GB611326A - Improvements in or relating to guide vanes for axial-flow turbines and compressors - Google Patents
Improvements in or relating to guide vanes for axial-flow turbines and compressorsInfo
- Publication number
- GB611326A GB611326A GB10630/46A GB1063046A GB611326A GB 611326 A GB611326 A GB 611326A GB 10630/46 A GB10630/46 A GB 10630/46A GB 1063046 A GB1063046 A GB 1063046A GB 611326 A GB611326 A GB 611326A
- Authority
- GB
- United Kingdom
- Prior art keywords
- vane
- axial
- ring
- compressors
- guide vanes
- 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
611,326. Axial-flow turbines and compressors. LOMBARD, A. A., and MORLEY, F. W. W. April 5, 1946, No. 10630. [Classes 110 (i) and 110 (iii)] In an axial-flow turbine or compressor of the type in which the guide vanes are mounted between inner and outer rings, each vane is secured to only one such ring at one part of the vane-end and is loosely supported by the other ring. Each vane is formed with circumferentially extending platforms 7, 8 which are of parallelogrammic or rectangular shape. The vane is located on rings 9, 10 by means of splines 17, 18, Figs. 3 and 4, which engage helically-disposed slots 11. The central part of each spline is machined away as at 19 to reduce any tendency to bind. A foot 13 projecting from one end of the spline 17 engages in a recess 14 in ring 9 and is loosely retained by an overlying flange 16 of the nozzle box 15. The platform 8 may engage an abutment 20. In a modified construction, Fig. 2, the splines 17, 18 are dispensed with, and the internal surfaces of the platforms 7, 8 are flush with the lands 12.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB257532X | 1946-04-05 | ||
GB30147X | 1947-01-03 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB611326A true GB611326A (en) | 1948-10-28 |
Family
ID=26237928
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB10630/46A Expired GB611326A (en) | 1946-04-05 | 1946-04-05 | Improvements in or relating to guide vanes for axial-flow turbines and compressors |
Country Status (5)
Country | Link |
---|---|
US (1) | US2605997A (en) |
BE (1) | BE487115A (en) |
CH (1) | CH257532A (en) |
FR (1) | FR944756A (en) |
GB (1) | GB611326A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2654566A (en) * | 1950-02-11 | 1953-10-06 | A V Roe Canada Ltd | Turbine nozzle guide vane construction |
US2932485A (en) * | 1954-10-01 | 1960-04-12 | United Aircraft Corp | Stator construction |
US2999670A (en) * | 1955-10-18 | 1961-09-12 | Rolls Royce | Stator construction for rotary fluid machine |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2915280A (en) * | 1957-04-18 | 1959-12-01 | Gen Electric | Nozzle and seal assembly |
NL104794C (en) * | 1957-08-16 | |||
US3072380A (en) * | 1959-02-05 | 1963-01-08 | Dresser Ind | Stator blade carrier assembly mounting |
US3075744A (en) * | 1960-08-16 | 1963-01-29 | United Aircraft Corp | Turbine nozzle vane mounting means |
FR1339521A (en) * | 1966-06-10 | 1963-10-11 | Rolls Royce | Fluid circulation machine |
US3423071A (en) * | 1967-07-17 | 1969-01-21 | United Aircraft Corp | Turbine vane retention |
GB2192233B (en) * | 1986-07-02 | 1990-11-28 | Rolls Royce Plc | A gas turbine engine load transfer structure |
US4861229A (en) * | 1987-11-16 | 1989-08-29 | Williams International Corporation | Ceramic-matrix composite nozzle assembly for a turbine engine |
US5494402A (en) * | 1994-05-16 | 1996-02-27 | Solar Turbines Incorporated | Low thermal stress ceramic turbine nozzle |
US6517313B2 (en) * | 2001-06-25 | 2003-02-11 | Pratt & Whitney Canada Corp. | Segmented turbine vane support structure |
US8096746B2 (en) * | 2007-12-13 | 2012-01-17 | Pratt & Whitney Canada Corp. | Radial loading element for turbine vane |
FR2935430B1 (en) * | 2008-08-26 | 2012-03-09 | Snecma | IMPROVED TURBOMACHINE HIGH-PRESSURE TURBINE, DISPENSER SECTOR AND AIRCRAFT ENGINE |
US9702252B2 (en) * | 2012-12-19 | 2017-07-11 | Honeywell International Inc. | Turbine nozzles with slip joints and methods for the production thereof |
US20140255174A1 (en) * | 2012-12-21 | 2014-09-11 | United Technologies Corporation | Manufacture of full ring strut vane pack |
US9816387B2 (en) * | 2014-09-09 | 2017-11-14 | United Technologies Corporation | Attachment faces for clamped turbine stator of a gas turbine engine |
EP3763917A1 (en) * | 2019-07-08 | 2021-01-13 | MTU Aero Engines GmbH | Guide blade segment with support section rib |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB191016889A (en) * | 1910-07-15 | 1910-10-20 | James Howden | Improvements in Means for Fixing Blades in Turbines. |
US2402418A (en) * | 1943-01-20 | 1946-06-18 | Westinghouse Electric Corp | Turbine apparatus |
US2427244A (en) * | 1944-03-07 | 1947-09-09 | Gen Electric | Gas turbine |
-
0
- BE BE487115D patent/BE487115A/xx unknown
-
1946
- 1946-04-05 GB GB10630/46A patent/GB611326A/en not_active Expired
-
1947
- 1947-01-31 CH CH257532D patent/CH257532A/en unknown
- 1947-02-10 US US727520A patent/US2605997A/en not_active Expired - Lifetime
- 1947-04-05 FR FR944756D patent/FR944756A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2654566A (en) * | 1950-02-11 | 1953-10-06 | A V Roe Canada Ltd | Turbine nozzle guide vane construction |
US2932485A (en) * | 1954-10-01 | 1960-04-12 | United Aircraft Corp | Stator construction |
US2999670A (en) * | 1955-10-18 | 1961-09-12 | Rolls Royce | Stator construction for rotary fluid machine |
Also Published As
Publication number | Publication date |
---|---|
BE487115A (en) | |
US2605997A (en) | 1952-08-05 |
FR944756A (en) | 1949-04-14 |
CH257532A (en) | 1948-10-15 |
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