GB833261A - Improvements relating to the manufacture of blades for turbines or compressors - Google Patents

Improvements relating to the manufacture of blades for turbines or compressors

Info

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
Application number
GB59957A
Inventor
Harold William George Hignett
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Henry Wiggin and Co Ltd
Original Assignee
Henry Wiggin and Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Henry Wiggin and Co Ltd filed Critical Henry Wiggin and Co Ltd
Priority to GB59957A priority Critical patent/GB833261A/en
Publication of GB833261A publication Critical patent/GB833261A/en
Expired legal-status Critical Current

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.
GB59957A 1957-01-07 1957-01-07 Improvements relating to the manufacture of blades for turbines or compressors Expired GB833261A (en)

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)

* Cited by examiner, † Cited by third party
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

Cited By (3)

* Cited by examiner, † Cited by third party
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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