GB797488A - Gas turbine rotor - Google Patents
Gas turbine rotorInfo
- Publication number
- GB797488A GB797488A GB36572/56A GB3657256A GB797488A GB 797488 A GB797488 A GB 797488A GB 36572/56 A GB36572/56 A GB 36572/56A GB 3657256 A GB3657256 A GB 3657256A GB 797488 A GB797488 A GB 797488A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shrouds
- blades
- row
- blade
- reaction
- 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
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
797,488. Elastic-fluid turbines. MASCHINENFABRIK OERLIKON. Nov. 29, 1956 [Dec. 30, 1955], No. 36572/56. Class 110 (3). The high-pressure end of multi-stage gas turbine rotor comprises at least one row of unshrouded blades 2 providing only a small degree of reaction, whereas the remaining rows of blades 3 are provided at their tips with shrouds 4 and have a high degree of reaction. The shrouds 4 may extend wholly circumferentially around each row of blades, or they may be in segments surrounding groups of blades of each blade row. The object of the invention is to dispense with blade shrouds at the high pressure end of the turbine since these shrouds tend to intercept any impurities such as vanadium pentoxides or sodium oxides contained in the gas stream whereby the balance of the rotor is disturbed. With only a small degree of reaction in the high pressure stage, the pressure drop across the blade row is reduced and the necessity of a blade shroud is avoided.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH797488X | 1955-12-30 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB797488A true GB797488A (en) | 1958-07-02 |
Family
ID=4537402
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB36572/56A Expired GB797488A (en) | 1955-12-30 | 1956-11-29 | Gas turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB797488A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3034762A (en) * | 1960-05-31 | 1962-05-15 | United Aircraft Corp | Blade damping means |
-
1956
- 1956-11-29 GB GB36572/56A patent/GB797488A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3034762A (en) * | 1960-05-31 | 1962-05-15 | United Aircraft Corp | Blade damping means |
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