GB630732A - An improved blade fixing for turbines and the like - Google Patents
An improved blade fixing for turbines and the likeInfo
- Publication number
- GB630732A GB630732A GB1865546A GB1865546A GB630732A GB 630732 A GB630732 A GB 630732A GB 1865546 A GB1865546 A GB 1865546A GB 1865546 A GB1865546 A GB 1865546A GB 630732 A GB630732 A GB 630732A
- Authority
- GB
- United Kingdom
- Prior art keywords
- key
- grooves
- tongue
- keyway
- blade
- 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
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/3046—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses the rotor having ribs around the circumference
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
630,732. Turbine and compressor blades. BRUSH ELECTRICAL ENGINEERING CO., Ltd., and HARRIS, J. W. June 21, 1946, No. 18655. [Class 110(iii)] In a bladed unit for a turbine or compressor, of the type comprising a deep tongue-and-slot connection between the blade roots and the blade carrier, an annular keyway is formed partly in the carrier and partly in the blade roots. A key of less length than the keyway is fitted in the keyway and is extended by elongation. The legs 6 are prevented from opening out by means of ribs 11 fitting in grooves 12; alternatively, or in addition, ribs 11<1> and grooves 12<1> may be provided. Each key 9 consists of a single hoop of wire or a number of accurate lengths of wire, and is of such length that a space is left for the insertion of the last blade. After the latter has been inserted, each key is elongated to close the gap by punching or pressing it by means of a tool inserted successively in holes 10 provided in the legs 6. The keys may be of rectangular section, and there may be only one key at each side of the tongue. The mating flanks of the tongue and grooves may be parallel instead of stepped or may be tapered. Speci- ' fication 9570/04 [CLass 110], is referred to.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1865546A GB630732A (en) | 1946-06-21 | 1946-06-21 | An improved blade fixing for turbines and the like |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1865546A GB630732A (en) | 1946-06-21 | 1946-06-21 | An improved blade fixing for turbines and the like |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB630732A true GB630732A (en) | 1949-10-20 |
Family
ID=10116179
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1865546A Expired GB630732A (en) | 1946-06-21 | 1946-06-21 | An improved blade fixing for turbines and the like |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB630732A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5073084A (en) * | 1989-10-04 | 1991-12-17 | Rolls-Royce Plc | Single-price labyrinth seal structure |
| US5536145A (en) * | 1992-10-27 | 1996-07-16 | Societe Europeenne De Propulsion | Method of manufacturing a turbine wheel having inserted blades, and a wheel obtained by performing the method |
| WO2005010323A1 (en) * | 2003-07-26 | 2005-02-03 | Alstom Technology Ltd | Device for fixing the blade root on a turbomachine |
| EP2818638A1 (en) | 2013-06-27 | 2014-12-31 | MTU Aero Engines GmbH | Rotor-blade group, method and turbomachine |
| EP2873808A1 (en) | 2013-11-19 | 2015-05-20 | MTU Aero Engines GmbH | Rotor-blade group, method and flow engine |
-
1946
- 1946-06-21 GB GB1865546A patent/GB630732A/en not_active Expired
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5073084A (en) * | 1989-10-04 | 1991-12-17 | Rolls-Royce Plc | Single-price labyrinth seal structure |
| US5536145A (en) * | 1992-10-27 | 1996-07-16 | Societe Europeenne De Propulsion | Method of manufacturing a turbine wheel having inserted blades, and a wheel obtained by performing the method |
| WO2005010323A1 (en) * | 2003-07-26 | 2005-02-03 | Alstom Technology Ltd | Device for fixing the blade root on a turbomachine |
| EP2818638A1 (en) | 2013-06-27 | 2014-12-31 | MTU Aero Engines GmbH | Rotor-blade group, method and turbomachine |
| EP2873808A1 (en) | 2013-11-19 | 2015-05-20 | MTU Aero Engines GmbH | Rotor-blade group, method and flow engine |
| DE102013223583A1 (en) | 2013-11-19 | 2015-05-21 | MTU Aero Engines AG | Shovel-disc composite, method and turbomachine |
| US10041363B2 (en) | 2013-11-19 | 2018-08-07 | MTU Aero Engines AG | Blade-disk assembly, method and turbomachine |
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