US3014693A - Turbine and compressor blades - Google Patents

Turbine and compressor blades Download PDF

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Publication number
US3014693A
US3014693A US736637A US73663758A US3014693A US 3014693 A US3014693 A US 3014693A US 736637 A US736637 A US 736637A US 73663758 A US73663758 A US 73663758A US 3014693 A US3014693 A US 3014693A
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US
United States
Prior art keywords
blade
holes
passages
billet
turbine
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
US736637A
Other languages
English (en)
Inventor
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
Priority to US839934A priority Critical patent/US3107416A/en
Application granted granted Critical
Publication of US3014693A publication Critical patent/US3014693A/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
    • 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
    • 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
    • B21C23/22—Making metal-coated products; Making products from two or more metals
    • B21C23/24—Covering indefinite lengths of metal or non-metal material with a metal coating
    • B21C23/26—Applying metal coats to cables, e.g. to insulated electric cables
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • 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
    • F01D5/187—Convection cooling
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/24—Manufacture essentially without removing material by extrusion
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to turbine blades and, more particularly, to fluid-cooled turbine blades made by hot Working from heat resistant metal.
  • Another object of the invention is to provide a process for producing a fluid-cooled turbine blade having a special configuration of cooling passages and improved cooling characteristics.
  • FIGURE 1 is a diagrammatical representation of the elevation of a rectangular billet as used in the present invention
  • FIG. 2 depicts a view of the billet of FIGURE 1 from above;
  • FIG. 3 shows a view of the billet of FIGURE 1 from below:
  • FIG. 4 illustrates a section of the billet of FIGURE 1 along line IV--IV;
  • FIG. 5 is a section of the billet of FIGURE 1 along line V-V;
  • FIG. 6 shows a longitudinal section of a blade machined from the billet of FIGURE 1 after partial extrusion in accordance with the present invention
  • FIG. 7 is a view from the tip end of the blade shown in FIG. 6;
  • FIGS. 8, 9 and 10 are sections of the blade shown in FIG. 6 along the lines VIII--VIII, IX-IX and XX, respectively;
  • FIG. 11 is a tip end view similar to FIG. 7 after a further operation in accordance with the invention.
  • the present invention contemplates fluid-cooled turbine blades (including compressor blades) having two sets of cooling passages which merge into each other close to the tip end of the blade and which extend substantially longitudinally, from the base of an integral root through the blade portion proper.
  • the blade portion proper of the novel turbine blade of the present invention is tapered with the tip end thereof having the smallest cross-sectional area of the atent advantageously be arranged in pairs so that each pair (composed of one passage from each set) forms a diamond pattern in longitudinal section normal to the chord of the blade.
  • Each' set of cooling passages advantageously consists of a plurality of cooling passages parallel to the adjacent surface of the blade.
  • the billet 11 is rectangular and is to be converted into a blade with an integral root with cooling passages running through it.
  • two holes 12 are drilled from the tip end par allel' to the sides of the billet through the preselected blade portion and into the preselected root portion as far as the plane XX andtwo smaller holes 13 are drilled from the opposite end to meet theholes 12.
  • four holes 14 are drilled at an inclina tion to the central longitudinal plane from the same end of the billet as the holes 12, these holes also terminating at the plane XX.
  • four more holes 15, similarly terminating at the plane X--X are drilled from the same end starting from the same points as the holes 14 but oppositely inclined to the central plane.
  • four holes 16 of smaller diameter are drilled from the root end to meet the holes 14 and are also inclined to the central plane.
  • four holes 17, starting from the same points as the holes 16 but oppositely inclined to the holes 16 are drilled to meet the holes 15.
  • the true length of the holes 15 is shown by the line A in FIG. 5.
  • All the holes are filled with filler material and the billet is then partly extruded through a die of airfoil cross section to form a blank 18 (indicated by dotted lines in FIG. 6) for the blade proper, some of the billet being left unextruded to form a blank 19 for the root.
  • Subsequent operations on the blank 18 may comprise coining to give twist, heat treatment and machining to the final blade form shown at 20.
  • the filler is removed, e.g., by acid leaching, before or after the machining.
  • the single row of passages at the tip, indicated at 14 in FIG. 7, may be converted into a slot 21, as shown in FIG. 11 by machining which may be of the kind known as spark erosion.
  • each passage should be as long as possible but as the initial holes are increased in diameter, their centers are necessarily displaced further'from the edges of the billet and theresultant passages do not lie as. close to the surfaces as is required in many blades. Good cooling can, however, be obtained if the inclinations at which the initial holes are drilled are such that the holes in the two sets are staggered in the manner shown in FIGS. 8 and 9.
  • the present invention is particularly applicable to blades of. gas turbines where the blades are subjected to extremeelevated temperatures and where efiicient cool-. ing isa practical necessity.
  • adequate cooling of integral heat-resistant metal blades is achieved even though the blade design requires a very thin tip, for example, usually not greater than about 0.150 inch as a maximum thickness.
  • heat-resistant metal is used to include austenitic nickel-chromium alloys, including nickel-chromium-iron and nickel-chromium-cobalt alloys, and cobalt-chromium alloys, including cobalt-chromiurn-iron alloys, which contain a total of at least about 25% nickelplus 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
  • nickel plus chromium plus cobalt in addition to small amounts of aluminum, titanium, molybdenum, tungsten, niobium, tantalum, silicon, manganese, zirconium and boron with the balance iron, if any, which may optionally be present in the alloys.
  • These alloys are adapted to be subjected inuse to temperatures up to about 700 C.
  • Such heat-resistant metal may be ferritic 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.
  • These steel filler materials are described and claimed in the Betteridge U.S. application Serial'No. 509,380, now U.S. Patent No. 2,891,307.
  • Other advantageous filler. materials are metal-ceramic mixtures having a continuous metal phase and containing about 5 to about 25 %-ceramic material, e.g., magnesia and the balance metal, e.g., iron.
  • Such metal-ceramic 4. fillers are described and claimed in the Hignett U.S. application Serial No. 472,755, now U.S. Patent No. 2,941,- 281.
  • a structurally integral fluid cooled, heat-resistant metal turbine blade comprising a one-piece joint-free structure having a taperedblade portion structurally integral with a root portion and having a plurality of paired cooling passages extending substantially longitudinally through said root portion and said blade portion, each of said paired cooling passages being positioned in the blade so that the individual members of the pair merge at the tip of said blade and at the bottom of said root, are inclined from each other and the camber plane of said blade and are substantially parallel to the, adjacent surfaces of said blade.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
US736637A 1957-06-07 1958-05-20 Turbine and compressor blades Expired - Lifetime US3014693A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US839934A US3107416A (en) 1958-05-20 1959-09-14 Method of making turbine and compressor blades

