GB345888A - An improved method of supporting the guide blades in turbines - Google Patents
An improved method of supporting the guide blades in turbinesInfo
- Publication number
- GB345888A GB345888A GB17072/30A GB1707230A GB345888A GB 345888 A GB345888 A GB 345888A GB 17072/30 A GB17072/30 A GB 17072/30A GB 1707230 A GB1707230 A GB 1707230A GB 345888 A GB345888 A GB 345888A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbines
- casing
- blades
- rateau
- june
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Polyesters Or Polycarbonates (AREA)
Abstract
345,888. Gas turbines. RATEAU, L. A. J., NOBLEMAIRE, M. A. G. MARGOT-, and RATEAU, A. J. A., 10 bis, Avenue Elisee Reclus, Paris. June 2, 1930, No. 17072. Convention date, June 4, 1929. [Class 110 (iii).] In axial-flow turbines, particularly those subject to high temperatures as in turbo-compressers for aircraft engines, the fixed distributer blades a are formed integral with or are fixed to a part d which is secured to the casing of the turbine at points, as at f, near the axis of rotation. The outer casing is not in contact with the hot gases. The outer tips of the blades are pinned to the member h at k, and this member is connected to the casing by resilient arms l. A fan i mounted on the shaft draws air through the duct e and serves to cool the parts and also to prevent leakage of gas.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| BE345888X | 1929-06-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB345888A true GB345888A (en) | 1931-04-02 |
Family
ID=3868108
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB17072/30A Expired GB345888A (en) | 1929-06-04 | 1930-06-02 | An improved method of supporting the guide blades in turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB345888A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2470126A (en) * | 1942-12-05 | 1949-05-17 | Allis Chalmers Mfg Co | Turbine construction |
| US3067981A (en) * | 1959-06-15 | 1962-12-11 | Ford Motor Co | Gas turbine engine |
| US4027996A (en) * | 1974-07-22 | 1977-06-07 | Kraftwerk Union Aktiengesellschaft | Turbomachine, such as a steam turbine with high steam inlet temperature, especially |
| US4032253A (en) * | 1975-09-11 | 1977-06-28 | Carrier Corporation | Compensating ring for a rotary machine |
-
1930
- 1930-06-02 GB GB17072/30A patent/GB345888A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2470126A (en) * | 1942-12-05 | 1949-05-17 | Allis Chalmers Mfg Co | Turbine construction |
| US3067981A (en) * | 1959-06-15 | 1962-12-11 | Ford Motor Co | Gas turbine engine |
| US4027996A (en) * | 1974-07-22 | 1977-06-07 | Kraftwerk Union Aktiengesellschaft | Turbomachine, such as a steam turbine with high steam inlet temperature, especially |
| US4032253A (en) * | 1975-09-11 | 1977-06-28 | Carrier Corporation | Compensating ring for a rotary machine |
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