GB526554A - Improvements in and relating to nozzles and nozzle segments for combustion turbines - Google Patents
Improvements in and relating to nozzles and nozzle segments for combustion turbinesInfo
- Publication number
- GB526554A GB526554A GB8823/39A GB882339A GB526554A GB 526554 A GB526554 A GB 526554A GB 8823/39 A GB8823/39 A GB 8823/39A GB 882339 A GB882339 A GB 882339A GB 526554 A GB526554 A GB 526554A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzles
- nozzle
- combustion turbines
- march
- walls
- 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
- F01D9/047—Nozzle boxes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
526,554. Combustion turbines. HOLZWARTH-GASTURBINEN AKT.-GES. March 20,1939, No. 8823. Convention date, March 19, 1938. [Class 110 (iii)] Nozzle segments for combustion turbines are cooled by circulating a coolant from an inlet 8 to an outlet 11, which are connected respectively to lower and upper chambers 9, 10. A nozzle valve admits combustion gases, generated in an explosion chamber, into the chamber 2 and nozzles 3 which are constructed as de Laval nozzles. Flanges 4, 5, may be milled to shape and welded together. A wall 12 separates chambers 9, 10. The coolant flows through holes in walls 21, 22, 20. The cooling space 13 is fed with hot water or other liquid under pressure through conduit 14, independently of the nozzle cooling system. The walls 25, 26, are thin and elastic to allow for thermal expansion.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE526554X | 1938-03-19 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB526554A true GB526554A (en) | 1940-09-20 |
Family
ID=6553023
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8823/39A Expired GB526554A (en) | 1938-03-19 | 1939-03-20 | Improvements in and relating to nozzles and nozzle segments for combustion turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB526554A (en) |
-
1939
- 1939-03-20 GB GB8823/39A patent/GB526554A/en not_active Expired
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