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB18195/57A GB844068A (en) 1957-06-07 1957-06-07 Improvements relating to turbine and compressor blades

Publications (1)

Publication Number Publication Date
US3014693A true US3014693A (en) 1961-12-26

Family

ID=10108284

Family Applications (1)

Application Number Title Priority Date Filing Date
US736637A Expired - Lifetime US3014693A (en) 1957-06-07 1958-05-20 Turbine and compressor blades

Country Status (6)

Country Link
US (1) US3014693A (hu)
BE (1) BE568389A (hu)
DE (1) DE1081276B (hu)
FR (1) FR1196738A (hu)
GB (1) GB844068A (hu)
NL (2) NL104493C (hu)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3420502A (en) * 1962-09-04 1969-01-07 Gen Electric Fluid-cooled airfoil
US3989412A (en) * 1974-07-17 1976-11-02 Brown Boveri-Sulzer Turbomachinery, Ltd. Cooled rotor blade for a gas turbine
US5980209A (en) * 1997-06-27 1999-11-09 General Electric Co. Turbine blade with enhanced cooling and profile optimization
US20060263218A1 (en) * 2005-05-23 2006-11-23 Pratt & Whitney Canada Corp. Angled cooling divider wall in blade attachment
US20080286104A1 (en) * 2007-05-18 2008-11-20 Siemens Power Generation, Inc. Near wall cooling for a highly tapered turbine blade
US8740567B2 (en) 2010-07-26 2014-06-03 United Technologies Corporation Reverse cavity blade for a gas turbine engine
EP2853689A1 (de) * 2013-09-25 2015-04-01 Siemens Aktiengesellschaft Anordnung von Kühlkanälen in einer Turbinenschaufel
US11542820B2 (en) 2017-12-06 2023-01-03 General Electric Company Turbomachinery blade and method of fabricating

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015102676A1 (en) * 2013-12-30 2015-07-09 United Technologies Corporation Fan blade with root through holes

