US3112557A - Turbine and compressor blades - Google Patents

Turbine and compressor blades Download PDF

Info

Publication number
US3112557A
US3112557A US789829A US78982959A US3112557A US 3112557 A US3112557 A US 3112557A US 789829 A US789829 A US 789829A US 78982959 A US78982959 A US 78982959A US 3112557 A US3112557 A US 3112557A
Authority
US
United States
Prior art keywords
bores
billet
bore
blade
overlapping
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
US789829A
Inventor
Kent Nelson Hector
Eccles George Oswald
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Application granted granted Critical
Publication of US3112557A publication Critical patent/US3112557A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • 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
    • 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
    • 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
    • Y10T29/4998—Combined manufacture including applying or shaping of fluent material
    • Y10T29/49988—Metal casting
    • Y10T29/49989—Followed by cutting or removing material

Definitions

  • Such blades may have passageways running axially of the blade for the flow of cooling or heating fluid such as air.
  • these passageways should provide a large scrubbing area that is to say that they should have a large internal wall area to be contacted by the cooling air.
  • This invention has for its object to provide passages through a blade which will in some measure overcome this diificulty and reconcile these conflicting requirements.
  • the method of forming the blade includes (a) Producing a billet,
  • One bore may be open to two others on different sides of itself.
  • the overlapping bores may be of different diameters.
  • the remainder of the process of forming the blade can be by any appropriate method such as one of the methods described in our co-pending U.S.A. applications 689,440, 708,045, 775,638.
  • the overlapping bores are formed by drilling one bore, filling it with a filler material such as metal, drilling a second bore, filling the second bore with filler material such as metal, and then extruding the billet.
  • a filler material such as metal
  • the centres of the bores could be positioned so that in the final blade the centres of the holes lie on the mean camber line of the blade; alternatively, for example, one bore can have its centre on the mean camber line and there can be two other bores overlapping said one bore and having their centres offset from and on opposite sides of the mean camber line and positioned inwardly of the lade with respect to the centre of the said one bore.
  • FIGURE 1 is a side elevation of a billet suitable for the production of a turbine blade embodying the invention
  • FIGURE 2 is a plan of the billet seen in the direction of arrow 2 of FIGURE 1;
  • FIGURES 3 to 7 are plans of the billet corresponding to FIGURE 2 showing steps in the formation of the bores according to the invention. 7
  • FIGURE 8 is a section through an extrusion die
  • FIGURE 9 is a side elevation of a finished blade
  • FIGURE 10 is a section on the line llllil of FIG- URE 9;
  • FIGURES 11 to 14 depict enlarged portions of plans of a billet showing an alternative method of forming bores according to the invention.
  • FIGURES 1 and 2 the billet 10 is shown with a number of holes 11, 12 and 13 bored in it.
  • the holes are circular and may be bored by a conventional mechanical drilling process.
  • the holes 11 and 13 are then filled with filler material 14 and 15 (FIGURE 3) respectively.
  • One filler material which may be used is a mild low carbon steel. Adjacent to bore 11, an overlapping bore 16 is drilled and adjacent to bore 15 an overlapping bore 17 is drilled, as seen in FIGURE 4.
  • the bore 20 is then filled with a mild steel filler 21.
  • the holes 12 are then also filled with mild steel filler.
  • the billet is then extruded through a die 26 of the shape shown in FIGURE 8 so as to cause the bores 11, 12, 13, 16, 17 and 29 to be elongated to substantially elliptical cross-section as shown in FIGURE 10.
  • the billet Before extrusion the billet is preferably nickel plated and the die surface covered with colloidal graphite as described in the application for Letters Patent No. 762,519.
  • the blade is then provided with a root 22, a root platform 23, a cap or tip platform 24 and bores 25 in the root 22 by a method set out in our co-pending patent applications referred to above.
  • the multiple bore 27 produced by the combination of bores ll, 16 and 24) provides a fairly large internal area at the same time maintaining a reasonable wall thickness, even at the extreme edge of the blade.
  • the bore 23 formed by extrusion of bores 13 and 27 provides reasonable internal wall area for a'fiow of coolant but at the same time leaves a satisfactory wall thickness at the edge of the blade.
  • FIGURE 11 is shown a portion of a billet 30 in which are formed three overlapping bores 31, 32 and 33. To remove sharp corners which will result from the extrusion described with reference to FIGURE 10 it is desired to add further bores which overlap bores 31, 32 and 33.
  • this hardened inserts 34, and 36 which are made from a nickel-chrome alloy are inserted in'respective bores 31, 33 and 32 to act as guides for a drill. Two further bores are then drilled having their centres within the overlapping portions of the existing bores and their diameters determined by the arcuate inner portions of the inserts.
  • a method of manufacturing a blade ready for machim ng for an internal combustion turbine engine to provide a plurality of independent passageways running axially of the blade for the passage of a fluid for heat exchange which includes:
  • the cross-section of such bores being initially basically circular, one of the bores being independently open to at least two other bores separate from each other resulting from the distance apart of the centers of said one bore and each of the other bores being less than the sum of the radii of the respective pairs of bores so that they overlap to provide substantial interconnection of the passages formed thereby, and inserting hardened metal inserts of substantially arcuate external shape in the existing three bores, each said insert having a longitudinal, parti-cylinclrical groove of the same radius as the groove in a facing insert in the overlapping bore and said grooves spaced from one another about a common center lying Within the overlapping portions of the bores, and inserting a drill using each pair of insert grooves to guide it to remove metal between the guide grooves remaining after the overlapping holes were drilled; removing the inserts;
  • a method of manufacturing a blade ready for machining for an internal combustion turbine engine to provide a plurality of independent passageways running axially of the blade for the passage of a fluid for heat exchange which includes:
  • the cross-section of such bores being initially basically circular, and the distance apart of the centers of 4 at least two of the bores being less than the sum of the radii of the bores so that the bores overlap to provide substantial interconnection of the passages formed thereby; and inserting hardened metal inserts of substantially arcuate external shape in the existing two overlapping bores, each said insert having a longitudinal, parti-cylindrical groove of the same radius as the groove in the facing insert in the overlapping bore and said grooves spaced from one another about a common center lying within the overlapping portion of the bores, and inserting a drill using the pair of insert grooves to guide it to remove metal between the guide grooves which remained after the overlapped holes were drilled, removing the inserts;

