GB635783A - Improvements in or relating to turbine wheels and the like - Google Patents
Improvements in or relating to turbine wheels and the likeInfo
- Publication number
- GB635783A GB635783A GB1723547A GB1723547A GB635783A GB 635783 A GB635783 A GB 635783A GB 1723547 A GB1723547 A GB 1723547A GB 1723547 A GB1723547 A GB 1723547A GB 635783 A GB635783 A GB 635783A
- Authority
- GB
- United Kingdom
- Prior art keywords
- disc
- discs
- shaft
- cool
- holes
- 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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
635,783. Turbine rotors. MORLEY, F. W. W. June 30, 1947, No 17235. [Class 110(iii)] A turbine rotor comprises a disc 10 integral with a shaft 13 and a disc 11 which is formed with a spigot 16 engaging in a socket provided by an annular projection 14 on the disc 10. A second stage rotor disc 12 has a similar spigot connection 17, 18 with the disc 11 and a spline connection 19, 20 with the shaft. The discs are clamped together by a nut 21. A spacing sleeve 23 between the discs is made slightly long so that the discs are conically deformed when clamped together. A washer 22a under the nut 21 is of a material such that its axial extension due to thermal expansion compensates for the axial shortening of the disc hubs due to stressing during running. In an alternative form, the socket 18 is formed on the shaft 13. Cooling air from the hollow shaft passes through holes 25 to cool the exterior of disc 10, through holes 26, 27 to cool the interior of rotor 10, 11 and through holes 26, 28 to cool the faces of discs 11, 12.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1723547A GB635783A (en) | 1947-06-30 | 1947-06-30 | Improvements in or relating to turbine wheels and the like |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1723547A GB635783A (en) | 1947-06-30 | 1947-06-30 | Improvements in or relating to turbine wheels and the like |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB635783A true GB635783A (en) | 1950-04-19 |
Family
ID=10091620
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1723547A Expired GB635783A (en) | 1947-06-30 | 1947-06-30 | Improvements in or relating to turbine wheels and the like |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB635783A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2757900A (en) * | 1950-06-01 | 1956-08-07 | United Aircraft Corp | Turbine rotor construction |
| US5857835A (en) * | 1996-05-14 | 1999-01-12 | Rolls Royce, Plc | Fluid-coated turbine rator disc for a gas turbine engine |
| US6190127B1 (en) * | 1998-12-22 | 2001-02-20 | General Electric Co. | Tuning thermal mismatch between turbine rotor parts with a thermal medium |
| US6379108B1 (en) | 2000-08-08 | 2002-04-30 | General Electric Company | Controlling a rabbet load and air/oil seal temperatures in a turbine |
| EP3244006A1 (en) * | 2016-03-31 | 2017-11-15 | Rolls-Royce plc | A shaft and a turbomachine |
-
1947
- 1947-06-30 GB GB1723547A patent/GB635783A/en not_active Expired
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2757900A (en) * | 1950-06-01 | 1956-08-07 | United Aircraft Corp | Turbine rotor construction |
| US5857835A (en) * | 1996-05-14 | 1999-01-12 | Rolls Royce, Plc | Fluid-coated turbine rator disc for a gas turbine engine |
| US6190127B1 (en) * | 1998-12-22 | 2001-02-20 | General Electric Co. | Tuning thermal mismatch between turbine rotor parts with a thermal medium |
| US6379108B1 (en) | 2000-08-08 | 2002-04-30 | General Electric Company | Controlling a rabbet load and air/oil seal temperatures in a turbine |
| EP3244006A1 (en) * | 2016-03-31 | 2017-11-15 | Rolls-Royce plc | A shaft and a turbomachine |
| US10316854B2 (en) | 2016-03-31 | 2019-06-11 | Rolls-Royce Plc | Shaft and a turbomachine |
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