GB655466A - Improved blade ring for radial flow elastic fluid turbines and compressors and method of manufacturing same - Google Patents
Improved blade ring for radial flow elastic fluid turbines and compressors and method of manufacturing sameInfo
- Publication number
- GB655466A GB655466A GB4936/48A GB493648A GB655466A GB 655466 A GB655466 A GB 655466A GB 4936/48 A GB4936/48 A GB 4936/48A GB 493648 A GB493648 A GB 493648A GB 655466 A GB655466 A GB 655466A
- Authority
- GB
- United Kingdom
- Prior art keywords
- roots
- ring
- blades
- blade
- rings
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
- F01D5/041—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the Ljungström type
Abstract
655,466. Turbine blades. SVENSKA TURBINFABRIKS AKTIEBOLAGET LJUNGSTROM. Feb. 19, 1948, Nos. 4936 and 4937. Convention dates, Oct. 17, 1947 and Nov. 14, 1947. [Class 110(iii)] [Also in Group XXII] In a blade ring for a radial-flow elasticfluid turbine or compressor, the roots 2 of the blades 1 and the grooves 3 in the supporting ring 4 are shaped so that the roots and the grooves may be brought into sealed engagement by a combined and substantially simultaneous axial and radial movement of the roots and supporting rings with respect to each other, no preliminary bending out or subsequent pressing down of the rims of the grooves being necessary. One method of assembly is shown in Fig. 2 in which the blades are assembled in a clamping device comprising rings 7 and 8, the diameters of which may be varied so that after suitably shaping the blade roots, the diameters of the rings may be first reduced and then increased. Alternatively, the blade ring may be assembled by heating the supporting rings and at the same time cooling the blades and then allowing the temperatures to equalize. The blade ring may be assembled by a combination of these methods. An auxiliary fastening such as the ring 25, Fig. 12, may be used to seal the joint between the blade roots and the supporting ring. Many modifications are described and illustrated.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SE655466X | 1947-10-17 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB655466A true GB655466A (en) | 1951-07-25 |
Family
ID=20314158
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB4936/48A Expired GB655466A (en) | 1947-10-17 | 1948-02-19 | Improved blade ring for radial flow elastic fluid turbines and compressors and method of manufacturing same |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB655466A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6102664A (en) * | 1995-12-14 | 2000-08-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Blading system and method for controlling structural vibrations |
| GB2380770A (en) * | 2001-10-13 | 2003-04-16 | Rolls Royce Plc | Stress-reducing indentor profile for gas turbine engine blade mountings and other applications |
-
1948
- 1948-02-19 GB GB4936/48A patent/GB655466A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6102664A (en) * | 1995-12-14 | 2000-08-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Blading system and method for controlling structural vibrations |
| GB2380770A (en) * | 2001-10-13 | 2003-04-16 | Rolls Royce Plc | Stress-reducing indentor profile for gas turbine engine blade mountings and other applications |
| GB2380770B (en) * | 2001-10-13 | 2005-09-07 | Rolls Royce Plc | Indentor arrangement |
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