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2440127A (en) * 1944-07-31 1948-04-20 Curtiss Wright Corp Art of producing propeller blades
US2514525A (en) * 1944-03-09 1950-07-11 Curtiss Wright Corp Method of producing blade constructions and propeller blades
GB660007A (en) * 1947-07-09 1951-10-31 Georges Bolsezian Improvements relating to turbine rotor blades
GB694241A (en) * 1950-04-18 1953-07-15 Rolls Royce Improvements relating to turbine blades
US2648520A (en) * 1949-08-02 1953-08-11 Heinz E Schmitt Air-cooled turbine blade
US2780435A (en) * 1953-01-12 1957-02-05 Jackson Thomas Woodrow Turbine blade cooling structure
GB768247A (en) * 1955-03-01 1957-02-13 Power Jets Res & Dev Ltd Blades for turbines, compressors and like bladed fluid flow machines
US2787441A (en) * 1952-03-05 1957-04-02 Thompson Prod Inc Hollow turbine bucket
US2848193A (en) * 1953-04-08 1958-08-19 Gen Electric Air cooled turbomachine blading
US2972182A (en) * 1957-02-22 1961-02-21 Rolls Royce Turbine and compressor blades
US2975509A (en) * 1956-05-07 1961-03-21 Cefilac Methods of extruding metals

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1657192A (en) * 1923-03-22 1928-01-24 Belluzzo Giuseppe Wheel for internal-combustion turbines
DE597556C (hu) * 1931-12-29
CH195736A (de) * 1936-11-24 1938-02-15 Alfred Buechi Turbinenrotor mit wenigstens einem Schaufelrad.
US2778601A (en) * 1951-05-28 1957-01-22 Ernst R G Eckert Fluid cooled turbine blade construction

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2514525A (en) * 1944-03-09 1950-07-11 Curtiss Wright Corp Method of producing blade constructions and propeller blades
US2440127A (en) * 1944-07-31 1948-04-20 Curtiss Wright Corp Art of producing propeller blades
GB660007A (en) * 1947-07-09 1951-10-31 Georges Bolsezian Improvements relating to turbine rotor blades
US2648520A (en) * 1949-08-02 1953-08-11 Heinz E Schmitt Air-cooled turbine blade
GB694241A (en) * 1950-04-18 1953-07-15 Rolls Royce Improvements relating to turbine blades
US2787441A (en) * 1952-03-05 1957-04-02 Thompson Prod Inc Hollow turbine bucket
US2780435A (en) * 1953-01-12 1957-02-05 Jackson Thomas Woodrow Turbine blade cooling structure
US2848193A (en) * 1953-04-08 1958-08-19 Gen Electric Air cooled turbomachine blading
GB768247A (en) * 1955-03-01 1957-02-13 Power Jets Res & Dev Ltd Blades for turbines, compressors and like bladed fluid flow machines
US2975509A (en) * 1956-05-07 1961-03-21 Cefilac Methods of extruding metals
US2972182A (en) * 1957-02-22 1961-02-21 Rolls Royce Turbine and compressor blades

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3420502A (en) * 1962-09-04 1969-01-07 Gen Electric Fluid-cooled airfoil
US3989412A (en) * 1974-07-17 1976-11-02 Brown Boveri-Sulzer Turbomachinery, Ltd. Cooled rotor blade for a gas turbine
US5980209A (en) * 1997-06-27 1999-11-09 General Electric Co. Turbine blade with enhanced cooling and profile optimization
US20060263218A1 (en) * 2005-05-23 2006-11-23 Pratt & Whitney Canada Corp. Angled cooling divider wall in blade attachment
US7357623B2 (en) 2005-05-23 2008-04-15 Pratt & Whitney Canada Corp. Angled cooling divider wall in blade attachment
US20080286104A1 (en) * 2007-05-18 2008-11-20 Siemens Power Generation, Inc. Near wall cooling for a highly tapered turbine blade
US7901182B2 (en) * 2007-05-18 2011-03-08 Siemens Energy, Inc. Near wall cooling for a highly tapered turbine blade
US8740567B2 (en) 2010-07-26 2014-06-03 United Technologies Corporation Reverse cavity blade for a gas turbine engine
EP2853689A1 (de) * 2013-09-25 2015-04-01 Siemens Aktiengesellschaft Anordnung von Kühlkanälen in einer Turbinenschaufel
US11542820B2 (en) 2017-12-06 2023-01-03 General Electric Company Turbomachinery blade and method of fabricating

Also Published As

Publication number Publication date
BE568389A (hu)
GB844068A (en) 1960-08-10
DE1081276B (de) 1960-05-05
FR1196738A (fr) 1959-11-25
NL104493C (hu)
NL228237A (hu)

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