GB1064089A – Improvements in and relating to gas turbines
– Google Patents
GB1064089A – Improvements in and relating to gas turbines
– Google Patents
Improvements in and relating to gas turbines
Info
Publication number
GB1064089A
GB1064089A
GB48028/65A
GB4802865A
GB1064089A
GB 1064089 A
GB1064089 A
GB 1064089A
GB 48028/65 A
GB48028/65 A
GB 48028/65A
GB 4802865 A
GB4802865 A
GB 4802865A
GB 1064089 A
GB1064089 A
GB 1064089A
Authority
GB
United Kingdom
Prior art keywords
blades
rotor
gases
stator
direct
Prior art date
1964-11-30
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
GB48028/65A
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.)
Canadian Patents and Development Ltd
Original Assignee
Canadian Patents and Development Ltd
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.)
1964-11-30
Filing date
1965-11-12
Publication date
1967-04-05
1965-11-12
Application filed by Canadian Patents and Development Ltd
filed
Critical
Canadian Patents and Development Ltd
1967-04-05
Publication of GB1064089A
publication
Critical
patent/GB1064089A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
239000007789
gas
Substances
0.000
abstract
7
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
Abstract
1,064,089. Gas turbines. CANADIAN PATENTS & DEVELOPMENT Ltd. Nov. 12, 1965 [Nov.30, 1964], No.48028/65. Heading F1T. A gas turbine comprises a rotor having a series of blades mounted thereon and a stator assembly comprising a series of blades for directing gases on to the rotor blades thereby causing the rotor to rotate in a first direction, there being means for angularly moving the stator blades so that the concave surfaces direct the gases with a circumferential component of velocity in the opposite direction on to the convex surfaces of the rotor blades whereby the rotor is urged in said opposite direction. The stator blades 10 shown in Fig. 1 are indicated in their normal position in which they direct gases on to the concave surfaces of the rotor blades 13 whereby the rotor 14 is caused to rotate in the forward direction indicated by arrow B. The stator blades are mounted on pivots 15 for angular movement from the position shown in Fig. 1 to that of Fig. 2 (not shown) in which the trailing edges 12 now become the leading edges and the blades direct the gases with a circumferential component in the opposite direction on to the convex surfaces 16 of the rotor blades 13 whereby a braking action is produced on the rotation of the rotor. The invention is suitable for application to gas turbine engines of road vehicles. The stator blades may be moved by means of a circumferential ring gear which engages with gear segments secured to the blade spindles.
GB48028/65A
1964-11-30
1965-11-12
Improvements in and relating to gas turbines
Expired
GB1064089A
(en)
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
US414651A
US3231239A
(en)
1964-11-30
1964-11-30
Gas turbine
Publications (1)
Publication Number
Publication Date
GB1064089A
true
GB1064089A
(en)
1967-04-05
Family
ID=23642346
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB48028/65A
Expired
GB1064089A
(en)
1964-11-30
1965-11-12
Improvements in and relating to gas turbines
Country Status (2)
Country
Link
US
(1)
US3231239A
(en)
GB
(1)
GB1064089A
(en)
Cited By (3)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2247051A
(en)
*
1990-08-07
1992-02-19
Secr Defence
Aerodynamic-braking
GB2301868A
(en)
*
1995-06-05
1996-12-18
Rolls Royce Plc
Actuator mechanism with emergency drive for variable angle vane arrays
US5630701A
(en)
*
1995-06-05
1997-05-20
Rolls-Royce Plc
Variable angle vane arrays
Families Citing this family (3)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US3728040A
(en)
*
1971-04-22
1973-04-17
J Ioanesian
Turbodrill
US3972644A
(en)
*
1975-01-27
1976-08-03
Caterpillar Tractor Co.
Vane control arrangement for variable area turbine nozzle
US6394766B1
(en)
*
1999-11-01
2002-05-28
James G. Gill
Fan with adjustable guide vanes
Family Cites Families (7)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US2337861A
(en)
*
1941-02-04
1943-12-28
James Russell Kennedy
Propeller
US2689680A
(en)
*
1949-06-16
1954-09-21
Rolls Royce
Means for regulating the characteristics of multistage axialflow compressors
US2805818A
(en)
*
1951-12-13
1957-09-10
Ferri Antonio
Stator for axial flow compressor with supersonic velocity at entrance
BE531926A
(en)
*
1953-10-09
US2819732A
(en)
*
1954-07-14
1958-01-14
Thompson Prod Inc
Variable area turbine entrance nozzle
US2988327A
(en)
*
1956-02-03
1961-06-13
Plessey Co Ltd
Emergency power systems for aircraft auxiliary apparatus
US3044262A
(en)
*
1960-05-09
1962-07-17
Chrysler Corp
Control mechanism for adjustable gas turbine nozzle
1964
1964-11-30
US
US414651A
patent/US3231239A/en
not_active
Expired – Lifetime
1965
1965-11-12
GB
GB48028/65A
patent/GB1064089A/en
not_active
Expired
Cited By (4)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2247051A
(en)
*
1990-08-07
1992-02-19
Secr Defence
Aerodynamic-braking
GB2301868A
(en)
*
1995-06-05
1996-12-18
Rolls Royce Plc
Actuator mechanism with emergency drive for variable angle vane arrays
US5630701A
(en)
*
1995-06-05
1997-05-20
Rolls-Royce Plc
Variable angle vane arrays
GB2301868B
(en)
*
1995-06-05
1999-08-11
Rolls Royce Plc
Improved actuator mechanism for variable angle vane arrays
Also Published As
Publication number
Publication date
US3231239A
(en)
1966-01-25
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