GB619690A - Improvements in or relating to blades and guide-blades for turbines, rotary compressors and the like - Google Patents
Improvements in or relating to blades and guide-blades for turbines, rotary compressors and the likeInfo
- Publication number
- GB619690A GB619690A GB1992646A GB1992646A GB619690A GB 619690 A GB619690 A GB 619690A GB 1992646 A GB1992646 A GB 1992646A GB 1992646 A GB1992646 A GB 1992646A GB 619690 A GB619690 A GB 619690A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- axis
- hyperboloid
- cutters
- blades
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
Landscapes
- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
619.690. Making compressor blades &c. CORBITT, R. W., and ROLLS-ROYCE, Ltd. July 3, 1946, No. 19926. Addition to 568,575. [Classes 83 (ii) and 83 (iii)] [Also in Group XXVI] The method of forming blades for turbines, rotary compressors &c. wherein the blade surfaces are generated by cutters arranged to traverse a conical surface of which the apex is beyond the blade tip and the axis inclined to the radial axis of the blade at such an angle that the generating line of the cone can occupy a position parallel with the blade axis, is modified in that the cutters are traversed over the surface of a hyperboloid with its axis inclined in a like manner and its part of smallest radius beyond the blade tips. As shown in Fig. 1, the concave surface of the blade 12 is generated by cutters traversing the surface of a hyperboloid 16 having its axis 17 inclined to the radial axis of the blade and in the plane generated by the rotation of the trailing edges of the blades, the part 18 of the hyperboloid having the smallest radius being located beyond the tip and equal to about half the axial length of the blade. The cutters 31-34, Fig. 3, are mounted in a tool-head rotatable about the axis 37 of the hyperboloid and are advanced along lines parallel to generating lines of a cone 36 co-axial with the hyperboloid and offset, by an amount a, from the axis of the cone. The cutters are slidably mounted in guideways 35 and are advanced by any suitable gearing, or hydraulically. In generating the convex faces, the hyperboloid has a smaller minimum radius whereby the thickness of the blade diminishes from the root to the tip and towards one or both edges. Tapering of the blade in both radial and axial directions may be produced by using hyperboloids for generating the front and back faces which are asymptotic to cones having different cone angles and generating lines diverging towards the root of the blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1992646A GB619690A (en) | 1946-07-03 | 1946-07-03 | Improvements in or relating to blades and guide-blades for turbines, rotary compressors and the like |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1992646A GB619690A (en) | 1946-07-03 | 1946-07-03 | Improvements in or relating to blades and guide-blades for turbines, rotary compressors and the like |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB619690A true GB619690A (en) | 1949-03-14 |
Family
ID=10137444
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1992646A Expired GB619690A (en) | 1946-07-03 | 1946-07-03 | Improvements in or relating to blades and guide-blades for turbines, rotary compressors and the like |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB619690A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2270348A (en) * | 1992-08-29 | 1994-03-09 | Asea Brown Boveri | Axial-flow turbine. |
| GB2344778A (en) * | 1998-12-18 | 2000-06-21 | Notetry Ltd | Cyclonic separator and fan combination |
| WO2010002294A1 (en) * | 2008-07-04 | 2010-01-07 | Volvo Aero Corporation | A vane for a gas turbine component, a gas turbine component and a gas turbine engine |
-
1946
- 1946-07-03 GB GB1992646A patent/GB619690A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2270348A (en) * | 1992-08-29 | 1994-03-09 | Asea Brown Boveri | Axial-flow turbine. |
| GB2270348B (en) * | 1992-08-29 | 1996-10-30 | Asea Brown Boveri | Axial-flow turbine |
| GB2344778A (en) * | 1998-12-18 | 2000-06-21 | Notetry Ltd | Cyclonic separator and fan combination |
| WO2010002294A1 (en) * | 2008-07-04 | 2010-01-07 | Volvo Aero Corporation | A vane for a gas turbine component, a gas turbine component and a gas turbine engine |
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