US3700418A - Cooled airfoil and method of making it - Google Patents

Cooled airfoil and method of making it Download PDF

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Publication number
US3700418A
US3700418A US879094A US3700418DA US3700418A US 3700418 A US3700418 A US 3700418A US 879094 A US879094 A US 879094A US 3700418D A US3700418D A US 3700418DA US 3700418 A US3700418 A US 3700418A
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United States
Prior art keywords
vane
sheet
pits
pores
transpiration
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
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US879094A
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English (en)
Inventor
Thomas H Mayeda
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Motors Liquidation Co
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General Motors Corp
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Filing date
Publication date
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Publication of US3700418A publication Critical patent/US3700418A/en
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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
    • F01D5/182—Transpiration cooling
    • F01D5/183—Blade walls being porous
    • 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
    • F01D5/182—Transpiration cooling
    • F01D5/184—Blade walls being made of perforated sheet laminae
    • 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
    • Y10T29/496—Multiperforated metal article making
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12361—All metal or with adjacent metals having aperture or cut
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12389—All metal or with adjacent metals having variation in thickness
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12479—Porous [e.g., foamed, spongy, cracked, etc.]

Definitions

  • pores are produced by photoetching pits from the outer and inner faces of the outer metal layer of the vane wall, the pits being offset so that their intersection has an axis at an acute angle to the surface of the vane, with the result that the air emitted flows generally with the direction of flow past the vane rather than transverse to the direction of flow.
  • DESCRIPTION My invention relates to improvements in turbine vanes and blades and other such devices which are protected from high temperature gas by discharge of a cooling gas through numerous pores distributed over the surface of the vane or the like. This mode of cooling is referred to as transpiration cooling.
  • My invention is particularly adapted to transpiration cooled vanes and blades of the general sort described in prior patent applications, of common ownership with this application, as follows: Bratkovich and Meginnis, Ser. No. 526,207 for LaminatedPorous Metal, filed Feb. 9, 1966; Pat. No. 3,584,972, Emmerson, Ser. No. 691,834 for Turbine Cooling, filed Dec. 19, 1967; Helms, Ser. No. 707,556 for Turbine Blade, filed Feb. 23, 1968; and Meginnis, Ser. No. 742,900 for Turbine Blade, filed July 5, 1968, Pat. No. 3,619,082.
  • vanes or blades having laminated walls having pores whtich are machined in the surface of the layer by a process such as photoetching to provide numerous outlets for cooling air or other gas from the interior of the vanes or blades.
  • Vanes, blades, or other structures to be protected from hot gas by transpiration cooling will be referred to hereafter in this specification as vanes for conciseness.
  • this is accomplished by angling the pores in the vane facing or outer layer by photoetching pits in from both the outer and inner surfaces of the layer, with the two sets of pits offset so that the intersection between them has an axis substantially inclined to the normal to the surface and so 3,700,418 Patented Oct. 24, 1972 that the gas discharged from the pore is directed largely downstream with respect to the motive fluid flow past the vane.
  • the principal objects of my invention are to improve the efficiency and temperature tolerance of high temperature turbomachinery; to improve the efliciency of transpiration cooled vanes, blades, and other elements of engines; and to provide a simple and elfective means for discharging transpiration cooling air from a vane in a direction largely conforming to the flow past the vane rather than directly transverse to such flow.
  • FIG. 1 is an axonometric view of a transpiration cooled turbine vane.
  • FIG. 2 is a transverse sectional view of a prior art vane, taken on the plane indicated by the line 22 in FIG. 1, illustrating the discharge of cooling air from the outer surface of the prior art vane.
  • FIG. 3 is a view similar to FIG. 2 showing the discharge of transpiration cooling air from a vane in accordance with my invention.
  • FIG. 4 is a greatly enlarged fragment of FIG. 3 illustrating more clearly the nature of the pore formation in the vane wall.
  • FIG. 1 illustrates a hollow tubular member 6 which may be a turbine vane airfoil or the airfoil portion of a turbine blade or might represent some other structure in a high temperature machine such as a turbine.
  • the airfoil 6 is a hollow tubular structure having a formed outer wall 7 perforated by numerous small closely spaced pores 8.
  • this structure as so far described may be similar to those described in the abovementioned patent applications.
  • FIG. 2 is a partial illustration of structure of such a vane in accordance with the prior applications in which the wall 7, which is the outermost layer of the blade wall, is broken by numerous more or less evenly spaced small transpiration air discharge pores 8.
