US3849025A - Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets - Google Patents

Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets Download PDF

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Publication number
US3849025A
US3849025A US00345538A US34553873A US3849025A US 3849025 A US3849025 A US 3849025A US 00345538 A US00345538 A US 00345538A US 34553873 A US34553873 A US 34553873A US 3849025 A US3849025 A US 3849025A
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coolant
cooling
airfoil
subsurface
improvement
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US00345538A
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English (en)
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C Grondahl
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General Electric Co
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General Electric Co
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Priority to US00345538A priority Critical patent/US3849025A/en
Priority to CA195,243A priority patent/CA994245A/en
Priority to GB1282774A priority patent/GB1470322A/en
Priority to IT49536/74A priority patent/IT1005870B/it
Priority to DE2414397A priority patent/DE2414397A1/de
Priority to NL7404171A priority patent/NL7404171A/xx
Priority to JP49034013A priority patent/JPS5025914A/ja
Priority to FR7410763A priority patent/FR2223549B1/fr
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    • 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
    • F01D5/185—Liquid cooling
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • Openings to the coolant supply conduits are preferably spaced at even intervals UNITED STATES PATENTS along the circumference of the gutter.
  • 02 5 SHEU 10F 3 PATENTE :znv 1 91974 sneer am a w. W Z 1 I BACKGROUND OF THE INVENTION Structural arrangements for the open-circuit liquid cooling of gas turbine buckets are shown in U.S. Pat. Nos. 3,446,481 Kydd and 3,446,482 Kydcl.
  • the bucket cooling is accomplished by means of a large number of cooling channels extending radially from the root toward the tip. Arrangements for metering liquid coolant to each of such cooling channels are shown in U.S. Pat. No. 3,658,439 Kydd and in U.S. application Ser. No. 285,633 Moore (now U.S. Pat. No. 3,804,551 assigned to the assignee of the instant invention). Both Kydd U.S. Pat. No. 3,658,439 and the Moore application employ axially-extending weir construction for the metering. These patents and patent application are incorporated by reference.
  • Open-circuit liquid cooling capability is particularly important, because it make feasible increasing the turbine inlet temperature to an operating range of from 2,500F to at least 3,500F thereby obtaining an increase in power output ranging from about 100 to 200 percent and an increase in thermal efficiency ranging to as high as 50 percent.
  • Such open-circuit liquidcooled turbine structures are referred to as ultra high temperature gas turbines.
  • Liquid coolant metering is complicated by the extremely high bucket tip speeds employed resulting in centrifugal fields of the order of 250,000 G. Under such severe operating conditions even slight errors in manufacture of the weir structure can orient the weir slightly askew of the axis of rotation and produce nonuniform coolant distribution to the cooling channels. Also, any distortion of the turbine disk or disk rim induced at speed can produce a similar effect.
  • the instant invention minimizes the number of cooling channels used in open-circuit liquid cooling of turbine buckets by arranging each cooling channel in a convoluted configuration in which most of the length of the cooling channelextends generally chordwise of the airfoil under the surface thereof with successive convolutions progressing from the root toward the tip thereof.
  • Each such convoluted coolant channel is in direct flow communication with a circumferentially disposed gutter in the rotor rim via a coolant supply conduit, whereby liquid coolant is supplied directly to each such winding cooling channel.
  • a coolant conduit of serpentine or sinuous configuration extending over at least a portion of the bucket platform is employed interposed in series between the coolant supply conduit and a serpentine coolant channel in the airfoil.
  • a uniform supply of liquid coolant to the inlet to each coolant supply conduit is insured by spacing the openings (gutter-end) of these coolant supply conduits at equal intervals around the circumference of the gutter.
  • FIG. 1 is a threedimensional view, partly cut away, showinga typical overall arrangement for at least one of the coolant paths for a turbine bucket constructed according to this invention
  • FIG. 2 is a view in section through the rotor disk showing the pressure side of the bucket of FIG. 1 in elevation and coolant supply conduits for two coolant paths on each side of the bucket;
