US2956773A - Cooled hollow turbine blades - Google Patents

Cooled hollow turbine blades Download PDF

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Publication number
US2956773A
US2956773A US659375A US65937557A US2956773A US 2956773 A US2956773 A US 2956773A US 659375 A US659375 A US 659375A US 65937557 A US65937557 A US 65937557A US 2956773 A US2956773 A US 2956773A
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US
United States
Prior art keywords
blade
cooling medium
partition
leading edge
passage
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
US659375A
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English (en)
Inventor
Michael J French
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son Ltd
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 D Napier and Son Ltd filed Critical D Napier and Son Ltd
Application granted granted Critical
Publication of US2956773A publication Critical patent/US2956773A/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
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall

Definitions

  • This invention relates to cooled hollow turbine blades. It is known to cool hollow turbine blades by passing a cooling medium, such as relatively cool air, through their hollow interiors, this air taking up heat from the walls of the hollow blades and thereby cooling them. In cooled blades which have hitherto been proposed it has been the usual practice to cause the cooling medium to flow predominantly in the longitudinal direction along the internal surfaces of the blades.
  • a cooling medium such as relatively cool air
  • the cooling medium is caused to flow across the internal surface of the blade adjacent to the leading edge in a direction approximately transverse to the length of the blade.
  • the leading edge of the blade is usually the region that needs the most cooling, and it has been found that by adopting an approximately transverse flow of cooling medium in accordance with the present invention the cooling of the leading edge is considerably improved. While the invention is not dependent upon any particular theory, it is thought that this improvement is due largely to the cooling medium sweeping quickly round the sharp curvature of the internal surface of the blade adjacent to the leading edge and removing the boundary layer of cooling medium from this surface more effectively than is the case when the flow is predominantly in the longitudinal direction.
  • the blade includes an internal member defining a longitudinal passage within the blade through which a cooling medium is passed from the blade root, and this passage has a slit or apertures disposed adjacent the internal surface of the blade in the vicinity of the leading edge and through which the cooling medium emerges from the passage in a direction approximately transverse to the length of the blade.
  • fresh cooling medium can be supplied along practically the whole length of the leading edge, providing substantially uniform cool-ing along this edge.
  • the cooling medium would get progressively hotter as it advanced along the leading edge, and in consequence would provide progressively less effective cooling.
  • the longitudinal passage can be formed in various ways. For instance, it may be bounded on one side by the internal member which in this case will be a partition dividing the hollow interior of the blade chordwise, and on the other side by one flank of the blade, preferably the convex flank.
  • the internal member may have a cross-section such that at least one of its sides is spaced by a small clearance from the adjacent flank of the blade so as to define at least one restricted passage for the flow of cooling medium, thereby ensuring that the cooling medium passes close to the internal surface of the blade on the flank or flanks as well as adjacent to the leading edge.
  • the internal member may be spaced from the flanks of the blade by forming raised pimples or weals thereon which touch the flanks of the blade.
  • the blade has outlet apertures for the cooling medium along its trailing edge, so that when the cooling medium has left the longitudinal chamber in the blade it flows substantially transversely, not only adjacent the leading edge but also across one or both flanks of the blade.
