GB840873A - Stator vane assemblies for axial-flow compressors or turbines - Google Patents
Stator vane assemblies for axial-flow compressors or turbinesInfo
- Publication number
- GB840873A GB840873A GB25987/58A GB2598758A GB840873A GB 840873 A GB840873 A GB 840873A GB 25987/58 A GB25987/58 A GB 25987/58A GB 2598758 A GB2598758 A GB 2598758A GB 840873 A GB840873 A GB 840873A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wedge
- secured
- tongues
- tongue
- segments
- 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
- 230000000712 assembly Effects 0.000 title 1
- 238000000429 assembly Methods 0.000 title 1
- 210000002105 tongue Anatomy 0.000 abstract 9
- 238000010276 construction Methods 0.000 abstract 1
- 239000012530 fluid Substances 0.000 abstract 1
- 239000002184 metal Substances 0.000 abstract 1
- 239000007787 solid Substances 0.000 abstract 1
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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T24/00—Buckles, buttons, clasps, etc.
- Y10T24/14—Bale and package ties, hose clamps
- Y10T24/1412—Bale and package ties, hose clamps with tighteners
- Y10T24/1414—Wedge
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
840,873. Elastic fluid turbines ; compressors. GENERAL MOTORS CORPORATION. Aug. 13, 1958 [Aug. 13, 1957], No. 25987/58. Class 110 (3). A stator. vane assembly of an axial now compressor or turbine comprises an outer shroud ring, an inner shroud ring and stator vanes connecting the two rings, the assembly being made up of segments which are secured together at the ends of the inner shroud ring portions by a coupling-device which draws together those ends. The device may comprise, Fig. 5, a screw 57 and nut 58 on which are mounted, respectively, wedge members 53, 54 having ramp surfaces 56 which engage with corresponding ramp surfaces 52 on two I-section tongues 51 secured to one segment of the inner shroud member 47 and surfaces ona similar tongue 49 disposed between the tongues 51 and secured to the adjacent segment of the member 47. As the nut is tightened on the screw the wedging action of the members draws the ends of the segments together. In another embodiment, Fig. 10, in which the I-section tongues and the wedging members are of solid, instead of sheet-metal, construction, the wedge 82 is threaded to receive the bolt 84. In a third embodiment, Fig. 8, the opposed ends of two adjacent segments of the inner shroud member 47 carry channel-section tongues 63, 64, respectively, the tongue 64 extending within the tongue 63. The upstanding flanges of each tongue are notched to provide tapered slots 68, 69 which are engaged by a wedge 71. The wedge is drawn into the slots, by a bolt 72 engaging a nut 73, to draw the ends of the segments together. In a fourth embodiment, Fig. 12, also providedwith interfitting tongues, the wedge 99 is tapped to receive the bolt 102. The stator vane assembly is axially located in the casing by circumferential ribs secured to that casing. Keys are secured to the outer shroud ring and engage with the casing and the ribs to secure the assembly against rotation.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US677933A US3026087A (en) | 1957-08-13 | 1957-08-13 | Stator ring assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB840873A true GB840873A (en) | 1960-07-13 |
Family
ID=24720702
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB25987/58A Expired GB840873A (en) | 1957-08-13 | 1958-08-13 | Stator vane assemblies for axial-flow compressors or turbines |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US3026087A (en) |
| GB (1) | GB840873A (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3269702A (en) * | 1964-01-13 | 1966-08-30 | United Aircraft Corp | Nozzle vane assembly |
| US4792277A (en) * | 1987-07-08 | 1988-12-20 | United Technologies Corporation | Split shroud compressor |
| US5299910A (en) * | 1992-01-23 | 1994-04-05 | General Electric Company | Full-round compressor casing assembly in a gas turbine engine |
| GB0318609D0 (en) * | 2003-08-08 | 2003-09-10 | Rolls Royce Plc | An arrangement for mounting a non-rotating component |
| US7008170B2 (en) * | 2004-03-26 | 2006-03-07 | Siemens Westinghouse Power Corporation | Compressor diaphragm with axial preload |
| GB2438858B (en) * | 2006-06-07 | 2008-08-06 | Rolls Royce Plc | A sealing arrangement in a gas turbine engine |
| US7588418B2 (en) * | 2006-09-19 | 2009-09-15 | General Electric Company | Methods and apparatus for assembling turbine engines |
| US7758307B2 (en) * | 2007-05-17 | 2010-07-20 | Siemens Energy, Inc. | Wear minimization system for a compressor diaphragm |
| US11629606B2 (en) * | 2021-05-26 | 2023-04-18 | General Electric Company | Split-line stator vane assembly |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA535509A (en) * | 1957-01-08 | R. Smith Leslie | Segmented stator ring assembly | |
| US2205474A (en) * | 1937-06-22 | 1940-06-25 | Robert A Goeller | Connector |
| US2371801A (en) * | 1943-08-18 | 1945-03-20 | Arthur C Chester | Propeller spinner attaching device |
| US2442182A (en) * | 1945-06-20 | 1948-05-25 | Wurlitzer Co | Piano action |
| US2610786A (en) * | 1946-06-25 | 1952-09-16 | Gen Electric | Axial flow compressor |
| US2693904A (en) * | 1950-11-14 | 1954-11-09 | A V Roe Canada Ltd | Air bleed for compressors |
| US2691538A (en) * | 1951-03-03 | 1954-10-12 | Albert P Clausen | Joint construction for body shells |
| US2801764A (en) * | 1954-12-03 | 1957-08-06 | Luber Finer Inc | Sealing structure |
-
1957
- 1957-08-13 US US677933A patent/US3026087A/en not_active Expired - Lifetime
-
1958
- 1958-08-13 GB GB25987/58A patent/GB840873A/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| US3026087A (en) | 1962-03-20 |
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