  • FIG. 3 is a view similar to FIG. 1 specifically applied to dovetailed bucket attachment
  • FIG. MS a view in section through the rotor disk with the pressure side of the bucket of FIG. 3 in elevation showing the coolant supply conduits for two coolant paths on each side of the bucket;
  • FIG. 5 is a three-dimensional view, partly cut away, showing a spiraled configuration of a cooling channel for a turbine bucket according to this invention
  • FIG. 6 is a plan view, partially cut away, of the bucket shown inFIG. 5 setting forth each platform cooling channel connected in series between a spiral bucket cooling channel and the coolant supply conduit therefor and 1
  • FIG. 7 is a section taken through any of the bucket cooling channels showing that in spite of the tortuous nature of the coolant path under the bucket skin, it still remains an open,'high velocity flow system throughout.
  • a similar arrangement of one or more groove patterns (not shown) extending in a serpentine pattern is disposed on the suction face of strut 12.
  • the serpentine cooling channels (preferably rectangular in cross section as shown in FIG. 7) are in flow communication with, and terminate at, manifold 16 (and a similar length of manifold, not shown, on the suction side) recessed into core 12.
  • a cross-over conduit (not shown) connects the manifold on the suction side with manifold 16 via opening 16a.
  • Kercher Even the use of very pure coolant is only a partial solution to these problems. Thus, the arrangement disclosed in Kercher is unsuitable to liquid cooling although it provides an effective approach to air cooling.
  • the open-circuit coolant discharge from manifold 16 is accomplished via the convergentdivergent nozzle 17 as described in US.
  • the root portion 18 fits into a mating slot in rim 19 of the turbine disk, being brazed thereto. After buckets 10 have been brazed into the rim 19, the gutters 21, 22 are machined into the rim.
  • Steel alloys may be used for the skin and core, preferably those containing at least 12 percent by weight of chromium or corrosion-resistant and heat treatable to achieve high strength. Conventional brazing alloys having melting points ranging from 700 to 1,200C. may be used.
  • each serpentine cooling channel pattern formed in the surface of core 12 is connected to (and is in flow communication with) a serpentine groove (e.g., grooves 23, 24) formed in the platform surface of root portion 18.
  • Serpentine platform cooling channels are defined by such grooves together with platform skin 26 and each such channel serves to cool a portion of the platform surface.
  • the cooling of the platform may be accomplished by the use of a single pool (or a series of interconnected pools) so long as any given pool cavity is properly baffled and in flow communication with one of gutters 21, 22 and with one of the convoluted cooling channels below the surface of the airfoil portion of bucket 10. Care must be taken to design for stress transfer between airfoil and root, of course.
  • each platform serpentine segment (such as serpentine grooves 23, 24) is in flow.
  • coolant supply conduits such as conduits 27, 28, 29
  • conduits 29, 31 shown in FIG. 2
  • serpentine cooling channels in the platform fed thereby the principles being fully illustrated with conduits 27 and 28.
  • the design of the rim, bucket root and gutters may be varied, of course, and as a consequence part of the length of conduits 27, 28, 29, 31 may extend through the rimstructure to reach the gutters. Such construction, for example, is shown in FIG. 4.
  • cooling liquid (usually water) is sprayed at low pressure in a generally radially outward direction from nozzles (not shown), but preferably located on each side of disk 32.
  • the coolant impinges on disk 19 and moves into gutters 21, 22 defined in part by downwardly extending lip portions formed in rotor rim 19.
  • the cooling liquid is retained in the gutters until this liquid has been accelerated to the prevailing disk rim velocity.
  • this liquid drains in one or more continuous path from gutters 21, 22 in the generally radially outward direction via:
  • coolant conduits e.g., conduits 27, 28, 29,
  • serpentine platform cooling channel patterns e.g., the cooling channels defined by grooves 23 and 24 and skin 26
  • chordwise-extending manifolds e. g., manifold 16
  • nozzle 17 from which the heated coolant (liquid and gas, or vapor, mixture) is discharged.
  • a uniform supply of coolant to each coolant supply conduit is insured by spacing the openings from the gutters to the coolant supply conduits at equal intervals along the circumference of the gutters;
  • the turbine buckets described herein are made by investment casting as generally described in US. Pat. No. 3,678,987 Kydd.
