GB1268301A – Improvements in or relating to gas turbine engines
– Google Patents
GB1268301A – Improvements in or relating to gas turbine engines
– Google Patents
Improvements in or relating to gas turbine engines
Info
Publication number
GB1268301A
GB1268301A
GB156470A
GB156470A
GB1268301A
GB 1268301 A
GB1268301 A
GB 1268301A
GB 156470 A
GB156470 A
GB 156470A
GB 156470 A
GB156470 A
GB 156470A
GB 1268301 A
GB1268301 A
GB 1268301A
Authority
GB
United Kingdom
Prior art keywords
openings
support ring
seal
rotor
chamber
Prior art date
1970-01-13
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
GB156470A
Inventor
James Alexander Petrie
Willie Williamson
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.)
1970-01-13
Filing date
1970-01-13
Publication date
1972-03-29
1970-01-13
Application filed by Rolls Royce PLC
filed
Critical
Rolls Royce PLC
1970-01-13
Priority to GB156470A
priority
Critical
patent/GB1268301A/en
1972-03-29
Publication of GB1268301A
publication
Critical
patent/GB1268301A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
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
F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F01D25/08—Cooling; Heating; Heat-insulation
F01D25/12—Cooling
Abstract
1,268,301. Gas turbine engines; cooling. ROLLS-ROYCE Ltd. Jan. 13, 1970, No.1564/70. Heading F1G. A gas turbine engine comprises stator structure and a bladed rotor, sealing means being disposed therebetween, the stator structure defining at least two flow paths for the passage of cooling fluid, one of the flow paths being arranged to supply cooling fluid to the bladed rotor. The engine shown comprises inlet guide vanes 10 supported at their inner ends by support ring 12 having flanges 16, 18 and at their outer ends by support ring 14, the inner support ring 12 being connected to a structural member 30. The guide vanes provide two flow paths 36, 38 for flow of cooling air, air flowing through the path 36 discharging through openings formed at the leading edges of the guide vanes. The engine comprises also a rotor 48 having blades 50 which carry shrouding 52. The rotor is formed with a seal element 54 which co-operates with a seal element 22 on the flange 18 of the support ring 12. The rotor also carries seal elements 56, 58 which co-operate with seal elements 32, 24 carried by the structural member 30 and the support ring 12 respectively. Openings 28 are formed in the support ring 12 and are provided with swirl vanes 26. Hollow spokes 34 are disposed between the openings 28. Cooling air is supplied through the openings 28 and swirl vanes 26 into the chamber 60 on to the rotor 48, this constituting one flow path, the air passing through the seal 24, 58 into a chamber 62, also through the seal 54, 22, through openings 64 into the second flow path. Cooling air is also supplied through the seal 32, 56 into the chamber 62, the air then flowing through the hollow spokes 34 and through the passages 38 in the guide vanes 10 into the chamber 42. The air then flows through openings 44 to chamber 46, through swirl vanes 40 on to the shroud elements 52. This constitutes the second flow path.
GB156470A
1970-01-13
1970-01-13
Improvements in or relating to gas turbine engines
Expired
GB1268301A
(en)
Priority Applications (1)
Application Number
Priority Date
Filing Date
Title
GB156470A
GB1268301A
(en)
1970-01-13
1970-01-13
Improvements in or relating to gas turbine engines
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
GB156470A
GB1268301A
(en)
1970-01-13
1970-01-13
Improvements in or relating to gas turbine engines
Publications (1)
Publication Number
Publication Date
GB1268301A
true
GB1268301A
(en)
1972-03-29
Family
ID=9724164
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB156470A
Expired
GB1268301A
(en)
1970-01-13
1970-01-13
Improvements in or relating to gas turbine engines
Country Status (1)
Country
Link
GB
(1)
GB1268301A
(en)
Cited By (8)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
JPS5225917A
(en)
*
1975-08-22
1977-02-26
Hitachi Ltd
Seal fin device of turbine wheel and diaphragm
GB2189845A
(en)
*
1986-04-30
1987-11-04
Gen Electric
Gas turbine cooling air transferring apparatus
GB2233401A
(en)
*
1989-06-21
1991-01-09
Rolls Royce Plc
Improvements in or relating to gas turbine engines
US5320485A
(en)
*
1992-06-11
1994-06-14
Societe Nationale D’etude Et De Construction De Moteurs D’aviation (S.N.E.C.M.A.)
Guide vane with a plurality of cooling circuits
US6837676B2
(en)
*
2002-09-11
2005-01-04
Mitsubishi Heavy Industries, Ltd.
Gas turbine
GB2426289A
(en)
*
2005-04-01
2006-11-22
Rolls Royce Plc
Gas turbine engine cooling system
US7874799B2
(en)
2006-10-14
2011-01-25
Rolls-Royce Plc
Flow cavity arrangement
WO2015023342A2
(en)
2013-06-04
2015-02-19
United Technologies Corporation
Gas turbine engine with dove-tailed tobi vane
1970
1970-01-13
GB
GB156470A
patent/GB1268301A/en
not_active
Expired
Cited By (14)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
JPS5225917A
(en)
*
1975-08-22
1977-02-26
Hitachi Ltd
Seal fin device of turbine wheel and diaphragm
GB2189845A
(en)
*
1986-04-30
1987-11-04
Gen Electric
Gas turbine cooling air transferring apparatus
GB2189845B
(en)
*
1986-04-30
1991-01-23
Gen Electric
Turbine cooling air transferring apparatus
GB2233401A
(en)
*
1989-06-21
1991-01-09
Rolls Royce Plc
Improvements in or relating to gas turbine engines
US5320485A
(en)
*
1992-06-11
1994-06-14
Societe Nationale D’etude Et De Construction De Moteurs D’aviation (S.N.E.C.M.A.)
Guide vane with a plurality of cooling circuits
US6837676B2
(en)
*
2002-09-11
2005-01-04
Mitsubishi Heavy Industries, Ltd.
Gas turbine
GB2426289A
(en)
*
2005-04-01
2006-11-22
Rolls Royce Plc
Gas turbine engine cooling system
GB2426289B
(en)
*
2005-04-01
2007-07-04
Rolls Royce Plc
Cooling system for a gas turbine engine
US7625171B2
(en)
2005-04-01
2009-12-01
Rolls-Royce Plc
Cooling system for a gas turbine engine
US7874799B2
(en)
2006-10-14
2011-01-25
Rolls-Royce Plc
Flow cavity arrangement
WO2015023342A2
(en)
2013-06-04
2015-02-19
United Technologies Corporation
Gas turbine engine with dove-tailed tobi vane
EP3004568A4
(en)
*
2013-06-04
2017-03-08
United Technologies Corporation
Gas turbine engine with dove-tailed tobi vane
US10494938B2
(en)
2013-06-04
2019-12-03
United Technologies Corporation
Gas turbine engine with dove-tailed TOBI vane
US11092025B2
(en)
2013-06-04
2021-08-17
Raytheon Technologies Corporation
Gas turbine engine with dove-tailed TOBI vane
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None