  • FIG. 2 also illustrates an inner layer 10 bonded to the layer 8 and spaced from it by numerous bosses 11, the layer 10 having holes 12 through it through which the cooling air is supplied from the hollow interior 14 of the vane to the pores 8.
  • the laminated structure may have various forms and, so far as the present invention is concerned, the blade wall is not necessarily laminated.
  • the flow of motive fluid such as hot combustion products, for example, is from the leading edge 15 of the vane 6 past both faces of the vane to the trailing edge 16.
  • the outflow of transpiration cooling air is generally perpendicular to the surface of the vane as indicated by the numerous small arrows 18.
  • the vane according to by invention has the structure of the holes in the outer layer 22 such that the air flow from the transpiration cooling pore 23 is at a substantial angle to the normal to the blade surface and is, in general, in a downstream direction consistent with the flow of motive fluid past the blade, as indicated by the small arrows 24.
  • one or more or more additional layers of metal may be provided inside the illustrated layer 22, as described in prior applications, but that is not material to the present invention.
  • the outer sheet, wall, or layer 22 which, for example, may be .010 inch thick, has the pores 23 each defined by a pit 26 extending into the inner surface 27 of the sheet 22 and a pit 28 extending into the outer surface 30 of the sheet.
  • these pits are of a character which is produced by chemical machining, specifically by photoetching, which is the preferred way to form the pits required for transpiration cooling, particularly in refractory metals of the sort used in high temperature machines.
  • the axis or center of the pore 23 made up by pits 26 and 28 may be considered to be on the line 31.
  • the machining of the pores is accomplished by coating the surface with a resist except for small spots indicated by the lines 32, 33, 34, and 36 indicating the boundaries of the clear area on the two surfaces of the sheet.
  • the metal is eaten away beyond the boundaries of the clear spot generally as shown, to provide two roughly hemispherical or hemispheroidal pits which are allowed to grow until they intersect to provide the air hole where the pits merge through which the cooling air flows as indicated by the arrow 38 in FIG. 4
  • the line 33 and 34 are each offset about 0.003 of an inch from the line 31, this being for a sheet 0.010 inch thick.
  • the preferred maximum diameter of the intersection between the two pits is 0.010 to 0.012 inch.
  • the direction of air flow as indicated by arrows 24 or 38 can be as low as 30 with respect to the surface of the sheet 22.
  • the result in operation of an engine is a substantial reduction in interference between the cooling air fiow and the motive fluid and less tendency for the cooling air flow to separate from the surface of the vane.
  • the cooling is improved and the aerodynamic efficiency enhanced.
  • a method of producing a metal sheet having pores distributed over the sheet adapted to flow a gas through the sheet at an actuate angle to the surface of the sheet comprising machining a rounded pit in one surface of the sheet at the location of each pore and machining a rounded pit in the other surface of the sheet offset from but tangentially intersecting each pit in the said one surface so as to provide the pore opening between the intersecting pits directed at an acute angle to the surface of the sheet.
  • a method of producing a transpiration-cooled airfoil comprising forming the exterior of the airfoil from a sheet produced by the method defined in claim 1.
  • a method of producing a transpiration-cooled airfoil comprising producing a sheet by the process recited in claim 1 and thereafter forming the sheet to an airfoil contour.
  • a hollow airfoil having a porous exterior sheet for transpiration cooling of the airfoil by a cooling gas discharged from the interior of the sheet through pores in the sheet to the exterior thereof characterized by array of pores extending through the said sheet; each pore being defined by two tangentially intersecting pits extending into the exterior and interior faces of the sheet, respectively, the pits extending into the interior face being upstream, with reference to the direction to flow past the airfoil, with respect to the pit extending into the exterior face, the opening defined by the intersection between the said pits having an axis directed at an acute angle to the face of the sheet.
  • a hollow airfoil having a porous exterior sheet for transpiration cooling of the airfoil by a cooling gas discharged from the interior of the sheet through pores in the sheet to the exterior thereof characterized by an array of pores extending through the said sheet configured to direct the gas at an acute angle to the surface of the sheet in a direction downstream relative to flow past the airfoil in normal operation, each pore being defined by two tangentially intersecting pits extending inwardly substantially perpendicularly from opposite surfaces of the sheet, the pits having offset centerlines and intersecting at a surface making an acute angle to the surface of the sheet.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • ing And Chemical Polishing (AREA)
US879094A 1969-11-24 1969-11-24 Cooled airfoil and method of making it Expired - Lifetime US3700418A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US87909469A 1969-11-24 1969-11-24

