Company Apparatus and methods for localized cooling of gas turbine nozzle walls
GB2386926A (en) * 2002-03-27 2003-10-01 Alstom Two part impingement tube for a turbine blade or vane
GB2398106B (en) * 2003-01-13 2005-03-16 Rolls Royce Plc Gas turbine cooling system
EP1589192A1 (en) * 2004-04-20 2005-10-26 Siemens Aktiengesellschaft Turbine blade with an insert for impingement cooling
US7104756B2 (en) * 2004-08-11 2006-09-12 United Technologies Corporation Temperature tolerant vane assembly
US7303372B2 (en) * 2005-11-18 2007-12-04 General Electric Company Methods and apparatus for cooling combustion turbine engine components
GB2446149B (en) * 2007-01-31 2009-03-18 Siemens Ag A gas turbine
US11603766B1 (en) * 2022-05-04 2023-03-14 Pratt & Whitney Canada Corp. Turbine stator vanes having inserts and splitter plates

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA491903A (en) * 1953-04-07 Rolls-Royce Limited Hollow blading for compressors and turbines
FR897709A (en) * 1942-06-09 1945-03-29 Process for cooling gas turbine blades
US2447095A (en) * 1944-12-30 1948-08-17 Cons Vultee Aircraft Corp Airplane anti-icing system
US2533078A (en) * 1945-02-22 1950-12-05 Rca Corp Antenna system
US2556736A (en) * 1945-06-22 1951-06-12 Curtiss Wright Corp Deicing system for aircraft
GB602530A (en) * 1945-10-16 1948-05-28 Bristol Aeroplane Co Ltd Improvements in or relating to gas turbines
US2514105A (en) * 1945-12-07 1950-07-04 Thomas Wilfred Airfoil conditioning means
US2779565A (en) * 1948-01-05 1957-01-29 Bruno W Bruckmann Air cooling of turbine blades
US2647368A (en) * 1949-05-09 1953-08-04 Hermann Oestrich Method and apparatus for internally cooling gas turbine blades with air, fuel, and water
US2648520A (en) * 1949-08-02 1953-08-11 Heinz E Schmitt Air-cooled turbine blade
US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade
FR1007303A (en) * 1949-08-24 1952-05-05 Improvements to rotor blades
BE498667A (en) * 1949-08-27

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1092255B (en) * 1957-05-28 1960-11-03 Snecma Method for cooling machine parts, in particular hollow gas turbine blades
DE1300349B (en) * 1964-07-06 1969-07-31 Rolls Royce Deicing device for a gas turbine jet engine

Also Published As

Publication number Publication date
CH322022A (en) 1957-05-31
US2847185A (en) 1958-08-12
FR1097531A (en) 1955-07-06

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