GB1009619A - Improvements relating to compressors and turbines - Google Patents
Improvements relating to compressors and turbinesInfo
- Publication number
- GB1009619A GB1009619A GB4210463A GB4210463A GB1009619A GB 1009619 A GB1009619 A GB 1009619A GB 4210463 A GB4210463 A GB 4210463A GB 4210463 A GB4210463 A GB 4210463A GB 1009619 A GB1009619 A GB 1009619A
- Authority
- GB
- United Kingdom
- Prior art keywords
- slot
- platform
- blades
- compressor
- blade
- 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
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1,009,619. Stator blade fixing. ROLLSROYCE Ltd. Aug. 11, 1964 [Oct. 24, 1963], No. 42104/63. Heading F1T. A compressor or turbine has a row of stator blades each of which has a platform mounted in a slot in the outer casing of the machine, and a flexible tube whose interior is supplied with fluid pressure for urging each stator blade towards a fixed position in its slot, the tube contacting the platform(s) of one or more blades. A turbine or compressor stator blade 16, Fig. 4, has a tapered platform 23 mounted in a corresponding circumferential slot 21 in a gas turbine engine outer casing. An annular seamless flexible metal tube 25 is supplied with pressurised air from the engine compressor, or an external source, to urge blade 16 radially inwardly tightly against slot walls 24. The engine casing is in two halves 15a, 15b, Fig. 3, and the ends of flexible tube 25 are clamped between adjacent flanges 30, 31 at one of the joints. A radially extending plate 32 is also clamped at the joint to prevent circumferential movement of blades 16 within slot 21. In a modification, Fig. 2 (not shown), each blade platform has an axially extending flange. In a further modification, Fig. 5 (not shown), the flexible tube 25 is formed of two metal strips welded together.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4210463A GB1009619A (en) | 1963-10-24 | 1963-10-24 | Improvements relating to compressors and turbines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4210463A GB1009619A (en) | 1963-10-24 | 1963-10-24 | Improvements relating to compressors and turbines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1009619A true GB1009619A (en) | 1965-11-10 |
Family
ID=10422866
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB4210463A Expired GB1009619A (en) | 1963-10-24 | 1963-10-24 | Improvements relating to compressors and turbines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1009619A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4621976A (en) * | 1985-04-23 | 1986-11-11 | United Technologies Corporation | Integrally cast vane and shroud stator with damper |
EP0331837A1 (en) * | 1988-01-11 | 1989-09-13 | General Electric Company | Method and device for mounting guide vanes in turbines |
FR2859509A1 (en) * | 2003-09-10 | 2005-03-11 | Snecma Moteurs | Rectifier vanes rotation stopping device for turbo-machine, has bar with pair of ends inserted in groove of housing, where each end has axial surface contacting axial surface of respective housing |
EP2943658B1 (en) | 2013-01-08 | 2017-03-29 | United Technologies Corporation | Stator anti-rotation device |
-
1963
- 1963-10-24 GB GB4210463A patent/GB1009619A/en not_active Expired
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4621976A (en) * | 1985-04-23 | 1986-11-11 | United Technologies Corporation | Integrally cast vane and shroud stator with damper |
EP0331837A1 (en) * | 1988-01-11 | 1989-09-13 | General Electric Company | Method and device for mounting guide vanes in turbines |
FR2859509A1 (en) * | 2003-09-10 | 2005-03-11 | Snecma Moteurs | Rectifier vanes rotation stopping device for turbo-machine, has bar with pair of ends inserted in groove of housing, where each end has axial surface contacting axial surface of respective housing |
EP1515002A1 (en) * | 2003-09-10 | 2005-03-16 | Snecma Moteurs | Anti-rotation means for turbine stator vanes in the split plane of the casing |
US7059832B2 (en) | 2003-09-10 | 2006-06-13 | Snecma Moteurs | Rotation-locking of sectors of rectifier blades by bars in the parting planes of the housing |
EP2943658B1 (en) | 2013-01-08 | 2017-03-29 | United Technologies Corporation | Stator anti-rotation device |
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