  • the bucket cores are made solid. Any passageways passing through the bucket root or formed in the platform surface of the root and extending under the base of the core airfoil portion are provided for by the inclusion of appropriately shaped leachable ceramic (e.g., quartz tubing) bodies in the wax replicas from which the ceramic shell molds are made.
  • leachable ceramic e.g., quartz tubing
  • FIGS. 3 and 4 illustrate the application of the improvement of this invention to a dovetail bucket 40 made up of metal skin 4l,'strut 42, dovetail root portion 43, and platform skin 44. At least part of three convoluted cooling passage patterns are shown and most of one cooling path from gutter to exit nozzle is shown. Such buckets are held in place in rim 46 by retaining rings (not shown)or retaining pins (not shown).
  • coolant supply conduits 47, 48 are those for which connections to serpentine platform groove patterns are shown.
  • Other such coolant supply channels must, of course, be provided for the conduct of liquid coolant to serpentinepattern 49, 51 and other patterns (not shown) on the suction face of core 42.
  • conduit 47 cooperates with passage 417a and conduit 48.
  • passage 48a to act as coolant supply ducts.
  • a pair of similar supply ducts is shown connected to gutter 53, but in the interest of clarity the connections from these supply ducts to platform cooling patterns are not shown. Gutter openings to passages connecting the gutters to the channels in the bucket roots for the total number of buckets are evenly spaced in any given gutter to insure equal feed of coolant thereto.
  • FIGS..5 and 6 Still another configuration for a convoluted cooling pattern according to this invention is shown in FIGS..5 and 6.
  • the cooling pattern for the airfoil of bucket 60 in this instance is a pair of spiraling conduits 61, 62 connected at the platform level to separate serpentine platform cooling patterns .63, 64, respectively, and discharging their coolant flows into manifold 66 for exit through nozzle 67.
  • Platform coolingpatterns 63, 64 would be connected to separate gutters (not shown) via supply conduits 68, 69, respectively, for the construction shown.
  • a double helical pattern is shown, either single or multiple helical patterns can be employed.
  • the number of convoluted cooling channel patterns employed under the airfoil surfaces of the buckets and the span of metal permitted between the successive chordwise-extending portions of these channels on a given bucket face can be designed to match the amount the channels do not, and need not, run full).
  • the coolant path is open such that liquid and vapor are each free to move without disturbing eachother.
  • the extremely large centrifugal force exerted on the system readily urges the liquid coolant through the most tortuous, small cross section channel pattern required.
  • the liquid coolant is disposed over surfaces of channels 71 that are the most radially-outward and are toward the pressure side of the bucket.
  • the liquid coolant has a free surface and, as vapor is generated
  • a single convoluted pattern may be utilized to cool the entire suction face and a similar such cooling channel pattern may be employed to cool the entire pressure face or any number of'zonecl cooling patterns may be devised wherein two, three or even more separate serpentine patterns may be disposed under either or both of the airfoil surfaces of the bucket.
  • FIG. 7 is a section taken through a portion of a cooling channel pattern and the adjacent skin and bucket core regionsk
  • the generally radial distance indicated by the letter P between corresponding points on chord- Wise-extending segments of the same convoluted cooling channel as well as the dimensions of the cooling channels are a function of:
  • a very important feature of this invention is the utilization of convoluted patterns for the cooling channels, in which channels in spite of the tortuous nature thereof coolant liquid always has a free surface (i.e.,
  • the velocity of the thin layer of coolant is reduced from the velocities that would prevail for liquid passing through radial cooling channels as in the Moore application, the velocity would still be of the order of about 25 times the velocity of the same liquid coolant, if used in the radially-directed serpentine passages of Ke rcher.
  • the skin and core thermal conductivities are considered equal to about 45 BTU ft/hr ft F; lower values of thermal conductivity will decrease the maximum allowable pitch.
  • the maximumallowable bucket skin surface temperature is to be l,400F; a lower temperature limit will decrease the maximum allowable pitch.
  • the temperature of the liquid coolant is to be F; an increase in this limit will decrease the maximum allowable pitch.