  • the blade instead of cooling medium emerging through the trailing edge of the blade, the blade may be provided with an internal return passage for the cooling medium leading back to the blade root or platform which will be provided with an outlet for the cooling medium.
  • Figure 1 is a perspective view of the blade, with the tip broken aawy to show the internal construction
  • Figure 2 is a cross-section taken on the line II-II in Figure 1;
  • Figure 3 is a fragmentary sectional view taken on the line III-III in Figure 2;
  • Figure 4 is a view, similar to Figure 3, of a modification.
  • Figure 5 is a cross-section, similar to Figure 2, of a further modification.
  • the hollow turbine blade shown in Figures 1 to- 3 comprises an aerofoil portion 10, a root portion 11 by which the blade is attached to the turbine rotor, and a platform portion 12.
  • the aerofoil portion 10 has a leading edge 13, a trailing edge 14, a convex flank 15 and a concave flank 16.
  • Secured within the hollow interior of the aerofoil portion 10 is a sheet metal partition 17, the partition having a row of apertures 18 down its forward edge and the tongues of metal 19 between these apertures being bent towards the convex flank 15 to touch the interior surface of this flank adjacent the leading edge 13.
  • the rear edge 20 of the partition touches the interior surface of the convex flank 15 towards the rear of the latter.
  • the platform portion 12 is provided with a cooling medium inlet aperture 21, and an internal baffle (not visible) which is conveniently an extension of the lower end of the partition 17 directs the flow of cooling medium as indicated by the dotted line provided with arrows into a longitudinal passage 22 defined on one side by the partition 17 and on the other side by the interior surface of the convex flank 15.
  • the other side of the partition 17 and the interior surface of the concave flank 16 together define another pas sage 23 which communicates with the passage 22 through the apertures 18.
  • the trailing edge 14 is provided with a series of apertures 24 communicating with the passage 23.
  • the partition 30 is provided, adjacent its forward edge, with raised pimples 31 which contact the convex blade flank 15 and provide apertures 32 corresponding to the apertures 18 of Figures 1-3.
  • the partition 17 is provided with a backing piece 33 which reduces the cross-sectional area between the partition 17 and flank 16 to define a restricted passage 23 and so provides a greater coolant flow velocity in this passage, thereby improving the cooling of the concave flank 16.
  • a backing piece 33 which reduces the cross-sectional area between the partition 17 and flank 16 to define a restricted passage 23 and so provides a greater coolant flow velocity in this passage, thereby improving the cooling of the concave flank 16.
  • all parts in this modification are identical to the corresponding parts of the preferred embodiment shown in Figures 1 and 2 and are, therefore, designated by similar reference characters.
  • a hollow turbine blade having a root portion, inlet means for a cooling medium in said root portion, a hollow aerofoil blade portion having a leading edge, a trailing edge provided with cooling medium outlet apertures, a convex flank and a concave flank, a partition extending longitudinally through the interior of said hollow aerofoil blade portion said front edge of said partition being adjacent said leading edge of said hollow aerofoil blade portion and said rear edge of said partition being in contact throughout its length with one of said flanks forwardly of said trailing edge, said partition defining between itself and said one flank a longitudinal passage extending lengthwise of said aerofoil portion and communicating with said cooling medium inlet means, said partition defining between itself and the other of said flanks a second passage communicating with said cooling medium outlet apertures, said partition being imperforate and separating said passages except adjacent said leading edge, and being formed adjacent said leading edge with at least one aperture for directing all of the said cooling medium from said first passage into said second passage at a location adjacent said leading edge and in a direction substantially

