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GB1119774A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB1119774A
GB1119774A GB5475965A GB5475965A GB1119774A GB 1119774 A GB1119774 A GB 1119774A GB 5475965 A GB5475965 A GB 5475965A GB 5475965 A GB5475965 A GB 5475965A GB 1119774 A GB1119774 A GB 1119774A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
turbine engine
vanes
low pressure
cooling air
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
GB5475965A
Inventor
John Gregory Keenan
Jack Palfreyman
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
Publication of GB1119774A publication Critical patent/GB1119774A/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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,119,774. Gas turbine engines. ROLLSROYCE Ltd. Dec. 23, 1965, No. 54759/65. Heading F1T. In a gas turbine engine the interior of each nozzle guide vane 20 between high and low pressure turbines driving high and low pressure compressors, is supplied with cooling air through an inlet 42, a tube 41 and ports 43. The cooling air is directed through the latter towards the leading edge of the vane and thereafter passes through slots 45 and over the trailing edge 46. The vanes 20 are adjustable by a motor-driven pinion 36 which rotates an actuator ring 35 meshing with spur gears 34 connected to the vanes.
GB5475965A 1967-07-06 1965-12-23 Gas turbine engine Expired GB1119774A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3125567A GB1127719A (en) 1967-07-06 1967-07-06 Gas turbine engine

Publications (1)

Publication Number Publication Date
GB1119774A true GB1119774A (en) 1968-07-10

Family

ID=10320363

Family Applications (2)

Application Number Title Priority Date Filing Date
GB5475965A Expired GB1119774A (en) 1967-07-06 1965-12-23 Gas turbine engine
GB3125567A Expired GB1127719A (en) 1967-07-06 1967-07-06 Gas turbine engine

Family Applications After (1)

Application Number Title Priority Date Filing Date
GB3125567A Expired GB1127719A (en) 1967-07-06 1967-07-06 Gas turbine engine

Country Status (2)

Country Link
FR (1) FR1579652A (en)
GB (2) GB1119774A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3966352A (en) * 1975-06-30 1976-06-29 United Technologies Corporation Variable area turbine
DE2915626A1 (en) * 1978-04-20 1979-10-31 Gen Electric COOLING AIR LINE FOR A GAS TURBINE ENGINE
US4378960A (en) * 1980-05-13 1983-04-05 Teledyne Industries, Inc. Variable geometry turbine inlet nozzle
EP0386200A4 (en) * 1988-08-17 1991-03-13 Sundstrand Corporation Guide vane assembly for auxiliary power unit
EP1256697A3 (en) * 2001-05-11 2004-03-10 AVIO S.p.A. Stator vane of a variable-geometry turbine
US7147431B2 (en) * 2002-11-27 2006-12-12 Rolls-Royce Plc Cooled turbine assembly

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4214852A (en) * 1978-04-20 1980-07-29 General Electric Company Variable turbine vane assembly

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3966352A (en) * 1975-06-30 1976-06-29 United Technologies Corporation Variable area turbine
DE2915626A1 (en) * 1978-04-20 1979-10-31 Gen Electric COOLING AIR LINE FOR A GAS TURBINE ENGINE
FR2423638A1 (en) * 1978-04-20 1979-11-16 Gen Electric COOLING AIR MANIFOLD FOR GAS TURBINE ENGINES
US4214851A (en) * 1978-04-20 1980-07-29 General Electric Company Structural cooling air manifold for a gas turbine engine
US4378960A (en) * 1980-05-13 1983-04-05 Teledyne Industries, Inc. Variable geometry turbine inlet nozzle
EP0386200A4 (en) * 1988-08-17 1991-03-13 Sundstrand Corporation Guide vane assembly for auxiliary power unit
EP1256697A3 (en) * 2001-05-11 2004-03-10 AVIO S.p.A. Stator vane of a variable-geometry turbine
US7147431B2 (en) * 2002-11-27 2006-12-12 Rolls-Royce Plc Cooled turbine assembly

Also Published As

Publication number Publication date
FR1579652A (en) 1969-08-29
GB1127719A (en) 1968-09-18

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