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Dec. 3, 1963 N. H.-KENT EIAL TURBINE AND COMPRESSOR BLADES 2 Sheets-Sheet 1 Filed Jan. 29, 1959 a G F w e F 6 2 Q m 3 4 G 2 2 I. F lll i W X HHHWWEWMIMH M m G nwwwwh w lmm nwww wm H F i m INVENTORS Qefiswz. 'vecc M:
BY bgzkgu ATTORNEYS Dec. 3, 1963 N- H- KENT ETA!- 3,112,557
TURBINE AND COMPRESSOR BLADES Filed Jan. 29, 1959 2 Shee tS-Sheet 2 F. l G. 14
INV ENTORS ATTORNEYS United States Patent 3,112,557 TURBEJE AW CGMPRESSQR BLADES Nelson Hector Kent, Allestree, and George Oswald Eecles, ilarrowford, England, assignors to Rolls-Royce Limited, Barby, England, a British company Filed Ian. 29, 1959, Ser. No. 739,829 (Ilaims priority, appl cation Great Britain Feb. 10, 1958 2 Claims. (Cl. 29-15615) This invention relates to the manufacture of blades for internal combustion turbine engines for example from metals which are resistant to high temperature such as nickel-chrome alloys.
Such blades may have passageways running axially of the blade for the flow of cooling or heating fluid such as air.
It is desirable that these passageways should provide a large scrubbing area that is to say that they should have a large internal wall area to be contacted by the cooling air.
It is also necessary to allow a substantial thickness of material between the walls of the cooling passages and the external blade surface. To reconcile these two requirements may be difficult particularly with holes near the leading and trailing edges of the blades.
This invention has for its object to provide passages through a blade which will in some measure overcome this diificulty and reconcile these conflicting requirements.
According to this invention the method of forming the blade includes (a) Producing a billet,
(b) Drilling a plurality of bores axially of the billet the cross section of such bores being initially basically circular and the distance apart of the centres of at least two of the bores being less than the sum of the radii of the bores so that the bores overlap,
(c) Inserting filler material into the bores,
(d) Extruding the billet in a die with lubrication to produce a blade section of approximately aerodynamic shape the pressure being such as to cause the bores to assume an elongated shape in cross section,
(2) Removing the filler material.
In saying that the two bores overlap we imply that the two bores are open to each other along their sides.
There may be more than two overlapping bores for example one bore may be open to two others on different sides of itself.
The overlapping bores may be of different diameters.
The remainder of the process of forming the blade can be by any appropriate method such as one of the methods described in our co-pending U.S.A. applications 689,440, 708,045, 775,638.
Preferably the overlapping bores are formed by drilling one bore, filling it with a filler material such as metal, drilling a second bore, filling the second bore with filler material such as metal, and then extruding the billet.
If more than two overlapping bores are required the above mentioned process can be repeated, filling each bore before drilling the next.
In order to reduce the possibility of sharp corners being formed further bores can be drilled with their centres in the overlapping portion of the existing bores, and to facilitate this operation hardened inserts can be put into the existing bores to guide the drill.
The centres of the bores could be positioned so that in the final blade the centres of the holes lie on the mean camber line of the blade; alternatively, for example, one bore can have its centre on the mean camber line and there can be two other bores overlapping said one bore and having their centres offset from and on opposite sides of the mean camber line and positioned inwardly of the lade with respect to the centre of the said one bore.
3,112,557 Patented Dec. 3, 1963 An example of this invention is illustrated in the accompanying drawings in which FIGURE 1 is a side elevation of a billet suitable for the production of a turbine blade embodying the invention;
FIGURE 2 is a plan of the billet seen in the direction of arrow 2 of FIGURE 1;
FIGURES 3 to 7 are plans of the billet corresponding to FIGURE 2 showing steps in the formation of the bores according to the invention; 7
FIGURE 8 is a section through an extrusion die;
FIGURE 9 is a side elevation of a finished blade;
FIGURE 10 is a section on the line llllil of FIG- URE 9;
FIGURES 11 to 14 depict enlarged portions of plans of a billet showing an alternative method of forming bores according to the invention.
In FIGURES 1 and 2, the billet 10 is shown with a number of holes 11, 12 and 13 bored in it. The holes are circular and may be bored by a conventional mechanical drilling process. The holes 11 and 13 are then filled with filler material 14 and 15 (FIGURE 3) respectively. One filler material which may be used is a mild low carbon steel. Adjacent to bore 11, an overlapping bore 16 is drilled and adjacent to bore 15 an overlapping bore 17 is drilled, as seen in FIGURE 4.
The bores 16 and 17 are then filfiled with mild steel 18 and 1? respectively as shown in FIGURE 5.
On the side of bore 11 remote from the bore 16 a further bore 20 is drilled, again overlapping the bore 11, as shown in FIGURE 6.
