GB569579A - Improvements in turbines - Google Patents
Improvements in turbinesInfo
- Publication number
- GB569579A GB569579A GB18800/43A GB1880043A GB569579A GB 569579 A GB569579 A GB 569579A GB 18800/43 A GB18800/43 A GB 18800/43A GB 1880043 A GB1880043 A GB 1880043A GB 569579 A GB569579 A GB 569579A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blades
- pressure
- reaction
- gas
- turbines
- 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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
- F01D1/023—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines the working-fluid being divided into several separate flows ; several separate fluid flows being united in a single flow; the machine or engine having provision for two or more different possible fluid flow paths
Abstract
569,579. Turbines. AKTIEBOLAGET GOTAVERKEN. Nov. 11, 1943, No. 18800. Convention date, Nov. 9, 1942. [Class 110 (iii)] In a turbine, elastic fluids of different pressures are led along separate paths tc different sets of blades, moving blades of the impulse type being provided for the higher pressure region, the reaction blades for working fluid at a lower pressure. For intermediate regions of pressure the blades may be shaped approximately as a mean between impulse and reaction shaped blades. Fig. 1 shows a high pres sure inlet 1 for impulse blades 10, and an inlet 2 for lower pressure gas for reaction blades 11, a common exhaust chamber 1: being provided. The 'gas pressure in the space 16 is preferably uniform. In Fig. 4 the high pressure gas enters at 18 and the low pressure gas at 17. The second ring of rotor blades 25 is common to the two gas streams, being of the reaction type. The pressure in the space 28 is uniform. The invention may be extended to turbines having more than two gas streams, and further expansion stages may be used. Radial flow turbines may be used, including those of the double rotation type.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SE569579X | 1942-11-09 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB569579A true GB569579A (en) | 1945-05-30 |
Family
ID=20312213
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB18800/43A Expired GB569579A (en) | 1942-11-09 | 1943-11-11 | Improvements in turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB569579A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2252133A (en) * | 1991-01-25 | 1992-07-29 | Gec Aerospace Ltd | Gas turbines |
-
1943
- 1943-11-11 GB GB18800/43A patent/GB569579A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2252133A (en) * | 1991-01-25 | 1992-07-29 | Gec Aerospace Ltd | Gas turbines |
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