US2972806A - Production of turbine or compressor blades - Google Patents

Production of turbine or compressor blades Download PDF

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Publication number
US2972806A
US2972806A US711375A US71137558A US2972806A US 2972806 A US2972806 A US 2972806A US 711375 A US711375 A US 711375A US 71137558 A US71137558 A US 71137558A US 2972806 A US2972806 A US 2972806A
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US
United States
Prior art keywords
billet
holes
blade
section
tapered
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
US711375A
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English (en)
Inventor
Harold W G Hignett
Turner Philip George
Campbell C Horne
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 US2972806A publication Critical patent/US2972806A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21H—MAKING PARTICULAR METAL OBJECTS BY ROLLING, e.g. SCREWS, WHEELS, RINGS, BARRELS, BALLS
    • B21H7/00—Making articles not provided for in the preceding groups, e.g. agricultural tools, dinner forks, knives, spoons
    • B21H7/16—Making articles not provided for in the preceding groups, e.g. agricultural tools, dinner forks, knives, spoons turbine blades; compressor blades; propeller blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • 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

  • the present invention relates to the production of turbine blades and, more particularly, to the production of fluid-cooled turbine blades having cooling passages running therethrough.
  • Figure 1 is a perspective view of one billet as used in accordance with the present invention.
  • Fig. 2 is an end view of this billet
  • Fig. 3 shows the billet of Figure 1 after hot working
  • Fig. 4 is a partial view of the hot worked billet of Fig. 3 after extrusion.
  • Fig. 5 shows the extruded billet of Fig. 4 after machining
  • Fig. 6 shows the extruded billet of Fig. 4 after rolling
  • Fig. 7 shows the air foil section of the final blade proper
  • Fig. 8 shows another billet as used in accordance with the invention which is a variation of the billet of Figure 1;
  • Fig. 9 shows this second billet of Fig. 8 after hot working to uniform section in accordance with the invention.
  • Fig. 10 is a partial view of the worked billet of Fig. 9 after extrusion
  • Figs. 11 and 12 show sections of the extruded second billet of Fig. 10 after machining and rolling, respectively;
  • Fig. 13 depicts a third billet which may be used in accordance with the present invention.
  • Fig. 14 shows the billet of Fig. 13 after hot working
  • Fig. 15 shows a section on the line XV-XV.
  • Fig. 16 shows part of the blade blankextruded from this hot-worked billet.
  • Figs. 17, 18, 19 and 20 are views of still another billet and correspond to Figs. 13 through 16 respectively.
  • the present invention contemplates an improvement in a process for the production of a turbine (or compressor) blade with cooling passages extending longitudinally through it which comprises making or providing filled holes in a billet (or the like) of heat resistant metal, said holes being filled with a material having properties of flow similar to those of the billet, deforming the billet to alter the shape of the filled holes and thereafter removing the filler to leave the holes as the cooling passages.
  • the billet initially tapers lengthwise over at least part of its length and the longitudinal filled holes in it extend through the tapering part and are of uniform cross section throughout their length, the tapering part of the billet is rendered substantially uniform in cross section by hot working, the holes thereupon becoming tapered, and this part of the billet is next extruded through a die of approximately airfoil section.
  • the holes may extend completely through the billet and, therefore, through the root and blade proper formed from the billet; and or they may be blind, i.e., extend only through part of the billet. If they are blind, the billet is preferably extruded with the holes leading, so that the blind part forms the root and holes may subsequently be made in the root to meet those in the blade proper; or the billet may be extruded with the blind part leading and this part may be upset to form a shroud through which holes are made to join those in the blade proper. If the whole billet is extruded, one end should be blind and later be upset to form the root.
  • the filed passages in the extruded bladeproper taper may be rolled so that it tapers in cross-sectional area from the root to the tip, the taper in the holes being thereby reduced or eliminated.
  • this extruded part may be machined so that it tapers in crosssectional area from the root to the tip, the taper in the holes remaining unchanged.
  • various well known machining, profiling, polishing, etc., operations may be performed on the blade blank to produce the final blade.
  • the filler material is removed at any convenient stage following the working operations to provide cooling passages.