The bore 20 is then filled with a mild steel filler 21.
The holes 12 are then also filled with mild steel filler.
The billet is then extruded through a die 26 of the shape shown in FIGURE 8 so as to cause the bores 11, 12, 13, 16, 17 and 29 to be elongated to substantially elliptical cross-section as shown in FIGURE 10.
Before extrusion the billet is preferably nickel plated and the die surface covered with colloidal graphite as described in the application for Letters Patent No. 762,519.
The blade is then provided with a root 22, a root platform 23, a cap or tip platform 24 and bores 25 in the root 22 by a method set out in our co-pending patent applications referred to above.
It will be seen that the multiple bore 27 produced by the combination of bores ll, 16 and 24) provides a fairly large internal area at the same time maintaining a reasonable wall thickness, even at the extreme edge of the blade. Similarly, the bore 23 formed by extrusion of bores 13 and 27 provides reasonable internal wall area for a'fiow of coolant but at the same time leaves a satisfactory wall thickness at the edge of the blade.
In FIGURE 11 is shown a portion of a billet 30 in which are formed three overlapping bores 31, 32 and 33. To remove sharp corners which will result from the extrusion described with reference to FIGURE 10 it is desired to add further bores which overlap bores 31, 32 and 33.
To do this hardened inserts 34, and 36 which are made from a nickel-chrome alloy are inserted in'respective bores 31, 33 and 32 to act as guides for a drill. Two further bores are then drilled having their centres within the overlapping portions of the existing bores and their diameters determined by the arcuate inner portions of the inserts.
The inserts 34, 35 and 36 are then removed leaving a composite bore 37 as shown in FIGURE 13.
On extrusion the bore 37 is reduced to the shape shown at 37a in FIGURE 14.
We claim:
1. A method of manufacturing a blade ready for machim ng for an internal combustion turbine engine to provide a plurality of independent passageways running axially of the blade for the passage of a fluid for heat exchange which includes:
(a) producing a billet;
(b) drilling a plurality of bores axially of the billet,
the cross-section of such bores being initially basically circular, one of the bores being independently open to at least two other bores separate from each other resulting from the distance apart of the centers of said one bore and each of the other bores being less than the sum of the radii of the respective pairs of bores so that they overlap to provide substantial interconnection of the passages formed thereby, and inserting hardened metal inserts of substantially arcuate external shape in the existing three bores, each said insert having a longitudinal, parti-cylinclrical groove of the same radius as the groove in a facing insert in the overlapping bore and said grooves spaced from one another about a common center lying Within the overlapping portions of the bores, and inserting a drill using each pair of insert grooves to guide it to remove metal between the guide grooves remaining after the overlapping holes were drilled; removing the inserts;
(c) inserting filler material into the bores;
(d) extruding the billet in a die with lubrication to produce a blade section of approximately aerodynamic shape the pressure being such as to cause each of the bores to assume an elongated shape in crosssection; and
(e) removing the filler material from all of the bores.
2. A method of manufacturing a blade ready for machining for an internal combustion turbine engine to provide a plurality of independent passageways running axially of the blade for the passage of a fluid for heat exchange which includes:
(a) producing a billet;
(b) drilling a plurality of bores axially of the billet,
the cross-section of such bores being initially basically circular, and the distance apart of the centers of 4 at least two of the bores being less than the sum of the radii of the bores so that the bores overlap to provide substantial interconnection of the passages formed thereby; and inserting hardened metal inserts of substantially arcuate external shape in the existing two overlapping bores, each said insert having a longitudinal, parti-cylindrical groove of the same radius as the groove in the facing insert in the overlapping bore and said grooves spaced from one another about a common center lying within the overlapping portion of the bores, and inserting a drill using the pair of insert grooves to guide it to remove metal between the guide grooves which remained after the overlapped holes were drilled, removing the inserts;
(c) inserting filler material into the bores;
(d) extruding the billet in a die with lubrication to produce a blade section of approximately aerodynamic shape the pressure being such as to cause each of the bores to assume an elongated shape in crosssection; and V (e) removing the filler material from all of the bores.
References Qited in the file of this patent UNITED STATES PATENTS FOREIGN PATENTS Australia Apr. 17, 1958 Canada Nov. 1, 1955 Germany Sept. 9, 1941 Great Britain Aug. 22, 1956 OTHER REFERENCES Hot Turbine, Flight Magazine, pages 293 and 294, volume 69, No. 2460, Mar. 16, 1956.