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US (1) US3700418A (enrdf_load_stackoverflow)
JP (1) JPS4824084B1 (enrdf_load_stackoverflow)
FR (1) FR2071653A5 (enrdf_load_stackoverflow)
GB (1) GB1265257A (enrdf_load_stackoverflow)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3819295A (en) * 1972-09-21 1974-06-25 Gen Electric Cooling slot for airfoil blade
US4022542A (en) * 1974-10-23 1977-05-10 Teledyne Industries, Inc. Turbine blade
US4118146A (en) * 1976-08-11 1978-10-03 United Technologies Corporation Coolable wall
US4283844A (en) * 1979-08-16 1981-08-18 Hughes Aircraft Company Method of making battery electrode structure
US4654939A (en) * 1979-04-27 1987-04-07 The Garrett Corporation Foil bearing surfaces and method of making same
US4657482A (en) * 1980-10-10 1987-04-14 Rolls-Royce Plc Air cooling systems for gas turbine engines
US4768700A (en) * 1987-08-17 1988-09-06 General Motors Corporation Diffusion bonding method
US4866826A (en) * 1987-12-22 1989-09-19 Makoto Koide Method of making squeezing roll and squeezing equipment
US5096379A (en) * 1988-10-12 1992-03-17 Rolls-Royce Plc Film cooled components
US5418345A (en) * 1994-02-28 1995-05-23 United Technologies Corporation Method for forming shaped passages
US5419039A (en) * 1990-07-09 1995-05-30 United Technologies Corporation Method of making an air cooled vane with film cooling pocket construction
US5545003A (en) * 1992-02-18 1996-08-13 Allison Engine Company, Inc Single-cast, high-temperature thin wall gas turbine component
US5810552A (en) * 1992-02-18 1998-09-22 Allison Engine Company, Inc. Single-cast, high-temperature, thin wall structures having a high thermal conductivity member connecting the walls and methods of making the same
US6042879A (en) * 1997-07-02 2000-03-28 United Technologies Corporation Method for preparing an apertured article to be recoated
US6126397A (en) * 1998-12-22 2000-10-03 United Technologies Corporation Trailing edge cooling apparatus for a gas turbine airfoil
US6202304B1 (en) * 1994-11-02 2001-03-20 Solomon Shatz Method of making a perforated metal sheet
US6589600B1 (en) * 1999-06-30 2003-07-08 General Electric Company Turbine engine component having enhanced heat transfer characteristics and method for forming same
DE10244199A1 (de) * 2002-09-23 2004-04-01 Alstom (Switzerland) Ltd. Einbringung eines Sekundärfluids in eine transsonische Primärströmung
US6923247B1 (en) * 1998-11-09 2005-08-02 Alstom Cooled components with conical cooling passages
US20090003989A1 (en) * 2007-06-26 2009-01-01 Volker Guemmer Blade with tangential jet generation on the profile
US20090053464A1 (en) * 2007-08-20 2009-02-26 Honeywell International, Inc. Percussion drilled shaped through hole and method of forming
US20100150734A1 (en) * 2007-07-31 2010-06-17 Mitsubishi Heavy Industries, Ltd. Turbine blade
WO2013123006A1 (en) 2012-02-15 2013-08-22 United Technologies Corporation Gas turbine engine component with cusped cooling hole
US20140302278A1 (en) * 2013-04-09 2014-10-09 General Electric Company Components with double sided cooling features and methods of manufacture
JP2015068340A (ja) * 2013-09-26 2015-04-13 ゼネラル・エレクトリック・カンパニイ 低角度の孔を有するエアフォイルおよびその穿孔方法

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS50109577A (enrdf_load_stackoverflow) * 1974-02-06 1975-08-28
US5695659A (en) * 1995-11-27 1997-12-09 United Technologies Corporation Process for removing a protective coating from a surface of an airfoil
US7311497B2 (en) 2005-08-31 2007-12-25 United Technologies Corporation Manufacturable and inspectable microcircuits
US7371049B2 (en) 2005-08-31 2008-05-13 United Technologies Corporation Manufacturable and inspectable microcircuit cooling for blades
GB2439330B (en) * 2006-06-22 2008-09-17 Rolls Royce Plc Aerofoil

