GB737472A - Turbines and like machines having adjustable guide blades - Google Patents
Turbines and like machines having adjustable guide bladesInfo
- Publication number
- GB737472A GB737472A GB2489452A GB2489452A GB737472A GB 737472 A GB737472 A GB 737472A GB 2489452 A GB2489452 A GB 2489452A GB 2489452 A GB2489452 A GB 2489452A GB 737472 A GB737472 A GB 737472A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blades
- adjusting member
- ring
- annular
- radial
- 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
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
737,472. Turbines ;axial-flow compressors. NAPIER & SON, Ltd., D. Sept. 28, 1953 [Oct. 3, 1952], No. 24894/52. Classes 110 (1) and 110 (3). In a turbine or compressor having a ring of guide blades adjustable about radial axes and lever arms each attached by one end to one of the adjustable blades, the other ends of the arms being connected to a common annular adjusting member so as to permit relative radial movement between the levers and the adjusting member, the adjusting movement of which is in the axial direction, the dimensions of the adjusting member are such that it is substantially more rigid in the axial than in the radial direction and is actuated by several similar servomotors disposed at intervals around it. The hot gases from an annular combustion chamber or several individual combustion chambers 11 pass through a ring of adjustable guide blades 12 to the turbine rotor blades 13. The combustion chambers 11 have a sliding fit in an annular member 16. The blades 12 are supported at their inner ends in the flange 19 of the annular member 16 by pivot spigots 24 and at their outer ends by pivot spigots 25 which turn in bearings 26 carried by the outer casing 27. Each of the spigots 24 has a lever arm 28 secured to its innermost end. The lever arms 28 which lie approximately in the circumferential direction when the blades 12 are set in the central position carry pins 30 which engage circumferential slots in an annular adjusting member 31 so that relative movement between the pins 30 and 31 is permitted in the radial and circumferential directions, but not in the axial direction. The adjusting member 31 comprises a hoop whose width a is substantially greater than its radial thickness b. Projections 32 on its rear edge are connected to the pistons 33 of servomotors 34 controlled by fluid supplied through pipes 35, 36 by a control valve. To avoid all of the axial thrust on the blades 12 being taken through the outer ends of the blades, compressed air from the compressor is led through the shaft 15 and ports 22, 23 to the rear of the annular member 16. The ring of blades 12 may include some fixed blades as described in Specification 737,473. The adjusting member 31 may be arranged outside the ring of guide blades instead of, as shown, inside this ring.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA561070A CA561070A (en) | 1952-10-03 | Turbo machines having adjustable guide blades | |
GB2489452A GB737472A (en) | 1952-10-03 | 1952-10-03 | Turbines and like machines having adjustable guide blades |
FR1084493D FR1084493A (en) | 1952-10-03 | 1953-09-30 | Turbo-machine with adjustable guide vanes |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2489452A GB737472A (en) | 1952-10-03 | 1952-10-03 | Turbines and like machines having adjustable guide blades |
Publications (1)
Publication Number | Publication Date |
---|---|
GB737472A true GB737472A (en) | 1955-09-28 |
Family
ID=10218932
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2489452A Expired GB737472A (en) | 1952-10-03 | 1952-10-03 | Turbines and like machines having adjustable guide blades |
Country Status (3)
Country | Link |
---|---|
CA (1) | CA561070A (en) |
FR (1) | FR1084493A (en) |
GB (1) | GB737472A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2854211A (en) * | 1955-11-25 | 1958-09-30 | Gen Electric | Adjustable vane arrangement for fluid flow machinery |
US3095010A (en) * | 1959-04-30 | 1963-06-25 | Rolls Royce | Gas turbine engine having adjustable guide vanes |
EP0169779A1 (en) * | 1984-07-26 | 1986-01-29 | Alsthom | Assembly for controlling the extraction pressure of a condensation turbine |
GB2259956A (en) * | 1991-09-25 | 1993-03-31 | Snecma | Turbomachine with variably settable stator blades |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE556572A (en) * | 1955-08-16 | |||
US3038697A (en) * | 1960-07-05 | 1962-06-12 | Chrysler Corp | Gas turbine adjustable nozzle and interstage inner shroud suspension |
GB1119439A (en) * | 1966-06-03 | 1968-07-10 | Rover Co Ltd | Adjustable nozzle guide vane assembly for an axial flow turbine |
US3630633A (en) * | 1970-05-07 | 1971-12-28 | Ford Motor Co | Gas turbine engine nozzle actuation system |
-
0
- CA CA561070A patent/CA561070A/en not_active Expired
-
1952
- 1952-10-03 GB GB2489452A patent/GB737472A/en not_active Expired
-
1953
- 1953-09-30 FR FR1084493D patent/FR1084493A/en not_active Expired
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2854211A (en) * | 1955-11-25 | 1958-09-30 | Gen Electric | Adjustable vane arrangement for fluid flow machinery |
US3095010A (en) * | 1959-04-30 | 1963-06-25 | Rolls Royce | Gas turbine engine having adjustable guide vanes |
EP0169779A1 (en) * | 1984-07-26 | 1986-01-29 | Alsthom | Assembly for controlling the extraction pressure of a condensation turbine |
GB2259956A (en) * | 1991-09-25 | 1993-03-31 | Snecma | Turbomachine with variably settable stator blades |
GB2259956B (en) * | 1991-09-25 | 1994-07-27 | Snecma | Turbomachine with variably settable stator blades |
Also Published As
Publication number | Publication date |
---|---|
FR1084493A (en) | 1955-01-19 |
CA561070A (en) | 1958-07-29 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US11448235B2 (en) | Axi-centrifugal compressor with variable outlet guide vanes | |
US3861822A (en) | Duct with vanes having selectively variable pitch | |
US2488875A (en) | Gas turbine engine | |
US3031132A (en) | Gas-turbine engine with air tapping means | |
GB1345892A (en) | Gas turbine engines | |
US3869221A (en) | Rotor wheel fan blade adjusting apparatus for turbojet engines and the like | |
US3898799A (en) | Device for bleeding-off compressor air in turbine jet engine | |
GB1368353A (en) | Actuation ring for variable geometry axial flow compressors | |
GB1178650A (en) | Improvements in Variable Geometry Axial Flow Compressors | |
US4780049A (en) | Compressor | |
GB737472A (en) | Turbines and like machines having adjustable guide blades | |
GB1266254A (en) | ||
GB907323A (en) | Improvements in or relating to axial flow compressors | |
US2955744A (en) | Compressor | |
GB803137A (en) | Improvements in or relating to axial-flow fluid machines for example turbines and compressors of gas-turbine engines | |
GB737473A (en) | Turbines and like machines having adjustable guide blades | |
GB1216920A (en) | Axial flow compressors having adjustable stator vanes | |
US3030006A (en) | Circumferential bleed valve | |
GB2024336A (en) | Gas turbine rotor tip clearance control apparatus | |
US2972441A (en) | Variable blade system | |
GB913147A (en) | Air compressors | |
US2932440A (en) | Compressor blade adjustment means | |
GB802165A (en) | Improvements in or relating to turbines | |
GB911160A (en) | Improvements in or relating to engines having gas compressors | |
GB736796A (en) | Improvements in or relating to axial-flow fluid machines such as axial-flow compressors and turbines |