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US659375A 1956-05-15 1957-05-15 Cooled hollow turbine blades Expired - Lifetime US2956773A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB342413X 1956-05-15

Publications (1)

Publication Number Publication Date
US2956773A true US2956773A (en) 1960-10-18

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ID=10363183

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Application Number Title Priority Date Filing Date
US659375A Expired - Lifetime US2956773A (en) 1956-05-15 1957-05-15 Cooled hollow turbine blades

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US (1) US2956773A (en))
BE (1) BE557503A (en))
CH (1) CH342413A (en))
DE (1) DE1056427B (en))
FR (1) FR1175169A (en))
GB (1) GB834811A (en))

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3220697A (en) * 1963-08-30 1965-11-30 Gen Electric Hollow turbine or compressor vane
US3420502A (en) * 1962-09-04 1969-01-07 Gen Electric Fluid-cooled airfoil
US3529902A (en) * 1968-05-22 1970-09-22 Gen Motors Corp Turbine vane
US3844678A (en) * 1967-11-17 1974-10-29 Gen Electric Cooled high strength turbine bucket
US3963368A (en) * 1967-12-19 1976-06-15 General Motors Corporation Turbine cooling
US4221539A (en) * 1977-04-20 1980-09-09 The Garrett Corporation Laminated airfoil and method for turbomachinery
US4416585A (en) * 1980-01-17 1983-11-22 Pratt & Whitney Aircraft Of Canada Limited Blade cooling for gas turbine engine
US5002460A (en) * 1989-10-02 1991-03-26 General Electric Company Internally cooled airfoil blade
US5165852A (en) * 1990-12-18 1992-11-24 General Electric Company Rotation enhanced rotor blade cooling using a double row of coolant passageways
EP0661414A1 (en) * 1993-12-28 1995-07-05 Kabushiki Kaisha Toshiba A cooled turbine blade for a gas turbine
US5704763A (en) * 1990-08-01 1998-01-06 General Electric Company Shear jet cooling passages for internally cooled machine elements
EP1207269A1 (de) * 2000-11-16 2002-05-22 Siemens Aktiengesellschaft Gasturbinenschaufel
US20050169752A1 (en) * 2003-10-24 2005-08-04 Ching-Pang Lee Converging pin cooled airfoil
US20090148269A1 (en) * 2007-12-06 2009-06-11 United Technologies Corp. Gas Turbine Engines and Related Systems Involving Air-Cooled Vanes
US20120014808A1 (en) * 2010-07-14 2012-01-19 Ching-Pang Lee Near-wall serpentine cooled turbine airfoil
US20160072141A1 (en) * 2013-04-24 2016-03-10 Intelligent Energy Limited A water separator
US20160326885A1 (en) * 2015-05-08 2016-11-10 United Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US10344619B2 (en) * 2016-07-08 2019-07-09 United Technologies Corporation Cooling system for a gaspath component of a gas powered turbine
WO2019245546A1 (en) * 2018-06-20 2019-12-26 Siemens Energy, Inc. Cooled turbine blade assembly, corresponding methods for cooling and manufacturing
CN112459849A (zh) * 2020-10-27 2021-03-09 哈尔滨广瀚燃气轮机有限公司 一种用于燃气轮机涡轮叶片的冷却结构

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB895077A (en) * 1959-12-09 1962-05-02 Rolls Royce Blades for fluid flow machines such as axial flow turbines
US3301526A (en) * 1964-12-22 1967-01-31 United Aircraft Corp Stacked-wafer turbine vane or blade

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2514105A (en) * 1945-12-07 1950-07-04 Thomas Wilfred Airfoil conditioning means
US2556736A (en) * 1945-06-22 1951-06-12 Curtiss Wright Corp Deicing system for aircraft
DE920641C (de) * 1943-07-15 1954-11-25 Maschf Augsburg Nuernberg Ag Gekuehlte Hohlschaufel, insbesondere fuer Gasturbinen

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE710289C (de) * 1938-02-08 1941-09-09 Bbc Brown Boveri & Cie Schaufel mit Einrichtung zur Bildung einer gegen hohe Temperaturen schuetzenden Grenzschicht und Verfahren zur Herstellung dieser Schaufel
DE853534C (de) * 1943-02-27 1952-10-27 Maschf Augsburg Nuernberg Ag Luftgekuehlte Gasturbinenschaufel
DE852786C (de) * 1943-11-10 1952-10-20 Versuchsanstalt Fuer Luftfahrt Zeitlich gestufter Kuehlluftdurchsatz durch Schaufeln von Gas- oder Abgasturbinen
GB680581A (en) * 1949-05-09 1952-10-08 Hermann Oestrich Means for cooling the blades of gas turbine engines
GB685769A (en) * 1949-11-22 1953-01-14 Rolls Royce Improvements relating to compressor and turbine blading

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE920641C (de) * 1943-07-15 1954-11-25 Maschf Augsburg Nuernberg Ag Gekuehlte Hohlschaufel, insbesondere fuer Gasturbinen
US2556736A (en) * 1945-06-22 1951-06-12 Curtiss Wright Corp Deicing system for aircraft
US2514105A (en) * 1945-12-07 1950-07-04 Thomas Wilfred Airfoil conditioning means

