GB578009A - Improvements in or relating to turbines - Google Patents
Improvements in or relating to turbinesInfo
- Publication number
- GB578009A GB578009A GB1500141A GB1500141A GB578009A GB 578009 A GB578009 A GB 578009A GB 1500141 A GB1500141 A GB 1500141A GB 1500141 A GB1500141 A GB 1500141A GB 578009 A GB578009 A GB 578009A
- Authority
- GB
- United Kingdom
- Prior art keywords
- passages
- disc
- discs
- roots
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
- F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
Abstract
578,009. Gas turbines. HALFORD, F. B. Nov. 21, 1941, No. 15001. [Class 110 (iii)] The serrated roots of turbine blades H are gripped between the rim parts of two rotor discs A, B. The discs may be secured together by hub bolts E only, or, also by riveted distance pieces near the rim. Meeting faces of the blade roots are grooved so as to form when assembled passages J<4> and holes J<3> in the blade roots form annular passages connecting the passages J<4>. Cooling air is admitted by passages G to the space between the discs and escapes through the passages J<4> over the periphery of disc B into an annular channel K<1> within the exhaust K. Cooling air passes also between disc A and a fixed cover O and enters the blade stream over the periph ery of the disc A.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1500141A GB578009A (en) | 1941-11-21 | 1941-11-21 | Improvements in or relating to turbines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1500141A GB578009A (en) | 1941-11-21 | 1941-11-21 | Improvements in or relating to turbines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB578009A true GB578009A (en) | 1946-06-12 |
Family
ID=10051325
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1500141A Expired GB578009A (en) | 1941-11-21 | 1941-11-21 | Improvements in or relating to turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB578009A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2552817A1 (en) * | 1978-11-27 | 1985-04-05 | Snecma | IMPROVEMENTS TO THE COOLING OF TURBINE ROTORS |
| US8708657B2 (en) | 2010-01-22 | 2014-04-29 | Rolls-Royce Plc | Rotor Disc |
| CN114542191A (en) * | 2022-03-28 | 2022-05-27 | 南昌航空大学 | Double-spoke-plate turbine disc with high-bearing flow guide structure |
-
1941
- 1941-11-21 GB GB1500141A patent/GB578009A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2552817A1 (en) * | 1978-11-27 | 1985-04-05 | Snecma | IMPROVEMENTS TO THE COOLING OF TURBINE ROTORS |
| US8708657B2 (en) | 2010-01-22 | 2014-04-29 | Rolls-Royce Plc | Rotor Disc |
| CN114542191A (en) * | 2022-03-28 | 2022-05-27 | 南昌航空大学 | Double-spoke-plate turbine disc with high-bearing flow guide structure |
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