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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
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 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB751011A (en) | Improvements in or relating to the cooling of turbine blades | |
GB837575A (en) | Improvements in gas turbine rotor | |
GB837469A (en) | Gas turbine rotor assembly | |
GB621545A (en) | Improvements relating to axial compressors and turbines | |
GB705387A (en) | Improvements relating to radial-flow turbine or centrifugal compressors | |
GB319622A (en) | Gas turbine | |
GB578009A (en) | Improvements in or relating to turbines | |
GB1450133A (en) | Cooling of gas turbine engines | |
GB359350A (en) | Connection of rotarys for combustion turbines | |
GB586562A (en) | Improvements in high speed axial flow elastic fluid turbines, compressors, superchargers and like apparatus | |
GB742288A (en) | Improvements in the cooling of turbines | |
GB617472A (en) | Improvements in or relating to gas-turbine-engines | |
GB635890A (en) | Improvements in or relating to turbine and like rotors | |
GB585331A (en) | Improvements in or relating to internal-combustion turbines | |
GB704882A (en) | Improvements in and relating to the securing of blading to turbine wheels and other high speed rotary members | |
GB586551A (en) | Improvements in or relating to internal combustion power turbine plant for propulsion in air | |
GB578191A (en) | Improvements in or relating to turbines | |
GB1302661A (en) | ||
GB561692A (en) | Improvements in or relating to thermal power plants | |
GB586556A (en) | Improvements in internal combustion turbine plant for propulsion | |
GB585350A (en) | Improvements in or relating to the cooling of turbine wheels and blades | |
GB512301A (en) | An arrangements for cooling solid blades for exhaust gas turbines | |
GB624777A (en) | Improvements in or relating to stator casings for compressors and like machines | |
GB586564A (en) | Improvements in high speed axial flow elastic fluid turbines, compressors, superchargers and like apparatus | |
GB1258837A (en) |