GB949231A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB949231A
GB949231A GB1609061A GB1609061A GB949231A GB 949231 A GB949231 A GB 949231A GB 1609061 A GB1609061 A GB 1609061A GB 1609061 A GB1609061 A GB 1609061A GB 949231 A GB949231 A GB 949231A
Authority
GB
United Kingdom
Prior art keywords
bonded
vanes
gas turbine
members
annular
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
GB1609061A
Inventor
Norman Robert Robinson
John Michael Storer Keen
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 GB1609061A priority Critical patent/GB949231A/en
Publication of GB949231A publication Critical patent/GB949231A/en
Priority claimed from GB26021/66A external-priority patent/GB1096257A/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
    • 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

Abstract

949,231. Compressor blades; gas turbine plant; axial flow compressors. ROLLS-ROYCE Ltd. April 27, 1962 [May 3, 1961], No. 16090/61. Headings F1C, F1G and FIT. A gas turbine engine has a compressor provided with a ring of angularly spaced apart inlet guide vanes, the radially inner and/or the radially outer ends of the vanes having their upstream and downstream sides mounted in angularly spaced apart slots in a pair of axially spaced slotted annular members. The radially outer ends 23 of the inlet guide vanes 14 of a gas turbine engine are bonded in slots 24, 25 of annular members 26, 27 which are bonded to the casing member 21, the latter having apertures through which the vanes 14 pass. The member 27 is bonded and connected by locating peg 30 to member 31 which is then bonded to casing member 22. Members 26, 27, 31 are bonded to an outer casing member 32. The radially inner ends 33 of the vanes 14 are bonded within slots 34, 35 of annular members 36, 37, member 36 consituting the end wall of a U-section ring 40 having radially outer and inner walls 41, 42. Roots 33 pass through apertures in the wall 41. An inner hub member 44 is bonded to ring 40 and bearing housing 45 is bonded to member 44. Outer race 47 of thrust bearing 46 is splined within housing 45 and retained in position by spring 50. An annular sealing plate 51 carries a labyrinth seal 52. The guide vanes, annular and casing members are formed of reinforced synthetic resin material such as epoxy or phenolic resin reinforced with glass fibres.
GB1609061A 1961-05-03 1961-05-03 Gas turbine engine Expired GB949231A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1609061A GB949231A (en) 1961-05-03 1961-05-03 Gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1609061A GB949231A (en) 1961-05-03 1961-05-03 Gas turbine engine
GB26021/66A GB1096257A (en) 1966-06-10 1966-06-10 Gas turbine engine

Publications (1)

Publication Number Publication Date
GB949231A true GB949231A (en) 1964-02-12

Family

ID=26251788

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1609061A Expired GB949231A (en) 1961-05-03 1961-05-03 Gas turbine engine

Country Status (1)

Country Link
GB (1) GB949231A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1551201B1 (en) * 1965-09-16 1970-11-19 Rolls Royce Method for fastening a ring of guide vanes in the housing of axial flow machines
DE2819808C1 (en) * 1977-05-05 1989-01-19 Rolls Royce Guide vane ring for the turbine of a gas turbine engine
GB2262574A (en) * 1991-12-18 1993-06-23 Snecma A structural arm for the casing of a turbomachine.
GB2455785A (en) * 2007-12-21 2009-06-24 Rolls Royce Plc An annular non-metallic component comprising a bore with a sleeve
GB2452297B (en) * 2007-08-30 2010-01-06 Rolls Royce Plc A compressor

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1551201B1 (en) * 1965-09-16 1970-11-19 Rolls Royce Method for fastening a ring of guide vanes in the housing of axial flow machines
DE2819808C1 (en) * 1977-05-05 1989-01-19 Rolls Royce Guide vane ring for the turbine of a gas turbine engine
GB2262574A (en) * 1991-12-18 1993-06-23 Snecma A structural arm for the casing of a turbomachine.
GB2262574B (en) * 1991-12-18 1994-10-05 Snecma A structural arm for the casing of a turbomachine
GB2452297B (en) * 2007-08-30 2010-01-06 Rolls Royce Plc A compressor
GB2455785A (en) * 2007-12-21 2009-06-24 Rolls Royce Plc An annular non-metallic component comprising a bore with a sleeve
GB2455785B (en) * 2007-12-21 2009-11-11 Rolls Royce Plc Annular component

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