GB1072538A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB1072538A
GB1072538A GB5475865A GB5475865A GB1072538A GB 1072538 A GB1072538 A GB 1072538A GB 5475865 A GB5475865 A GB 5475865A GB 5475865 A GB5475865 A GB 5475865A GB 1072538 A GB1072538 A GB 1072538A
Authority
GB
United Kingdom
Prior art keywords
low pressure
turbines
turbine
slots
pressure compressor
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
GB5475865A
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
Priority to GB5475865A priority Critical patent/GB1072538A/en
Publication of GB1072538A publication Critical patent/GB1072538A/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections

Landscapes

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

Abstract

1,072,538. Gas turbine engines; turbines. ROLLS-ROYCE Ltd. Dec. 23, 1965, No. 54758/65. Headings F1G and F1T. A gas turbine engine has an annular flow duct (11) in which are mounted in flow series a low pressure compressor (12), a high pressure compressor (13), combustion equipment (14), a high pressure turbine (16) which drives the high pressure compressor (13), and a low pressure turbine (21) which drives the low pressure compressor (12), the annular flow duct (11) having a portion rotatable about the longitudinal axis of the annular flow duct, this portion being disposed between the high and low pressure turbines (16, 21) and carried by and driven by one of the turbines. By reason of the fact that the rotatable portion is driven by one of the turbines, it is not necessary to provide sealing between this portion and the turbine. When the low pressure turbine (21) is used for this purpose, the rotatable portion comprises a plurality of segments (27) which are mounted in slots in a disc (23) secured to the upstream side of the low pressure turbine (21). The segments (27) are disposed radially inwardly of a ring of angularly spaced apart nozzle guide vanes (20), each of which is pivotally mounted and adjustable. Each nozzle guide vane (20) has a hollow interior which is supplied with cooling air, the trailing edge (46) of each vane being provided with slots (45) out through which the air passes. The slots (45) are so disposed that streams of air passing through them flow over the trailing edge (46) so as to impinge on the adjacent streams and have a scrubbing effect on the trailing edge, whereby the latter is cooled.
GB5475865A 1965-12-23 1965-12-23 Gas turbine engine Expired GB1072538A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB5475865A GB1072538A (en) 1965-12-23 1965-12-23 Gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5475865A GB1072538A (en) 1965-12-23 1965-12-23 Gas turbine engine

Publications (1)

Publication Number Publication Date
GB1072538A true GB1072538A (en) 1967-06-21

Family

ID=10471989

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5475865A Expired GB1072538A (en) 1965-12-23 1965-12-23 Gas turbine engine

Country Status (1)

Country Link
GB (1) GB1072538A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2210935A (en) * 1987-10-10 1989-06-21 Rolls Royce Plc Variable stator vane assembly

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2210935A (en) * 1987-10-10 1989-06-21 Rolls Royce Plc Variable stator vane assembly
US4861228A (en) * 1987-10-10 1989-08-29 Rolls-Royce Plc Variable stator vane assembly
GB2210935B (en) * 1987-10-10 1992-05-27 Rolls Royce Plc Variable stator vane assembly

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