  • the initial billet may be of various tapered shapes. Some of these are shown in the accompanying diagrammatic drawings. It should be appreciated, however, that one may roll a tapered oval section to the round or a frusto-cone to oval section provided there is some asymmetry in the transformation. Itis not practicable to roll a circular section to circular section.
  • the billet may be a truncated pyramid or rectangular section as shown at 1 in Figure l and blind holes 2 may be drilled in it parallel to one another and to the axis. There may, for instance, as shown in Fig. 2, be ten holes 2, of which only two are shown in Figure l and these holes are filled.
  • the billet is then rolled to parallelepiped form as shown in Fig. 3 so that the holes taper towards their blind ends.
  • the billet is now partially extruded to form a blade blank 3 of roughly airfoil section and a root blank 4.
  • the root blank 4 is converted to the desired shape, e.g.,- fir-tree, by machining with. or without preliminary forging and holes are then drilled in it to meet the holes in the blade proper.
  • desired shape e.g.,- fir-tree
  • the billet 1 shown in Fig. 8 is of the same shape as that in Fig. l, but the holes 2 in it are parallel to two of its opposed tapered sides. The result is that after conversion of the billet to the parallelepiped form shown in Fig. 9 and partial extrusion to the shape shown in Fig. 10, the billet has holes separated from one another by tapering metal 6.
  • Figs. 11 and 12 are the equivalents of Figs. 5 and 6, respectively, Fig. 11 depicting the results of machining and Fig. 12 illustrating the results of rolling.
  • the billet may taper on only two opposite sides, i.e.,
  • . be a frustum of a wedge as shown in Fig. 13;
  • the hot working then causes the holes 2 to change in cross-seetional shape as well as size as shown in Figs. 14 and 15 and after the extrusion they vary similarly, as shown in Fig. 16.
  • the holes 2 may be drilled from the large, rather than the small end of a billet, as shown in Fig. 17, with the result that after forging and partial extrusion of the billet, the holes vary in cross section size and shape in the ways diagrammatically illustrated by Figs. 18, 19 and 20, respectively.
  • Example I A tapered billet in the form of a frustu m of a wedge, base 2" x 1.65", top 2" x 1", height 2%" is drilled with one hole /2" diameter right through.
  • the billet is made from an alloy of nickel chromium having the composition: carbon 0.1 max, titanium 1.8-3.0, chromium 18-21, aluminum 0.8-2.0, silicon 1.5 max, manganese 1.0 max., iron 5.0 max, cobalt 15-21, nickel balance.
  • the hole is then filled with a filler of iron manganese titanium alloy, composition iron 80%, manganese 10%, titanium 2%.
  • the tapered billet is then rolled at 1100 C.1l60 C. to parallelepiped form of rectangular section 2" x 1 length 3".
  • the circular filled rod at the highly worked end becomes pseudo-elliptical with axes of 0.5" x 0.3".
  • the billet is now partially extruded at 70 tons/ square inch with graphite lubricant at 1140 C.1160 C. to give a blade length of 6", having a blade section of chord 2" maximum thickness normal to the chord of /2".
  • the unextruded root form is parallelepiped of 2" x 1" length l".
  • the filler in the root is /2" diameter while the filler in the blade portion changes from a section near the root of pseudo-elliptical form having axes of /2" X A" to a section near the tip of pseudo-elliptical form ha'ving axes of 0.5" x 0.150".
  • the filler in the blade being in effect of pseudo-conical form.
  • the blade is then leached to remove the filler and machined to finished size with the requisite root fitting. It is to be appreciated that the example treats one hole for convenience only. In practice a plurality of holes would be drilled to give a blade of high Z factor for optimum cooling.
  • Example II A billet is prepared of parallelepiped form at the base, changing to a frustum of a wedge. Total height 2.175" base section 2" x 1.5" height 0.675. The truncated wedge portion is of base section 2" x 1.5" top section 2" x 1" height 1.5".
  • the billet is made in nickel-chromium alloy of the composition given in Example I.
  • Two holes are drilled in the parallelepiped base of 0.175" diameter pitched apart 1.125" such that each hole is on the 1.5" centre line and 0.1875" from the edge. In the wedge portion the holes run parallel with the tapered wall and at the top are pitched apart on the 1" centre line a distance of 0.5.
  • the holes are filled with filler rod of iron, manganese titanium having the composition iron 88%, manganese 10%, titanium 2%.
  • the billet is now rolled at 1100-1160 C. to the parallelepiped form having a section of 1" x 2" length 2.52".
  • the holes in the wedge portion are thereby changed from circular section to pseudo-elliptical section and taper along their length on tapering centre lines.
