GB1053846A - - Google Patents
Info
- Publication number
- GB1053846A GB1053846A GB1053846DA GB1053846A GB 1053846 A GB1053846 A GB 1053846A GB 1053846D A GB1053846D A GB 1053846DA GB 1053846 A GB1053846 A GB 1053846A
- Authority
- GB
- United Kingdom
- Prior art keywords
- casing
- blade
- flanges
- section
- unsplit
- 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.)
- Active
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1,053,846. Turbines; gas turbine plant; axial flow compressors. LICENTIA PATENTVERWALTUNGS-G.m.b.H. Oct. 9, 1963 [Oct. 10, 1962], No.39803/63. Headings F1C, F1G and F1T. The stator blades 10 of an axial flow compressor or gas turbine are mounted in apertures 11 in an unsplit inner casing 14 which are profiled to conform with the cross section of each blade 10 at the aperture. A further casing 12 having larger apertures 13 surrounding each blade 10 and annular flanges 20, 21 surrounds the casing 14. The blades 10 are located radially by resilient sheet metal sections 17 carried in grooves 18, 19 in the flanges 20, 21. Each section 17 locates in a groove 22, Fig. 2 (not shown) in the concave face of a blade 10 and engages with the convex face of the circumferentially adjacent blade, a recess (23) being provided in the section 17 for this purpose. A split or unsplit outer shell 24 surrounds the casings 13, 14 in sealing engagement with piston rings 27 on the flanges 20, 21. When the construction is applied to a compressor stator, the casing 14 may be of a synthetic plastic. Coolant may be supplied to the annular chambers between the casing 12 and shell 24.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE1962L0043159 DE1291559B (en) | 1962-10-10 | 1962-10-10 | Multi-stage axial turbo machine, in particular a gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1053846A true GB1053846A (en) |
Family
ID=7270184
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1053846D Active GB1053846A (en) | 1962-10-10 |
Country Status (3)
| Country | Link |
|---|---|
| CH (1) | CH427415A (en) |
| DE (1) | DE1291559B (en) |
| GB (1) | GB1053846A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2220034A (en) * | 1988-06-22 | 1989-12-28 | Rolls Royce Plc | Load transmission in gas turbine engines |
| WO1999031357A1 (en) * | 1997-12-17 | 1999-06-24 | Pratt & Whitney Canada Corp. | Support for a turbine stator assembly |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1605297A (en) * | 1977-05-05 | 1988-06-08 | Rolls Royce | Nozzle guide vane structure for a gas turbine engine |
| FR2606071B1 (en) * | 1986-10-29 | 1990-11-30 | Snecma | STATOR STAGE AND TURBOMACHINE COMPRESSOR COMPRISING THE SAME |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE492385A (en) * | 1948-11-27 | |||
| GB666537A (en) * | 1949-08-27 | 1952-02-13 | Armstrong Siddeley Motors Ltd | Mounting of the stator blades of a gaseous fluid turbine |
| FR998220A (en) * | 1949-10-26 | 1952-01-16 | Soc D Const Et D Equipements M | Advanced training in the assembly and fixing of fixed blades for turbomachines |
| GB695724A (en) * | 1950-08-01 | 1953-08-19 | Rolls Royce | Improvements in or relating to structural elements for axial-flow turbo-machines such as compressors or turbines of gas-turbine engines |
| FR1057993A (en) * | 1952-04-08 | 1954-03-12 | Rolls Royce | Improvements to turbo-machines |
-
0
- GB GB1053846D patent/GB1053846A/en active Active
-
1962
- 1962-10-10 DE DE1962L0043159 patent/DE1291559B/en active Pending
-
1963
- 1963-10-03 CH CH1222463A patent/CH427415A/en unknown
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2220034A (en) * | 1988-06-22 | 1989-12-28 | Rolls Royce Plc | Load transmission in gas turbine engines |
| US4984423A (en) * | 1988-06-22 | 1991-01-15 | Rolls-Royce Plc | Aerodynamic loading in gas turbine engines |
| GB2220034B (en) * | 1988-06-22 | 1992-12-02 | Rolls Royce Plc | Aerodynamic loading in gas turbine engines |
| WO1999031357A1 (en) * | 1997-12-17 | 1999-06-24 | Pratt & Whitney Canada Corp. | Support for a turbine stator assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| CH427415A (en) | 1966-12-31 |
| DE1291559B (en) | 1969-03-27 |
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