GB865544A - Turbines - Google Patents
TurbinesInfo
- Publication number
- GB865544A GB865544A GB1187358A GB1187358A GB865544A GB 865544 A GB865544 A GB 865544A GB 1187358 A GB1187358 A GB 1187358A GB 1187358 A GB1187358 A GB 1187358A GB 865544 A GB865544 A GB 865544A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blades
- ring
- flange
- rings
- project
- 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
- 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)
- Gasket Seals (AREA)
Abstract
865,544. Turbine stator blade assemblies. NAPIER & SON Ltd., D. April 8, 1959 [April 14, 1958], No. 11873/58. Class 110 (3). A turbine stator assembly comprises inner and outer support rings and a series of hollow stator blades mounted between the two rings, the inner and outer support rings being each formed with a series of circumferentially spaced slots through which the respective ends of the blades project, tangentially extending apertures being formed in the projecting ends of the blades and locking- wires being threaded through the apertures. Means are also provided for delivering cooling air to an annular cooling chamber surrounding the outer support ring, the cooling air then passing radially inwardly through the hollow blades and issuing into an annular space formed within the inner support ring. The invention is shown applied to gas turbine inlet nozzle structure which comprises a series of hollow sheet-metal guide-blades 14 mounted between outer and inner rings 11, 12, the outer ring 11 being of substantially channel section and the inner ring 12 of T-section. The outer ends 18 of the blades 14 project through openings in the base of the ring 11 and a locking wire 20 is threaded through holes in the projecting ends. Similarly, the inner ends 19 project through openings in the flange of the inner ring 12 and a locking wire 21 is threaded through holes in the projecting ends. A cover-plate 32 is secured to the outer support ring 11 so as to form a cooling air manifold 31 to which air is supplied through duct 30 and from which it passes through the hollow guide blades 14 to discharge radially inwardly of the inner support ring 12. The plate 32 lies over the flange 33 of the outer support ring and under the flange 35, the flange 35 being formed with spaced projections 36 to which the plate 32 is secured by welding, the portions 37 between the projections not being welded. The flange 33 is formed with notches 34 which form openings for the inflow of cooling air from the duct 30. The parts 37 between the welded joints are sealed by applying thereto a coating of stainless steel applied in molten form from a hot metal spray gun. The coating would also in practice be applied over the welded joints at the projections 36. The parts of the blades which project through the slots in the outer and inner support rings are also sealed to the support rings by a sprayed metal coating. Specification 865,545 is referred to.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1187358A GB865544A (en) | 1958-04-14 | 1958-04-14 | Turbines |
GB1162259A GB865545A (en) | 1958-04-14 | 1958-04-14 | Turbines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1187358A GB865544A (en) | 1958-04-14 | 1958-04-14 | Turbines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB865544A true GB865544A (en) | 1961-04-19 |
Family
ID=9994231
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1187358A Expired GB865544A (en) | 1958-04-14 | 1958-04-14 | Turbines |
GB1162259A Expired GB865545A (en) | 1958-04-14 | 1958-04-14 | Turbines |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1162259A Expired GB865545A (en) | 1958-04-14 | 1958-04-14 | Turbines |
Country Status (1)
Country | Link |
---|---|
GB (2) | GB865544A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1548233A1 (en) * | 2003-12-18 | 2005-06-29 | Techspace Aero S.A. | Fastening device for stator blades and compressor stator stage comprising such a fastening device |
EP3284912A1 (en) * | 2016-08-18 | 2018-02-21 | United Technologies Corporation | Stator shroud with mechanical retention |
US10450878B2 (en) | 2016-07-06 | 2019-10-22 | United Technologies Corporation | Segmented stator assembly |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4492517A (en) * | 1983-01-06 | 1985-01-08 | General Electric Company | Segmented inlet nozzle for gas turbine, and methods of installation |
US5176496A (en) * | 1991-09-27 | 1993-01-05 | General Electric Company | Mounting arrangements for turbine nozzles |
FR3018308B1 (en) * | 2014-03-06 | 2016-04-08 | Herakles | STATOR SECTOR FOR TURBOMACHINE AND METHOD FOR MANUFACTURING THE SAME |
-
1958
- 1958-04-14 GB GB1187358A patent/GB865544A/en not_active Expired
- 1958-04-14 GB GB1162259A patent/GB865545A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1548233A1 (en) * | 2003-12-18 | 2005-06-29 | Techspace Aero S.A. | Fastening device for stator blades and compressor stator stage comprising such a fastening device |
US10450878B2 (en) | 2016-07-06 | 2019-10-22 | United Technologies Corporation | Segmented stator assembly |
EP3284912A1 (en) * | 2016-08-18 | 2018-02-21 | United Technologies Corporation | Stator shroud with mechanical retention |
US10472979B2 (en) | 2016-08-18 | 2019-11-12 | United Technologies Corporation | Stator shroud with mechanical retention |
Also Published As
Publication number | Publication date |
---|---|
GB865545A (en) | 1961-04-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4522557A (en) | Cooling device for movable turbine blade collars | |
US3670497A (en) | Combustion chamber support | |
US5399066A (en) | Integral clearance control impingement manifold and environmental shield | |
US3864056A (en) | Cooled turbine blade ring assembly | |
US2510645A (en) | Air nozzle and porting for combustion chamber liners | |
US2581999A (en) | Hemispherical combustion chamber end dome having cooling air deflecting means | |
GB1311630A (en) | Gas turbine power plant | |
GB790293A (en) | Improvements in or relating to heat-resisting wall structures for gas-turbine enginecombustion equipment | |
GB806349A (en) | Improvements relating to combustion chambers | |
GB647293A (en) | Cooled metallic combustion chamber for the production of heating and driving gases | |
GB705150A (en) | Improvements in and relating to variable guide blade arrangements for high temperature turbines | |
GB1425879A (en) | Cooled turbine rotor shroud | |
GB618525A (en) | Improvements in or relating to gas-turbine engines | |
GB840054A (en) | A device for generating power gases for driving power plants such as turbines | |
US4718230A (en) | Augmentor liner construction | |
US10203114B2 (en) | Sleeve assemblies and methods of fabricating same | |
GB865544A (en) | Turbines | |
EP3412972B1 (en) | Gas turbine comprising a plurality of can-combustors | |
GB879337A (en) | Improvements relating to stator vane units for rotary power plants | |
GB677274A (en) | Improvements in and relating to gas turbine nozzle structures | |
US3749512A (en) | Inlet structure for turbo machine | |
CA2956526C (en) | Burner for a combustion machine, and combustion machine | |
US2670600A (en) | Air distribution system for flame tubes of gas turbine engines | |
GB806815A (en) | Turbine blade shroud rings | |
GB1024959A (en) | Improvements in self-aligning mounting structure for a gas turbine engine |