GB865877A - Axial-flow compressor or turbine rotor discs - Google Patents
Axial-flow compressor or turbine rotor discsInfo
- Publication number
- GB865877A GB865877A GB37098/59A GB3709859A GB865877A GB 865877 A GB865877 A GB 865877A GB 37098/59 A GB37098/59 A GB 37098/59A GB 3709859 A GB3709859 A GB 3709859A GB 865877 A GB865877 A GB 865877A
- Authority
- GB
- United Kingdom
- Prior art keywords
- ring
- rim
- radially inner
- pins
- turbine
- 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
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/326—Locking of axial insertion type blades by other means
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
865,877. Turbine and compressor rotor blades. GENERAL MOTORS CORPORATION. Nov. 2, 1959 [Jan. 27, 1959], No. 37098/59. Class 110 (3). An axial flow compressor or turbine disc comprising blades mounted on its rim in dovetail slots has each blade locked axially in position by a pin which passes through the rim of the disc to co-operate with abutments on the blade roots, and an expandable split ring fitted around the radially inner ends of the pins to prevent them dropping out. Turbine blades 13 are inserted into dovetail slots 12 in the rim 11 of a compressor disc 10. Each blade root 14 has a peripheral notch 21 cut in it, into which is fitted a locking pin 16 which is inserted through a hole 17 in the rim 11 from the radially inner surface 18 of the rim. A channel section split ring 25 is fitted around the radially inner ends of the locking pins 16 such that a gap 29 is left between the two ends of the split ring 25. Flange 27 of the ring 25 engages the upstream edges of the locking pins and flange 28 extends radially outwardly to engage with the radially inner surface 18 of the rotor rim. To prevent rotation of the split ring 25 tabs 31 and 32 formed from the base 26 of the ring are arranged to engage one of the pins 16. In a further embodiment (Figs. 4, 5 and 6, not shown) a split retaining ring has the tabs for locating the ring formed from the side flanges of the ring.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US789647A US2982518A (en) | 1959-01-28 | 1959-01-28 | Blade lock pin retainer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB865877A true GB865877A (en) | 1961-04-19 |
Family
ID=25148249
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB37098/59A Expired GB865877A (en) | 1959-01-28 | 1959-11-02 | Axial-flow compressor or turbine rotor discs |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US2982518A (en) |
| GB (1) | GB865877A (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3295826A (en) * | 1966-04-08 | 1967-01-03 | Gen Motors Corp | Blade lock |
| US4767276A (en) * | 1986-12-19 | 1988-08-30 | General Electric Company | Retainer ring |
| US10641111B2 (en) * | 2018-08-31 | 2020-05-05 | Rolls-Royce Corporation | Turbine blade assembly with ceramic matrix composite components |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR341486A (en) * | 1904-03-03 | 1904-08-09 | Leon Dufour | Blade fastening system for steam or gas turbines |
| US2713991A (en) * | 1951-05-05 | 1955-07-26 | A V Roe Canada Ltd | Rotor blade locking device |
| GB712112A (en) * | 1951-07-13 | 1954-07-21 | Bristol Aeroplane Co Ltd | Improvements in or relating to blade-locking means for turbine and the like rotor assemblies |
| US2953348A (en) * | 1952-12-30 | 1960-09-20 | Gen Motors Corp | Blade fastenings |
| BE529656A (en) * | 1953-04-10 | |||
| DE1070335B (en) * | 1955-06-24 |
-
1959
- 1959-01-28 US US789647A patent/US2982518A/en not_active Expired - Lifetime
- 1959-11-02 GB GB37098/59A patent/GB865877A/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| US2982518A (en) | 1961-05-02 |
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