Cited By (29)

* 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
US3220697A (en) * 1963-08-30 1965-11-30 Gen Electric Hollow turbine or compressor vane
US3844678A (en) * 1967-11-17 1974-10-29 Gen Electric Cooled high strength turbine bucket
US3963368A (en) * 1967-12-19 1976-06-15 General Motors Corporation Turbine cooling
US3529902A (en) * 1968-05-22 1970-09-22 Gen Motors Corp Turbine vane
US4221539A (en) * 1977-04-20 1980-09-09 The Garrett Corporation Laminated airfoil and method for turbomachinery
US4416585A (en) * 1980-01-17 1983-11-22 Pratt & Whitney Aircraft Of Canada Limited Blade cooling for gas turbine engine
US5002460A (en) * 1989-10-02 1991-03-26 General Electric Company Internally cooled airfoil blade
US5704763A (en) * 1990-08-01 1998-01-06 General Electric Company Shear jet cooling passages for internally cooled machine elements
US5165852A (en) * 1990-12-18 1992-11-24 General Electric Company Rotation enhanced rotor blade cooling using a double row of coolant passageways
EP0661414A1 (en) * 1993-12-28 1995-07-05 Kabushiki Kaisha Toshiba A cooled turbine blade for a gas turbine
US5538394A (en) * 1993-12-28 1996-07-23 Kabushiki Kaisha Toshiba Cooled turbine blade for a gas turbine
EP1207269A1 (de) * 2000-11-16 2002-05-22 Siemens Aktiengesellschaft Gasturbinenschaufel
US6572329B2 (en) 2000-11-16 2003-06-03 Siemens Aktiengesellschaft Gas turbine
US20050169752A1 (en) * 2003-10-24 2005-08-04 Ching-Pang Lee Converging pin cooled airfoil
US6981840B2 (en) * 2003-10-24 2006-01-03 General Electric Company Converging pin cooled airfoil
US10156143B2 (en) * 2007-12-06 2018-12-18 United Technologies Corporation Gas turbine engines and related systems involving air-cooled vanes
US20090148269A1 (en) * 2007-12-06 2009-06-11 United Technologies Corp. Gas Turbine Engines and Related Systems Involving Air-Cooled Vanes
US20120014808A1 (en) * 2010-07-14 2012-01-19 Ching-Pang Lee Near-wall serpentine cooled turbine airfoil
US8535006B2 (en) * 2010-07-14 2013-09-17 Siemens Energy, Inc. Near-wall serpentine cooled turbine airfoil
US20130302167A1 (en) * 2010-07-14 2013-11-14 Mikro Systems, Inc. Near-Wall Serpentine Cooled Turbine Airfoil
US8870537B2 (en) * 2010-07-14 2014-10-28 Mikro Systems, Inc. Near-wall serpentine cooled turbine airfoil
US20160072141A1 (en) * 2013-04-24 2016-03-10 Intelligent Energy Limited A water separator
US20160326885A1 (en) * 2015-05-08 2016-11-10 United Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US10502066B2 (en) * 2015-05-08 2019-12-10 United Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US11143039B2 (en) 2015-05-08 2021-10-12 Raytheon Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US10344619B2 (en) * 2016-07-08 2019-07-09 United Technologies Corporation Cooling system for a gaspath component of a gas powered turbine
WO2019245546A1 (en) * 2018-06-20 2019-12-26 Siemens Energy, Inc. Cooled turbine blade assembly, corresponding methods for cooling and manufacturing
CN112459849A (zh) * 2020-10-27 2021-03-09 哈尔滨广瀚燃气轮机有限公司 一种用于燃气轮机涡轮叶片的冷却结构

Also Published As

Publication number Publication date
GB834811A (en) 1960-05-11
DE1056427B (de) 1959-04-30
CH342413A (fr) 1959-11-15
BE557503A (en))
FR1175169A (fr) 1959-03-20

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