  • the skin thickness is to be 0.010 inch; increasing the thickness of the skin will decrease the maximum allowable pitch.
  • Cooling channel dimensions are to be 0.030 inch X 0.030 inch; an increase in the channel crosssectional area will decrease the pitch in those locations on the bucket at which the cooling problem is the most severe (coolant film not in contact with the skin).
  • the cross-sectional area of the convoluted cooling channels can be varied as a-function of the heat flux, which is widely variant chordwise of the bucket. However, it is preferred that the dimensions of any given cooling channel (e.g., pattern 113) be kept substantially constant. p
  • a vane structure adapted for mounting in a rotating element of a machine wherein the airfoil surfaces of the vane are subjected to contact with hot gas
  • the vane comprising an airfoil-shaped core and a conforming skin affixed thereto, said core and said skin defining at least one open-ended subsurface passage therebetween for the transit of coolant therethrough, said at least one passage being adapted to receive coolant flow at the radially inner end thereof from a source of coolant and to discharge the coolant flow from the radially outer end thereof into a chordwise-extending manifold, said manifold in turn being adapted to discharge coolant flow from said vane
  • the improvement in which a plurality of subsurface passages are employed, each passage being arranged in a serpentine pattern confined to one face of the vane and having a substantially constant depth along the length thereof, most of each successive convolution of said serpentine pattern extending in the generally chordwise direction.
  • a turbine disk is mounted on a shaft rotatably supported in a casing, said turbine disk extending substantially perpendicular to the axis of said shaft and having turbine buckets affixed to the outer rim thereof, each bucket comprising an airfoilshaped core and a conforming skin affixed thereto, said buckets receiving a driving force from a hot motive fluid moving in a direction generally parallel to said axis of said shaft and the driving force being transmitted to said shaft via said turbine disk, means located radially inward of said buckets for introducing liquid coolant within said turbine in a radially outward direction to enter an open-ended coolant distribution circuit comprising in the airfoil of each of said buckets at least one subsurface cooling channel defined by said core and said skin, said at least one cooling channel being adapted to receive liquid coolant at the radially inner end thereof, and a manifolding and discharge portion located in the radially outer end region of the airfoil of the given bucket, said manifold
  • said at least one subsurface cooling channel being of a substantially constant depth along the length thereof and being arranged ina serpentine pattern confined to one face of the vane with most of each of the successive convolutions thereof extending in the generally chordwise direction, the radially inner end of said cooling channel being in flow communication with said gutter region.
  • each cooling channel is connected to the gutter region by a separate closed conduit having as part of the length thereof a subsurface cooling passage of convoluted configuration located in platform structure at the base of the airfoil.
  • each subsurface cooling channel is connected to a separate closed conduit in flow communication with an annular gutter region, the opening from each closed conduit into the same gutter region being equally spaced from openings of closed conduits adjacent thereto on each side thereof.
  • each airfoil is provided with a plurality of subsurface cooling channe 5.
  • each closed conduit has as part of the length thereof a subsurface cooling passage of convoluted configuration located in platform structure at the base of the airfoil.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00345538A 1973-03-28 1973-03-28 Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets Expired - Lifetime US3849025A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US00345538A US3849025A (en) 1973-03-28 1973-03-28 Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets
CA195,243A CA994245A (en) 1973-03-28 1974-03-18 Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets
IT49536/74A IT1005870B (it) 1973-03-28 1974-03-22 Struttura di canali di raffredda mento a serpentina per palette di turbine a gas raffreddate in circui to aperto
GB1282774A GB1470322A (en) 1973-03-28 1974-03-22 Rotor vane
DE2414397A DE2414397A1 (de) 1973-03-28 1974-03-26 Kuehlkanalaufbau fuer fluessigkeitsgekuehlte turbinenschaufeln
NL7404171A NL7404171A (de) 1973-03-28 1974-03-27
JP49034013A JPS5025914A (de) 1973-03-28 1974-03-28
FR7410763A FR2223549B1 (de) 1973-03-28 1974-03-28