Claims (1)

1. A METHOD OF MANUFACTURING A BLADE READY FOR MACHINING FOR AN INTERNAL COMBUSTION TURBINE ENGINE TO PROVIDE A PLURALITY OF INDEPENDENT PASSAGEWAYS RUNNING AXIALLY OF THE BLADE FOR THE PASSAGE OF A FLUID FOR HEAT EXCHANGE WHICH INCLUDES: (A) PRODUCING A BILLET; (B) DRILLING A PLURALITY OF BORES AXIALLY OF THE BILLET, THE CROSS-SECTION OF SUCH BORES BEING INITIALLY BASICALLY CIRCULAR, ONE OF THE BORES BEING INDEPENDENTLY OPEN TO AT LEAST TWO OTHER BORES SEPARATE FROM EACH OTHER RESULTING FROM THE DISTANCE APART OF THE CENTERS OF SAID ONE BORE AND EACH OF THE OTHER BORES BEING LESS THAN THE SUM OF THE RADII OF THE RESPECTIVE PAIRS OF BORES SO THAT THEY OVERLAP TO PROVIDE SUBSTANTIAL INTERCONNECTION OF THE PASSAGES FORMED THEREBY, AND INSERTING HARDENED METAL INSERTS OF SUBSTANTIALLY ARCUATE EXTERNAL SHAPE IN THE EXISTING THREE BORES, EACH SAID INSERT HAVING A LONGITUDINAL, PARTI-CYLINDRICAL GROOVE OF THE SAME RADIUS AS THE GROOVE IN A FACING INSERT IN THE OVERLAPPING BORE AND SAID GROOVES SPACED FROM ONE ANOTHER ABOUT A COMMON CENTER LYING WITHIN THE OVERLAPPING PORTIONS OF THE BORES, AND INSERTING A DRILL USING EACH PAIR OF INSERT GROOVES TO GUIDE IT TO REMOVE METAL BETWEEN THE GUIDE GROOVES REMAINING AFTER THE OVERLAPPING HOLES WERE DRILLED; REMOVING THE INSERTS; (C) INSERTING FILLER MATERIAL INTO THE BORES; (D) EXTRUDING THE BILLET IN A DIE WITH LUBRICATION TO PRODUCE A BLADE SECTION OF APPROXIMATELY AERODYNAMIC SHAPE THE PRESSURE BEING SUCH AS TO CAUSE EACH OF THE BORES TO ASSUME AN ELONGATED SHAPE IN CROSSSECTION; AND (E) REMOVING THE FILLER MATERIAL FROM ALL OF THE BORES.
US789829A 1958-02-10 1959-01-29 Turbine and compressor blades Expired - Lifetime US3112557A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3112557X 1958-02-10

