GB622078A - Improvements relating to gas turbine engines - Google Patents
Improvements relating to gas turbine enginesInfo
- Publication number
- GB622078A GB622078A GB681847A GB681847A GB622078A GB 622078 A GB622078 A GB 622078A GB 681847 A GB681847 A GB 681847A GB 681847 A GB681847 A GB 681847A GB 622078 A GB622078 A GB 622078A
- Authority
- GB
- United Kingdom
- Prior art keywords
- platforms
- recesses
- gas turbine
- turbine engines
- improvements relating
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
622,078. Gas turbines. RUBBRA, A. A. March 11, 1947, No. 6818. [Class 110(iii)] The stator and nozzle blades 16 of a gas turbine are cast in pairs or groups with integral inner and outer segmental platforms 17, 18. The platforms are received in annular recesses 12, 14 in supporting rings 10, 11. They are located circumferentially by cross ribs in the supporting rings between the platforms, or, by projections on the platforms which engage recesses in the floors of the recesses 12, 14. There is a radial clearance between the platforms and the floors of the recesses and the blades are located radially by stepped flanges 19 on the inner platforms 17 which are held between the ring 10 and a casing part 24.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB681847A GB622078A (en) | 1947-03-11 | 1947-03-11 | Improvements relating to gas turbine engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB681847A GB622078A (en) | 1947-03-11 | 1947-03-11 | Improvements relating to gas turbine engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB622078A true GB622078A (en) | 1949-04-26 |
Family
ID=9821313
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB681847A Expired GB622078A (en) | 1947-03-11 | 1947-03-11 | Improvements relating to gas turbine engines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB622078A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2962260A (en) * | 1954-12-13 | 1960-11-29 | United Aircraft Corp | Sweep back in blading |
-
1947
- 1947-03-11 GB GB681847A patent/GB622078A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2962260A (en) * | 1954-12-13 | 1960-11-29 | United Aircraft Corp | Sweep back in blading |
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