US3201856A - Process of producing holes with reduced openings - Google Patents

Process of producing holes with reduced openings Download PDF

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Publication number
US3201856A
US3201856A US188197A US18819762A US3201856A US 3201856 A US3201856 A US 3201856A US 188197 A US188197 A US 188197A US 18819762 A US18819762 A US 18819762A US 3201856 A US3201856 A US 3201856A
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US
United States
Prior art keywords
length
hole
filler body
cross
flowability
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 - Lifetime
Application number
US188197A
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English (en)
Inventor
Keegan Barclay
Roderick C Mackenzie
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.)
Huntington Alloys Corp
Original Assignee
International Nickel Co Inc
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 International Nickel Co Inc filed Critical International Nickel Co Inc
Application granted granted Critical
Publication of US3201856A publication Critical patent/US3201856A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
    • B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
    • B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES, PROFILES OR LIKE SEMI-MANUFACTURED PRODUCTS 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y10T29/49341—Hollow blade with cooling passage
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/4981—Utilizing transitory attached element or associated separate material

Definitions

  • a known kind of process for the production of a blank for a turbine or compressor blade with cooling passages extending longitudinally through it comprises making holes in a billet, filling them with rods of a material having properties of flow similar to those of the billet, deforming the billet to a blank with consequent elongation of the filled holes and finally removing the filler to leave the holes as the cooling passages.
  • the holes are made in the billet by drilling and so are of uniform cross section throughout their length. Normally, such uniformity of cross section is desirable.
  • the tip section is exceptionally thin and in order to obtain a passage of substantial cross section in the main body of the blade, it is necessary to reduce the area of the cross section of the passage in the tip region.
  • Another object of the invention is to provide a novel process for the production of turbine structures having internal passages of non-uniform cross-sectional area.
  • the invention also contemplates providing a novel process for the production of fluid-cooled turbine blades having internal passages of non-uniform cross-sectional area.
  • FIGURES l, 2, 3 and 4 are cross-sectional views of filled metallic masses or billets employed in the process of the present invention; and FIGS. 1A, 2A, 3A and 4A are cross-sectional views of worked structures produced from the masses of FIGS. 1, 2, 3 and 4, respectively, by the use of the process of the present invention.
  • the resistance to deformation of the billet presented by the filler rods is reduced over a length from one end of a billet with the result that under substantially uniform deformation forces the crosssectional area of the deformed filled holes becomes less over that length than over the remaining length of the holes. If the passages should be smaller at the tip, the resistance to deformation usually need be reduced over a short length of filler rod only.
  • the deformation is most conveniently effected by extrusion. If the billet is only partially extruded so as to leave in the extrusion container a length of billet which is to form the root of the blade and the passages should be smaller at the tip, the resistance to deformation of the billet is, of course, reduced at the end that leads during the extrusion. If the billet is extruded as completely as possible so as to provide an extruded product that after removal of a short length of the trailing end is of uniform cross section throughout its length, the resistance to deformation may be reduced from either end of the billet.
  • each filler rod may be drilled to provide an internal cavity concentric with the outer Wall of the rod; or a slot may be cut in each rod from the end; or a length of the rod may be made frusto conical instead of cylindrical.
  • the metal of the billet will fill the resultant cavity and the final pas sage will be reduced in cross section in accordance with the reduction in the cross-sectional area of the filler rod. The extent to which this area can be reduced is limited by the risk of cracking and depends in part upon the composition of the billet.
  • the maximum permissible reduction in area is not more than about 60%.
  • a nickel-chromium-cobalt-molybdenum alloy billet for use at higher service temperature 13.5% to 16% chromium, 18% to 22% cobalt, 4.5% to 5.5% molybdenum
  • the maximum per missible reduction in area is not more than about 35%.
  • the cavity in the filled hole may be filled with a particulate material, e.g., aluminia, the proportion of voids in this material then determining the shape of the final passage.
  • a particulate material may be kept in place by a weld deposit over the end of the hole.
  • the use of a particulate material may be beneficial when the incompletely filled hole is in the root metal and the exclusion of air is desirable to keep irregularities to a minimum.
  • Another way of reducing the resistance to deformation is to use a length of filler rod of weaker material than that of the remaining length.
  • the latter length may be an iron-manganese-titanium alloy as described in US. Patent No. 2,941,281 and the former length may be mild steel.
  • FIGURES 1 to 4 show billets 11 of heat resistant metal having at least one hole 12 of uniform cross-sectional area extending therethrough which hole 12 is at least partly filled with filler body 13.
  • Filler body 13 is positioned in hole 12 so that an ascertained zone of enhanced flowability is present in hole 12.
  • the ascertained zone of enhanced flowability is provided by void 14 in filler body 13 extending from leading end 15.
  • passage 16 of non-uniform cross-sectional area in turbine blade 17 is produced as shown in FIG. 1A.
  • void 14 provided by employing partly tapered filler body 13 is the zone of enhanced flowability.
  • the passageway in the root closes to.( d FIGFZA) and is smaller than the original; hole,
  • This closure is brought about by the flow of rnetal'near the radius of the extrusion die. This is useful where the finished root shape 17 is very slim.
  • the zone of enhanced flowability can be a non-compacted mass of ceramic particles'19 as shown in FIG. '3 or it can be a relatively weak metalbody, e.g.,*rnild steel, such as shownt at in FIG. 4. *The configuration of passage 16 in worked-metal 21 resulting from the extrusion of billets 11 of FIGS. 3 and 4 and removal of the filler body therefrom are shown in FIGS.- 3A and- 4A, respectively.
  • the present invention is particularly applicable to the production of hollow'fluid cooled turbine blades
  • heat resistant metal is used to include austenitic nickel-chromium alloys, including 'nickel-chromium iron and nickel-chromium -cobalt and cobalt-chr'omium alloys, including cobalt-tehromium-iron alloys, which .con tain a total of at-least about nickel plus chromium, cobalt plus chromium or nickel plus chromium plus cobalt (i.e.,a total of at least about 25 of chromium plus nickel and/or cobalt) in addition to small amounts of tantalum, silicon, manganese, zirconium and boron which may optionally be present 'in the alloys.
  • austenitic nickel-chromium alloys including 'nickel-chromium iron and nickel-chromium -cobalt and cobalt-chr'omium alloys, including cobalt-tehromium-iron alloys, which .con tain a total of at-l
  • alloys if any, is iron.
  • These alloys are adapted stantially uniform deformation'forces to induce flow of I said metallic mass and said filler body and thereafter removing said fillerybody from the thus worked metallic mass to open the thus-produced passage of controlled non-uniform cross-sectional area.
  • a processfor producing a worked heat resistant metalobject having a plurality of passages of controlled nonruniformity'of cross-sectional area which comprises providing a billet of heat resistant metal having a plurality 7 aluminum, titanium, molybdenum, tungsten, niobium,
  • the present invention has been describe'd in, conjunction with' preferred embodiments, it is to be Zone of enhanced flowability in each'of said holes and also at least one predetermined zone of flowability less than the flowability of the zone of enhanced flowability in reach of said holes, working-the billet together with said filler body by extrusion to inducev flow of said heat resistant metal ancl said filler body'and thereafter removing said filler body from .the thus-worked heat resistant metal to opeuthe thus-produced passages'of controlled non-uniform cross sectional area V a J 6.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Extrusion Of Metal (AREA)
US188197A 1961-04-20 1962-04-17 Process of producing holes with reduced openings Expired - Lifetime US3201856A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB14323/61A GB934647A (en) 1961-04-20 1961-04-20 Improvements relating to the production of turbine or compressor blades