Publications (1)

Publication Number Publication Date
US3112557A true US3112557A (en) 1963-12-03

Family

ID=10921954

Family Applications (1)

Application Number Title Priority Date Filing Date
US789829A Expired - Lifetime US3112557A (en) 1958-02-10 1959-01-29 Turbine and compressor blades

Country Status (1)

Country Link
US (1) US3112557A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2013622A (en) * 1932-03-24 1935-09-03 Parsons C A & Co Ltd Method of making turbine blades
US2047555A (en) * 1933-05-31 1936-07-14 Parsons & Co Ltd C A Manufacture of hollow turbine blades
US2220420A (en) * 1938-02-08 1940-11-05 Bbc Brown Boveri & Cie Means for cooling machine parts
DE710289C (en) * 1938-02-08 1941-09-09 Bbc Brown Boveri & Cie Blade with a device for the formation of a boundary layer protecting against high temperatures and a method for producing this blade
US2363085A (en) * 1943-11-29 1944-11-21 Richard T Roye Guide bushing for drills
CA517991A (en) * 1955-11-01 A. Ekman Sven Method of manufacturing rock drill steel
GB755610A (en) * 1953-04-30 1956-08-22 Henry Wiggin And Company Ltd Improvements in the manufacture of turbine blades
US2836884A (en) * 1954-04-29 1958-06-03 Int Nickel Co Production of hollow metal articles
US2975509A (en) * 1956-05-07 1961-03-21 Cefilac Methods of extruding metals
US3014692A (en) * 1956-12-04 1961-12-26 Int Nickel Co Gas turbine blades

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA517991A (en) * 1955-11-01 A. Ekman Sven Method of manufacturing rock drill steel
US2013622A (en) * 1932-03-24 1935-09-03 Parsons C A & Co Ltd Method of making turbine blades
US2047555A (en) * 1933-05-31 1936-07-14 Parsons & Co Ltd C A Manufacture of hollow turbine blades
US2220420A (en) * 1938-02-08 1940-11-05 Bbc Brown Boveri & Cie Means for cooling machine parts
DE710289C (en) * 1938-02-08 1941-09-09 Bbc Brown Boveri & Cie Blade with a device for the formation of a boundary layer protecting against high temperatures and a method for producing this blade
US2363085A (en) * 1943-11-29 1944-11-21 Richard T Roye Guide bushing for drills
GB755610A (en) * 1953-04-30 1956-08-22 Henry Wiggin And Company Ltd Improvements in the manufacture of turbine blades
US2836884A (en) * 1954-04-29 1958-06-03 Int Nickel Co Production of hollow metal articles
US2975509A (en) * 1956-05-07 1961-03-21 Cefilac Methods of extruding metals
US3014692A (en) * 1956-12-04 1961-12-26 Int Nickel Co Gas turbine blades

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly

Similar Documents

Publication Publication Date Title
US2013622A (en) Method of making turbine blades
DE60315374T2 (en) Hybrid process for producing a compressor wheel on titanium
US4883404A (en) Gas turbine vanes and methods for making same
CN102205488A (en) Method for processing hole in split-sleeve cold extrusion manner
JP5010911B2 (en) Extrusion die manufacturing method and electric discharge machining electrode used therefor
US10099276B2 (en) Method and assembly for forming components having an internal passage defined therein
BR102018004502B1 (en) METHOD FOR PRODUCING A BRUCT OF LONG CARTRIDGE CASE AND PUNCTURES AND DIE KIT
US1996850A (en) Method of making propeller blades
US3112557A (en) Turbine and compressor blades
US2891307A (en) Method of hot working heat-resistant metal articles
US2512264A (en) Method of making propeller blades
US1928504A (en) Cooled nozzle segment for combustion gas turbines
US3222764A (en) Method of making articles having base layers and integral fins projecting therefrom
GB855684A (en) Improved method of manufacturing blades for gas turbines
US2040640A (en) Hollow turbine blade
US2740519A (en) Process and apparatus for forging pistons or the like
US2312095A (en) Method of making hollow propellers
US2985953A (en) Manufacture of blades of internal combustion turbine engines
US2308344A (en) Method of making airplane propellers
US3058202A (en) Method of making hollow blades for compressors, turbines, and the like
US2487860A (en) Method of fabricating propeller blades
GB868989A (en) Improved method for the production of blades for gas turbines or compressors
US3635070A (en) Method of working cellular material
US3039178A (en) Manufacture by extrusion of turbine engine blades
US2972182A (en) Turbine and compressor blades