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3819295A (en) * 1972-09-21 1974-06-25 Gen Electric Cooling slot for airfoil blade
US4022542A (en) * 1974-10-23 1977-05-10 Teledyne Industries, Inc. Turbine blade
US4118146A (en) * 1976-08-11 1978-10-03 United Technologies Corporation Coolable wall
US4654939A (en) * 1979-04-27 1987-04-07 The Garrett Corporation Foil bearing surfaces and method of making same
US4283844A (en) * 1979-08-16 1981-08-18 Hughes Aircraft Company Method of making battery electrode structure
US4657482A (en) * 1980-10-10 1987-04-14 Rolls-Royce Plc Air cooling systems for gas turbine engines
US4768700A (en) * 1987-08-17 1988-09-06 General Motors Corporation Diffusion bonding method
US4866826A (en) * 1987-12-22 1989-09-19 Makoto Koide Method of making squeezing roll and squeezing equipment
US5096379A (en) * 1988-10-12 1992-03-17 Rolls-Royce Plc Film cooled components
US5419039A (en) * 1990-07-09 1995-05-30 United Technologies Corporation Method of making an air cooled vane with film cooling pocket construction
US5545003A (en) * 1992-02-18 1996-08-13 Allison Engine Company, Inc Single-cast, high-temperature thin wall gas turbine component
US5641014A (en) * 1992-02-18 1997-06-24 Allison Engine Company Method and apparatus for producing cast structures
US5810552A (en) * 1992-02-18 1998-09-22 Allison Engine Company, Inc. Single-cast, high-temperature, thin wall structures having a high thermal conductivity member connecting the walls and methods of making the same
US5924483A (en) * 1992-02-18 1999-07-20 Allison Engine Company, Inc. Single-cast, high-temperature thin wall structures having a high conductivity member connecting the walls and methods of making the same
US6255000B1 (en) 1992-02-18 2001-07-03 Allison Engine Company, Inc. Single-cast, high-temperature, thin wall structures
US6071363A (en) * 1992-02-18 2000-06-06 Allison Engine Company, Inc. Single-cast, high-temperature, thin wall structures and methods of making the same
US6244327B1 (en) 1992-02-18 2001-06-12 Allison Engine Company, Inc. Method of making single-cast, high-temperature thin wall structures having a high thermal conductivity member connecting the walls
US5418345A (en) * 1994-02-28 1995-05-23 United Technologies Corporation Method for forming shaped passages
US6202304B1 (en) * 1994-11-02 2001-03-20 Solomon Shatz Method of making a perforated metal sheet
US6042879A (en) * 1997-07-02 2000-03-28 United Technologies Corporation Method for preparing an apertured article to be recoated
US6923247B1 (en) * 1998-11-09 2005-08-02 Alstom Cooled components with conical cooling passages
US6126397A (en) * 1998-12-22 2000-10-03 United Technologies Corporation Trailing edge cooling apparatus for a gas turbine airfoil
US6589600B1 (en) * 1999-06-30 2003-07-08 General Electric Company Turbine engine component having enhanced heat transfer characteristics and method for forming same
DE10244199A1 (de) * 2002-09-23 2004-04-01 Alstom (Switzerland) Ltd. Einbringung eines Sekundärfluids in eine transsonische Primärströmung
US20090003989A1 (en) * 2007-06-26 2009-01-01 Volker Guemmer Blade with tangential jet generation on the profile
US8152467B2 (en) * 2007-06-26 2012-04-10 Rolls-Royce Deutschland Ltd & Co Kg Blade with tangential jet generation on the profile
US8079815B2 (en) * 2007-07-31 2011-12-20 Mitsubishi Heavy Industries, Ltd. Turbine blade
US20100150734A1 (en) * 2007-07-31 2010-06-17 Mitsubishi Heavy Industries, Ltd. Turbine blade
US7820267B2 (en) * 2007-08-20 2010-10-26 Honeywell International Inc. Percussion drilled shaped through hole and method of forming
US20090053464A1 (en) * 2007-08-20 2009-02-26 Honeywell International, Inc. Percussion drilled shaped through hole and method of forming
WO2013123006A1 (en) 2012-02-15 2013-08-22 United Technologies Corporation Gas turbine engine component with cusped cooling hole
EP2815101A4 (en) * 2012-02-15 2015-12-30 United Technologies Corp GAS TURBINE ENGINE COMPONENT WITH TOP COOLING HOLE
US20140302278A1 (en) * 2013-04-09 2014-10-09 General Electric Company Components with double sided cooling features and methods of manufacture
JP2015068340A (ja) * 2013-09-26 2015-04-13 ゼネラル・エレクトリック・カンパニイ 低角度の孔を有するエアフォイルおよびその穿孔方法
US20150184517A1 (en) * 2013-09-26 2015-07-02 General Electric Company Airfoils with low-angle holes and methods for drilling same
US10316672B2 (en) * 2013-09-26 2019-06-11 General Electric Company Airfoils with low-angle holes and methods for drilling same

Also Published As

Publication number Publication date
FR2071653A5 (enrdf_load_stackoverflow) 1971-09-17
JPS4824084B1 (enrdf_load_stackoverflow) 1973-07-18
GB1265257A (enrdf_load_stackoverflow) 1972-03-01

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