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US00345538A US3849025A (en) 1973-03-28 1973-03-28 Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets

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US (1) US3849025A (de)
JP (1) JPS5025914A (de)
CA (1) CA994245A (de)
DE (1) DE2414397A1 (de)
FR (1) FR2223549B1 (de)
GB (1) GB1470322A (de)
IT (1) IT1005870B (de)
NL (1) NL7404171A (de)

Cited By (36)

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US4017210A (en) * 1976-02-19 1977-04-12 General Electric Company Liquid-cooled turbine bucket with integral distribution and metering system
US4118145A (en) * 1977-03-02 1978-10-03 Westinghouse Electric Corp. Water-cooled turbine blade
US4156582A (en) * 1976-12-13 1979-05-29 General Electric Company Liquid cooled gas turbine buckets
US4260336A (en) * 1978-12-21 1981-04-07 United Technologies Corporation Coolant flow control apparatus for rotating heat exchangers with supercritical fluids
US4275990A (en) * 1977-12-17 1981-06-30 Rolls-Royce Limited Disc channel for cooling rotor blade roots
US4338780A (en) * 1977-12-02 1982-07-13 Hitachi, Ltd. Method of cooling a gas turbine blade and apparatus therefor
US4543781A (en) * 1981-06-17 1985-10-01 Rice Ivan G Annular combustor for gas turbine
US4565490A (en) * 1981-06-17 1986-01-21 Rice Ivan G Integrated gas/steam nozzle
US5611662A (en) * 1995-08-01 1997-03-18 General Electric Co. Impingement cooling for turbine stator vane trailing edge
US5967752A (en) * 1997-12-31 1999-10-19 General Electric Company Slant-tier turbine airfoil
US5971708A (en) * 1997-12-31 1999-10-26 General Electric Company Branch cooled turbine airfoil
US6022190A (en) * 1997-02-13 2000-02-08 Bmw Rolls-Royce Gmbh Turbine impeller disk with cooling air channels
US20050031452A1 (en) * 2003-08-08 2005-02-10 Siemens Westinghouse Power Corporation Cooling system for an outer wall of a turbine blade
US20060108395A1 (en) * 2002-09-30 2006-05-25 The Curators Of University Of Missouri Integral channels in metal components and fabrication thereof
US20060171809A1 (en) * 2005-02-02 2006-08-03 Siemens Westinghouse Power Corporation Cooling fluid preheating system for an airfoil in a turbine engine
US20070104576A1 (en) * 2005-11-08 2007-05-10 United Technologies Corporation Peripheral microcircuit serpentine cooling for turbine airfoils
US20070172355A1 (en) * 2006-01-25 2007-07-26 United Technlogies Corporation Microcircuit cooling with an aspect ratio of unity
US20080050241A1 (en) * 2006-08-24 2008-02-28 Siemens Power Generation, Inc. Turbine airfoil cooling system with axial flowing serpentine cooling chambers
US20080056909A1 (en) * 2006-09-05 2008-03-06 United Technologies Corporation Multi-peripheral serpentine microcircuits for high aspect ratio blades
US20100239431A1 (en) * 2009-03-20 2010-09-23 Siemens Energy, Inc. Turbine Airfoil Cooling System with Dual Serpentine Cooling Chambers
US20110110772A1 (en) * 2009-11-11 2011-05-12 Arrell Douglas J Turbine Engine Components with Near Surface Cooling Channels and Methods of Making the Same
US8047788B1 (en) * 2007-10-19 2011-11-01 Florida Turbine Technologies, Inc. Turbine airfoil with near-wall serpentine cooling
WO2012033643A1 (en) * 2010-09-07 2012-03-15 Siemens Energy, Inc. Ring segment with serpentine cooling passages
EP2634369A1 (de) * 2012-03-01 2013-09-04 General Electric Company Turbinenschaufel und zugehöriges Kühlverfahren
US20150184530A1 (en) * 2013-12-27 2015-07-02 General Electric Company Turbine nozzle and method for cooling a turbine nozzle of a gas turbine engine
US10233761B2 (en) 2016-10-26 2019-03-19 General Electric Company Turbine airfoil trailing edge coolant passage created by cover
US10273810B2 (en) 2016-10-26 2019-04-30 General Electric Company Partially wrapped trailing edge cooling circuit with pressure side serpentine cavities
US10301946B2 (en) 2016-10-26 2019-05-28 General Electric Company Partially wrapped trailing edge cooling circuits with pressure side impingements
US10309227B2 (en) 2016-10-26 2019-06-04 General Electric Company Multi-turn cooling circuits for turbine blades
US10352176B2 (en) * 2016-10-26 2019-07-16 General Electric Company Cooling circuits for a multi-wall blade
US10450950B2 (en) 2016-10-26 2019-10-22 General Electric Company Turbomachine blade with trailing edge cooling circuit
US10450875B2 (en) 2016-10-26 2019-10-22 General Electric Company Varying geometries for cooling circuits of turbine blades
US10465521B2 (en) 2016-10-26 2019-11-05 General Electric Company Turbine airfoil coolant passage created in cover
US10598028B2 (en) 2016-10-26 2020-03-24 General Electric Company Edge coupon including cooling circuit for airfoil
CN111335960A (zh) * 2018-12-18 2020-06-26 通用电气公司 涡轮发动机翼型件及冷却方法
US11814965B2 (en) 2021-11-10 2023-11-14 General Electric Company Turbomachine blade trailing edge cooling circuit with turn passage having set of obstructions