  • the billet is then partially extruded at 1140-1l60 C. with graphite lubricant to give a blade length of 3%" blade chord of 2 thickness 0.5" the root block is of 1" x 2 section length 1".
  • the filler in the blade tapers and the centre lines of the filler are tapered within a parallel walled blade.
  • the blade is now rolled to taper over a length of with a thickness at the tip of A.
  • the filler now lies on tapering centre lines parallel to the tapering wall of the blade.
  • the filler per se being of substantially uniform section over its length.
  • the blade is then leached and finish machined.
  • heat-resistant metal is used to include austenitic nickel-chromium alloys, including nickel-chro mium-iron and nickel-chromium-cobalt, and cobalt-chromium alloys, including cobalt-chromium-iron alloys, which contain a total of at least about 25% nickel plus chromium, cobalt plus chromium or nickel plus chromium plus cobalt (ie a total of at least about 25 of chromium plus nickel and/or cobalt) in addition to small amounts of aluminum, titanium, molybdenum, tungsten, vanadium, niobium, tantalum, silicon, manganese, Zirconium and boron which may optionally be present, either singly or in combination, in the alloys.
  • Fillers adapted to cooperate with such heat-resistant metal may be fern'tic alloys of iron, manganese and titanium containing from about 5% to about 20% manganese, about 1% to about 10% titanium with the balance essentially iron.
  • Other fillers may be mixtures of ceramic material such as magnesia "and metal such as iron, with the metal being the continuous phase and the ceramic material constituting between about 5% and 25 of the composition by weight.
  • a process for the production of a turbine blade blank which comprises providing a tapered metal billet having a larger cross-sectional area at one end than the other end and having holes of substantially uniform cross-sectional area which are filled With a filler having deformation characteristics similar to the deformation characteristics of the metal of said billet and which extend from one of said ends toward the other, hot working said tapered metal billet in a direction parallel to the direction of said filled holes-to provide a worked billet having a substantially uniform cross section and thereby tapering said filled holes so that said filled holes have a larger cross-sectional area at one end than the other end, deforming the billet of uniform cross-sectional area so produced to provide a turbine blade blank and thereafter removing the filler from the filled holes in said blank to provide tapered cooling passages therein.
  • a process for the production of a turbine blade blank which comprises providing a tapered rectangular metal billet having a larger cross-sectional area at one end than the other end and having substantially longitudinal holes of substantially uniform cross-sectional area which are filled with a filler having deformation characteristics similar to the deformation characteristics of the metal of said billet and which extend from one of said ends toward the other, hot rolling said tapered metal billet in a direction parallel to the direction of said filled holes to provide a rolled billet having a substantially uniform cross section and thereby tapering said filled holes so that said filled holes have a larger cross-sectional area at one end than the other end, extruding the billet of uniform cross-sectional area so produced to provide a turbine blade blank and thereafter removing the filler from the filled holes in said blank to provide tapered cooling passages therein.
  • a process for the production of a turbine blade blank which comprises providing a tapered rounded metal billet having a larger cross-sectional area at one end than the other end and having substantially longitudinal holes of substantially uniform cross-sectional area which are filled with a filler having deformation characten'stics similar to the deformation characteristics of the metal of said billet and which extend from one of said ends toward the other, hot rolling said tapered metal billet in a direction parallel to the direction of said filled holes to provide a rolled billet having a substantially uniform cross section and thereby tapering said filled holes so that said filled holes have a larger cross-sectional area at one end than the other end, extruding the billet of uniform cross-sectional. area so produced to provide a turbine blade blank and thereafter removing the-filler from the filled holes in said blank to provide tapered cooling passages therein.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Agronomy & Crop Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Forging (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US711375A 1957-01-30 1958-01-27 Production of turbine or compressor blades Expired - Lifetime US2972806A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3312/57A GB842114A (en) 1957-01-30 1957-01-30 Improvements relating to the production of turbine or compressor blades