Publications (1)

Publication Number Publication Date
US3201856A true US3201856A (en) 1965-08-24

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ID=10039121

Family Applications (1)

Application Number Title Priority Date Filing Date
US188197A Expired - Lifetime US3201856A (en) 1961-04-20 1962-04-17 Process of producing holes with reduced openings

Country Status (3)

Country Link
US (1) US3201856A (fr)
BE (1) BE616751A (fr)
GB (1) GB934647A (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3890685A (en) * 1973-06-06 1975-06-24 Bayer Ag Method for manufacturing hollow screws for heat exchangers
US4639568A (en) * 1984-07-13 1987-01-27 Ex-Cell-O Corporation Apparatus and method for finishing fuel injector spray tips using EDM
US20100098527A1 (en) * 2008-10-21 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with peripheral energization near the suction side

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2047555A (en) * 1933-05-31 1936-07-14 Parsons & Co Ltd C A Manufacture of hollow turbine blades
US2093775A (en) * 1931-10-29 1937-09-21 Thompson Prod Inc Method of making valves
US2948052A (en) * 1956-06-30 1960-08-09 Teves Kg Alfred Method of manufacturing hollow poppet valves for internal combustion engines
US2970368A (en) * 1957-05-23 1961-02-07 Int Nickel Co Hollow turbine or compressor blades
US2972806A (en) * 1957-01-30 1961-02-28 Int Nickel Co Production of turbine or compressor blades
US2986806A (en) * 1957-01-21 1961-06-06 Int Nickel Co Production of turbine or compressor blades
US3044153A (en) * 1956-10-12 1962-07-17 Rolls Royce Manufacture by extrusion of turbine engine blades

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2093775A (en) * 1931-10-29 1937-09-21 Thompson Prod Inc Method of making valves
US2047555A (en) * 1933-05-31 1936-07-14 Parsons & Co Ltd C A Manufacture of hollow turbine blades
US2948052A (en) * 1956-06-30 1960-08-09 Teves Kg Alfred Method of manufacturing hollow poppet valves for internal combustion engines
US3044153A (en) * 1956-10-12 1962-07-17 Rolls Royce Manufacture by extrusion of turbine engine blades
US2986806A (en) * 1957-01-21 1961-06-06 Int Nickel Co Production of turbine or compressor blades
US2972806A (en) * 1957-01-30 1961-02-28 Int Nickel Co Production of turbine or compressor blades
US2970368A (en) * 1957-05-23 1961-02-07 Int Nickel Co Hollow turbine or compressor blades

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3890685A (en) * 1973-06-06 1975-06-24 Bayer Ag Method for manufacturing hollow screws for heat exchangers
US4639568A (en) * 1984-07-13 1987-01-27 Ex-Cell-O Corporation Apparatus and method for finishing fuel injector spray tips using EDM
US20100098527A1 (en) * 2008-10-21 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with peripheral energization near the suction side
US8834116B2 (en) * 2008-10-21 2014-09-16 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with peripheral energization near the suction side

Also Published As

Publication number Publication date
GB934647A (en) 1963-08-21
BE616751A (fr) 1962-08-16

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