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JPS5244994U (de) * 1975-09-26 1977-03-30
GB2163219B (en) * 1981-10-31 1986-08-13 Rolls Royce Cooled turbine blade
ES2122423T3 (es) * 1994-11-14 1998-12-16 Nippon Catalytic Chem Ind Procedimiento para la produccion de acido acrilico.
DE19713268B4 (de) * 1997-03-29 2006-01-19 Alstom Gekühlte Gasturbinenschaufel
DE69928073T2 (de) 1999-02-19 2006-07-20 Nippon Shokubai Co., Ltd. Verfahren zur Herstellung von Acrylsäure und Verfahren zur Herstellung vom Katalysator
JP3943284B2 (ja) 1999-05-27 2007-07-11 株式会社日本触媒 アクリル酸の製造方法
JP5134745B2 (ja) 2001-09-19 2013-01-30 株式会社日本触媒 アクリル酸の製造方法
JP4813758B2 (ja) 2003-02-27 2011-11-09 株式会社日本触媒 複合酸化物触媒およびそれを用いたアクリル酸の製造方法
KR100497175B1 (ko) 2003-03-26 2005-06-23 주식회사 엘지화학 프로필렌 및 이소부틸렌 부분산화 반응용 촉매의 제조방법

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US2888243A (en) * 1956-10-22 1959-05-26 Pollock Robert Stephen Cooled turbine blade
US3220697A (en) * 1963-08-30 1965-11-30 Gen Electric Hollow turbine or compressor vane
US3370829A (en) * 1965-12-20 1968-02-27 Avco Corp Gas turbine blade construction
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US3736071A (en) * 1970-11-27 1973-05-29 Gen Electric Bucket tip/collection slot combination for open-circuit liquid-cooled gas turbines

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US2888241A (en) * 1954-06-09 1959-05-26 Stalker Corp Fabricated cooled turbine blades
US2888243A (en) * 1956-10-22 1959-05-26 Pollock Robert Stephen Cooled turbine blade
US3220697A (en) * 1963-08-30 1965-11-30 Gen Electric Hollow turbine or compressor vane
US3370829A (en) * 1965-12-20 1968-02-27 Avco Corp Gas turbine blade construction
US3658439A (en) * 1970-11-27 1972-04-25 Gen Electric Metering of liquid coolant in open-circuit liquid-cooled gas turbines
US3736071A (en) * 1970-11-27 1973-05-29 Gen Electric Bucket tip/collection slot combination for open-circuit liquid-cooled gas turbines

Cited By (59)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4017210A (en) * 1976-02-19 1977-04-12 General Electric Company Liquid-cooled turbine bucket with integral distribution and metering system
US4156582A (en) * 1976-12-13 1979-05-29 General Electric Company Liquid cooled gas turbine buckets
US4118145A (en) * 1977-03-02 1978-10-03 Westinghouse Electric Corp. Water-cooled turbine blade
US4338780A (en) * 1977-12-02 1982-07-13 Hitachi, Ltd. Method of cooling a gas turbine blade and apparatus therefor
US4275990A (en) * 1977-12-17 1981-06-30 Rolls-Royce Limited Disc channel for cooling rotor blade roots
US4260336A (en) * 1978-12-21 1981-04-07 United Technologies Corporation Coolant flow control apparatus for rotating heat exchangers with supercritical fluids
US4543781A (en) * 1981-06-17 1985-10-01 Rice Ivan G Annular combustor for gas turbine
US4565490A (en) * 1981-06-17 1986-01-21 Rice Ivan G Integrated gas/steam nozzle
US5611662A (en) * 1995-08-01 1997-03-18 General Electric Co. Impingement cooling for turbine stator vane trailing edge
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DE2414397A1 (de) 1974-10-17
JPS5025914A (de) 1975-03-18
IT1005870B (it) 1976-09-30
GB1470322A (en) 1977-04-14
CA994245A (en) 1976-08-03
FR2223549B1 (de) 1979-10-12
FR2223549A1 (de) 1974-10-25
NL7404171A (de) 1974-10-01

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