GB833261A - Improvements relating to the manufacture of blades for turbines or compressors - Google Patents
Improvements relating to the manufacture of blades for turbines or compressorsInfo
- Publication number
- GB833261A GB833261A GB59957A GB59957A GB833261A GB 833261 A GB833261 A GB 833261A GB 59957 A GB59957 A GB 59957A GB 59957 A GB59957 A GB 59957A GB 833261 A GB833261 A GB 833261A
- Authority
- GB
- United Kingdom
- Prior art keywords
- billet
- molybdenum
- nickel
- alloy
- blade
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C23/00—Extruding metal; Impact extrusion
- B21C23/02—Making uncoated products
- B21C23/04—Making uncoated products by direct extrusion
- B21C23/14—Making other products
- B21C23/16—Making turbo blades or propellers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
833,261. Turbine and compressor blades. WIGGIN & CO. Ltd., H. Dec. 31, 1957 [Jan. 7, 1957], No. 599/57. Class 110 (3). [Also in Groups II and XXII] A turbine or compressor blade comprises a matrix 1 of a creep- and heat-resisting alloy surrounding and stiffened by rods 2 of molybdenum or a molybdenum-base alloy. The matrix alloy may have a base of nickel and chromium, or nickel, chromium and cobalt, hardened by aluminium and titanium. The blade is manufactured by inserting the rods in holes drilled in a billet of the matrix alloy, the billet being extruded through a die. The blade shown is formed from a billet 1¢ inches square of an alloy having a composition 58% nickel, 20% chromium, 16% cobalt, 0.08% carbon and small amounts of aluminium, titanium, manganese, silicon and iron, the billet being drilled with blind holes each # inch in diameter, the inside surfaces of the holes being plated with nickel. The molybdenum rods 2 are initially 3/32 inch in diameter, are coated with gold, then palladium, and finally nickel and are then inserted into the holes, being sealed in position by a nickel weld on the end of the billet. The billet is heated for 40 minutes at 1150‹ C. and then extruded to form a blade section 1¢ inches in chord width. The blade is heat treated by heating for 4 hours at 1150‹ C., cooled in air, heated for 8 hours at 1080‹ C. and then cooled in air, this treatment causing diffusion between the various layers and good bonding between the matrix and the molybdenum rods. If the blade is to be provided with cooling passages 3, some of the holes drilled in the billet may be filled with a filler, e.g. an iron, manganese, titanium alloy, which is finally removed. The billet may be only partially extruded through a die so as to leave a portion from which the root may be formed. The holes forming the cooling fluid passages may extend completely through the billet. The stiffening rods are preferably a molybdenum base alloy containing at least 80% molybdenum, e.g. an alloy containing 99.5% molybdenum and 0.5% titanium. Other such alloys contain a small amount of zirconium, vanadium or niobium.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB59957A GB833261A (en) | 1957-01-07 | 1957-01-07 | Improvements relating to the manufacture of blades for turbines or compressors |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB59957A GB833261A (en) | 1957-01-07 | 1957-01-07 | Improvements relating to the manufacture of blades for turbines or compressors |
Publications (1)
Publication Number | Publication Date |
---|---|
GB833261A true GB833261A (en) | 1960-04-21 |
Family
ID=9707214
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB59957A Expired GB833261A (en) | 1957-01-07 | 1957-01-07 | Improvements relating to the manufacture of blades for turbines or compressors |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB833261A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3248082A (en) * | 1965-08-19 | 1966-04-26 | Whitfield Lab Inc | Reinforced gas-turbine blade or vane |
GB2142387A (en) * | 1983-07-02 | 1985-01-16 | Rolls Royce | An aerofoil for a gas turbine engine |
US4604780A (en) * | 1983-02-03 | 1986-08-12 | Solar Turbines Incorporated | Method of fabricating a component having internal cooling passages |
-
1957
- 1957-01-07 GB GB59957A patent/GB833261A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3248082A (en) * | 1965-08-19 | 1966-04-26 | Whitfield Lab Inc | Reinforced gas-turbine blade or vane |
US4604780A (en) * | 1983-02-03 | 1986-08-12 | Solar Turbines Incorporated | Method of fabricating a component having internal cooling passages |
GB2142387A (en) * | 1983-07-02 | 1985-01-16 | Rolls Royce | An aerofoil for a gas turbine engine |
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