Publications (1)

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US2972806A true US2972806A (en) 1961-02-28

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US711375A Expired - Lifetime US2972806A (en) 1957-01-30 1958-01-27 Production of turbine or compressor blades

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US (1) US2972806A (xx)
BE (1) BE564389A (xx)
CH (1) CH344285A (xx)
DE (1) DE1095634B (xx)
GB (1) GB842114A (xx)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3201856A (en) * 1961-04-20 1965-08-24 Int Nickel Co Process of producing holes with reduced openings
US3301528A (en) * 1964-11-13 1967-01-31 Rolls Royce Aerofoil shaped blade for fluid flow machines
EP0113882A2 (en) * 1982-12-22 1984-07-25 General Electric Company Method for producing an article with a fluid passage
US4625545A (en) * 1985-04-05 1986-12-02 Testrite, Inc. Method and apparatus for detecting leaks
US4726104A (en) * 1986-11-20 1988-02-23 United Technologies Corporation Methods for weld repairing hollow, air cooled turbine blades and vanes
US20100098527A1 (en) * 2008-10-21 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with peripheral energization near the suction side

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1196938B (de) * 1961-04-20 1965-07-15 Wiggin & Co Ltd Henry Verfahren zur Herstellung von Gasturbinen- oder Kompressorenschaufeln mit Laengskanaelen
US4604780A (en) * 1983-02-03 1986-08-12 Solar Turbines Incorporated Method of fabricating a component having internal cooling passages

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1019191A (en) * 1911-04-29 1912-03-05 James C Russell Treating metal articles.
US2628417A (en) * 1949-01-31 1953-02-17 Saint Gobain Method of preparing perforate bodies
GB739499A (en) * 1952-10-01 1955-11-02 Comptoir Ind Etirage Improvements in or relating to the extrusion of metals
GB755610A (en) * 1953-04-30 1956-08-22 Henry Wiggin And Company Ltd Improvements in the manufacture of turbine blades

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE375203C (de) * 1923-05-08 Ewald Menzel Verfahren zur Umformung von Pilgerkoepfen in Nutzwerkstuecke
DE376759C (de) * 1923-06-02 Ewald Menzel Umformung von Pilgerkoepfen
US2217193A (en) * 1937-08-12 1940-10-08 Oxweld Acetylene Co Method of swaging blowpipe nozzles

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1019191A (en) * 1911-04-29 1912-03-05 James C Russell Treating metal articles.
US2628417A (en) * 1949-01-31 1953-02-17 Saint Gobain Method of preparing perforate bodies
GB739499A (en) * 1952-10-01 1955-11-02 Comptoir Ind Etirage Improvements in or relating to the extrusion of metals
GB755610A (en) * 1953-04-30 1956-08-22 Henry Wiggin And Company Ltd Improvements in the manufacture of turbine blades

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3201856A (en) * 1961-04-20 1965-08-24 Int Nickel Co Process of producing holes with reduced openings
US3301528A (en) * 1964-11-13 1967-01-31 Rolls Royce Aerofoil shaped blade for fluid flow machines
EP0113882A2 (en) * 1982-12-22 1984-07-25 General Electric Company Method for producing an article with a fluid passage
EP0113882A3 (en) * 1982-12-22 1986-07-16 General Electric Company Method for producing an article with a fluid passage
US4625545A (en) * 1985-04-05 1986-12-02 Testrite, Inc. Method and apparatus for detecting leaks
US4726104A (en) * 1986-11-20 1988-02-23 United Technologies Corporation Methods for weld repairing hollow, air cooled turbine blades and vanes
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
CH344285A (fr) 1960-01-31
GB842114A (en) 1960-07-20
BE564389A (xx)
DE1095634B (de) 1960-12-22

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