GB686807A - Improvements in and relating to blades for compressors and the like - Google Patents
Improvements in and relating to blades for compressors and the likeInfo
- Publication number
- GB686807A GB686807A GB2781850A GB2781850A GB686807A GB 686807 A GB686807 A GB 686807A GB 2781850 A GB2781850 A GB 2781850A GB 2781850 A GB2781850 A GB 2781850A GB 686807 A GB686807 A GB 686807A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- machining
- profile
- root
- tip
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
Abstract
686,807. Making turbine blades. BRITISH THOMSON-HOUSTON CO., Ltd., and FORSLING, B. E. G. Aug. 13, 1951 [Nov. 14, 1950], No. 27818/50. Class 83 (ii). [Also in Group XXVI] A method of making a rotor blade for an axial flow compressor or turbine comprises machining the two surfaces of the blade to a cylindrical contour, each surface being inclined relatively to the other so that the thickness decreases from the root to the tip and the chord width and the camber angle of the blade profile are also reduced from the root to the tip, the blade after machining being twisted so that the desired chord angle is obtained at all radii. The concave surface of the blade is formed by machining a flat plane E, F, H, G on the underside of the blade said plane being slightly inclined towards the convex upper surface of the blade so that the thickness of the leading and trailing edges of the blade remains constant or slightly decreasing from the root to the tip. The blade is next hollowed out on the flat machined underside to the line I, U, K at the root profile and L, V, M at the tip profile leaving small flat portions E, I, L, G at the inlet edge and K, F, H, M at the trailing edge. The flat portions ensure that the position of the chord relative to the blade profile is not altered by the removal of sharp corners after machining. Measurement of the blade twist is facilitated by using a straight edge along these flats. The contour of the convex surface may be made up from two or more circular arcs. After machining the blade by planing or cam-milling and boring, the corners are rounded off to form the blade profile and the blade is twisted by pressing between dies shaped to fit the blade. The blades are preferably twisted cold and heat treated afterwards to relieve internal stresses, the amount of twist being such that the centres of gravity of the blade sections, after twisting, remain approximately on the same radial line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2781850A GB686807A (en) | 1950-11-14 | 1950-11-14 | Improvements in and relating to blades for compressors and the like |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2781850A GB686807A (en) | 1950-11-14 | 1950-11-14 | Improvements in and relating to blades for compressors and the like |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB686807A true GB686807A (en) | 1953-01-28 |
Family
ID=10265792
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2781850A Expired GB686807A (en) | 1950-11-14 | 1950-11-14 | Improvements in and relating to blades for compressors and the like |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB686807A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0112003A1 (en) * | 1982-10-22 | 1984-06-27 | Westinghouse Electric Corporation | Rotor blade form for the first stage of a combustion turbine |
| US4550497A (en) * | 1981-11-16 | 1985-11-05 | United Technologies Corporation | Tool to produce a new angle on a fan blade |
| CN102168687A (en) * | 2011-05-26 | 2011-08-31 | 哈尔滨汽轮机厂有限责任公司 | Compressor first-stage blade with hub diameter of phi 762 |
| CN102950318A (en) * | 2011-08-22 | 2013-03-06 | 钴碳化钨硬质合金公司 | Method for milling blank in production of turbine blade |
| CN113751974A (en) * | 2021-09-29 | 2021-12-07 | 中国航发航空科技股份有限公司 | Machining and forming method of aero-engine blade |
-
1950
- 1950-11-14 GB GB2781850A patent/GB686807A/en not_active Expired
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4550497A (en) * | 1981-11-16 | 1985-11-05 | United Technologies Corporation | Tool to produce a new angle on a fan blade |
| EP0112003A1 (en) * | 1982-10-22 | 1984-06-27 | Westinghouse Electric Corporation | Rotor blade form for the first stage of a combustion turbine |
| AU568313B2 (en) * | 1982-10-22 | 1987-12-24 | Westinghouse Electric Corporation | Turbine blade |
| CN102168687A (en) * | 2011-05-26 | 2011-08-31 | 哈尔滨汽轮机厂有限责任公司 | Compressor first-stage blade with hub diameter of phi 762 |
| CN102168687B (en) * | 2011-05-26 | 2013-03-27 | 哈尔滨汽轮机厂有限责任公司 | Compressor first-stage blade with hub diameter of phi 762 |
| CN102950318A (en) * | 2011-08-22 | 2013-03-06 | 钴碳化钨硬质合金公司 | Method for milling blank in production of turbine blade |
| CN113751974A (en) * | 2021-09-29 | 2021-12-07 | 中国航发航空科技股份有限公司 | Machining and forming method of aero-engine blade |
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