GB790895A - Improvements relating to axial-flow compressor or turbine stator vane assemblies - Google Patents
Improvements relating to axial-flow compressor or turbine stator vane assembliesInfo
- Publication number
- GB790895A GB790895A GB1825356A GB1825356A GB790895A GB 790895 A GB790895 A GB 790895A GB 1825356 A GB1825356 A GB 1825356A GB 1825356 A GB1825356 A GB 1825356A GB 790895 A GB790895 A GB 790895A
- Authority
- GB
- United Kingdom
- Prior art keywords
- tenons
- vane
- turbine stator
- tenon
- pair
- 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)
Abstract
790,895. Compressor and turbine stator vane assemblies. GENERAL MOTORS CORPORATION. June 13, 1956, No. 18253/56. Class 110 (3). An axial-flow compressor or turbine stator vane assembly comprises a pair of arcuate, radially-spaced concentric shroud members 10, 12 having openings receiving tenons 48, 50 at opposite ends of the vanes, the tenons forming at least in part a continuation of the aerofoil vane shape. Each opening is so shaped that its wall is partly relieved from the associated tenon but contacts it sufficiently to hold the vane in fixed angular position. The outer arcuate member 10 is of channel section with axially-extending flanges, and the inner member 12 comprises a pair of channel section members one within the other. The tenons 48 and 50 are formed by removing the leading and trailing edge portions at the two ends of the vane. An opening 64 in the outer arcuate member 10 for receiving the tenon 48 is shown in Fig. 5, and comprises a straight wall 68, a pair of end walls 70, 72 at right angles thereto, and a curved wall 66, the tenon contacting the opening at three points 74, 76 and 78. The radius of curvature of the curved wall 66 is greater than that of the convex blade surface 56. The tenons may be secured either by brazing or by upsetting.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US300576A US2856118A (en) | 1952-07-24 | 1952-07-24 | Blading assembly |
| GB1825356A GB790895A (en) | 1956-06-13 | 1956-06-13 | Improvements relating to axial-flow compressor or turbine stator vane assemblies |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1825356A GB790895A (en) | 1956-06-13 | 1956-06-13 | Improvements relating to axial-flow compressor or turbine stator vane assemblies |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB790895A true GB790895A (en) | 1958-02-19 |
Family
ID=10109286
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1825356A Expired GB790895A (en) | 1952-07-24 | 1956-06-13 | Improvements relating to axial-flow compressor or turbine stator vane assemblies |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB790895A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110781573A (en) * | 2019-08-13 | 2020-02-11 | 中国航发贵阳发动机设计研究所 | Reverse design method for rotor blade of aircraft engine |
-
1956
- 1956-06-13 GB GB1825356A patent/GB790895A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110781573A (en) * | 2019-08-13 | 2020-02-11 | 中国航发贵阳发动机设计研究所 | Reverse design method for rotor blade of aircraft engine |
| CN110781573B (en) * | 2019-08-13 | 2023-11-10 | 中国航发贵阳发动机设计研究所 | Mapping design method for aero-engine rotor blade |
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