GB191211706A - Improvements in Turbine Vanes and in Means for Securing such Vanes to the Rotor of a Steam or Gas Turbine. - Google Patents
Improvements in Turbine Vanes and in Means for Securing such Vanes to the Rotor of a Steam or Gas Turbine.Info
- Publication number
- GB191211706A GB191211706A GB191211706DA GB191211706A GB 191211706 A GB191211706 A GB 191211706A GB 191211706D A GB191211706D A GB 191211706DA GB 191211706 A GB191211706 A GB 191211706A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- vanes
- shank
- flange
- shanks
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
11,706. Fraser & Chalmers, and Pochobradsky, B. F. May 16. Blades.-The rivets which secure the shanks of the blades to the turbine rotor are arranged on one and the same pitch circle, and each rivet is shared between two adjacent vanes. Short and light shanks may consequently be employed. The shank b of the blade a may be solid, Fig. 1, and is provided with recesses c, d or the same pitch circle registering with similar recesses in adjacent blade shanks, each rivet thereby holding two adjacent vanes. The shank b, Fig. 2, may carry a curved flange e at the rear of the blade, the back of the flange abutting against the next blade. Alternatively, this flange may be disposed in front of the blade. The invention is applicable to a forked shank f, Fig. 5, which may similarly be fitted with a flange. A modified form of blade having a shrouding i is shown in Figs. 9 and 10 secured by its forked shank f astride a web j.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB191211706T | 1912-05-16 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB191211706A true GB191211706A (en) | 1912-10-17 |
Family
ID=32572100
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB191211706D Expired GB191211706A (en) | 1912-05-16 | 1912-05-16 | Improvements in Turbine Vanes and in Means for Securing such Vanes to the Rotor of a Steam or Gas Turbine. |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB191211706A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3063674A (en) * | 1961-02-08 | 1962-11-13 | Jr Clarence E Middlebrooks | Rotor construction and method |
US20220412216A1 (en) * | 2019-12-10 | 2022-12-29 | Safran Aircraft Engines | Turbine rotor wheel for an aircraft turbomachine |
-
1912
- 1912-05-16 GB GB191211706D patent/GB191211706A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3063674A (en) * | 1961-02-08 | 1962-11-13 | Jr Clarence E Middlebrooks | Rotor construction and method |
US20220412216A1 (en) * | 2019-12-10 | 2022-12-29 | Safran Aircraft Engines | Turbine rotor wheel for an aircraft turbomachine |
US11788423B2 (en) * | 2019-12-10 | 2023-10-17 | Safran Aircraft Engines | Turbine rotor wheel for an aircraft turbomachine |
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