GB730638A - Improvements in welded turbine or compressor bladed rotors and the construction thereof - Google Patents
Improvements in welded turbine or compressor bladed rotors and the construction thereofInfo
- Publication number
- GB730638A GB730638A GB469451A GB469451A GB730638A GB 730638 A GB730638 A GB 730638A GB 469451 A GB469451 A GB 469451A GB 469451 A GB469451 A GB 469451A GB 730638 A GB730638 A GB 730638A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- blade
- slots
- welded
- head
- 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
- F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
730,638. Fixing turbine and compressor blades. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Feb. 19, 1952 [Feb. 26, 1951], No. 4694/51. Class 110 (3). [Also in Group XXII] In making a bladed rotor of an axial flow turbine or compressor a surface on the root of a blade is welded to the corresponding radial surface on the rotor rim by heating the blade root and rim, preferably by arcing or sparking, and then applying pressure. In an embodiment a rotor 2, which may be two discs welded together, has slots in its periphery half way through its thickness with faces 2c, Fig. 1, transverse to the rotor axis, the slots alternately facing different directions. The rotor is mounted on a mandrel in bearings 11, 12, Fig. 3, which can be raised and lowered and moved towards and away from a fixed head 4 by handles 13a, 13b. A blade 1 with a step formed half-way through its thickness with a face 1b, Fig. 2, to co-operate with 2c, is held in a clamp 15 on a head 5 movable by hydraulic means 9. The rotor is pressed against an abutment 16 and head 5 is moved to insert the blade in a slot. Current from a transformer 17 causes sparking between blade and rotor and means 9 applies pressure for welding. Blades are welded in alternate slots from one side of the rotor and in the other slots from the other side of the rotor.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB469451A GB730638A (en) | 1951-02-26 | 1951-02-26 | Improvements in welded turbine or compressor bladed rotors and the construction thereof |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB469451A GB730638A (en) | 1951-02-26 | 1951-02-26 | Improvements in welded turbine or compressor bladed rotors and the construction thereof |
Publications (1)
Publication Number | Publication Date |
---|---|
GB730638A true GB730638A (en) | 1955-05-25 |
Family
ID=9782038
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB469451A Expired GB730638A (en) | 1951-02-26 | 1951-02-26 | Improvements in welded turbine or compressor bladed rotors and the construction thereof |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB730638A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3590454A (en) * | 1969-03-03 | 1971-07-06 | Us Air Force | Turbine assembly fabrication |
WO2010081467A1 (en) * | 2009-01-16 | 2010-07-22 | Mtu Aero Engines Gmbh | Divided disk of a turbine or compressor stage, comprising vanes welded onto it |
-
1951
- 1951-02-26 GB GB469451A patent/GB730638A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3590454A (en) * | 1969-03-03 | 1971-07-06 | Us Air Force | Turbine assembly fabrication |
WO2010081467A1 (en) * | 2009-01-16 | 2010-07-22 | Mtu Aero Engines Gmbh | Divided disk of a turbine or compressor stage, comprising vanes welded onto it |
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