US3804551A - System for the introduction of coolant into open-circuit cooled turbine buckets - Google Patents

System for the introduction of coolant into open-circuit cooled turbine buckets Download PDF

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Publication number
US3804551A
US3804551A US00285633A US28563372A US3804551A US 3804551 A US3804551 A US 3804551A US 00285633 A US00285633 A US 00285633A US 28563372 A US28563372 A US 28563372A US 3804551 A US3804551 A US 3804551A
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United States
Prior art keywords
coolant
cooling channels
platform structure
open
underside
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Expired - Lifetime
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US00285633A
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English (en)
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J Moore
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General Electric Co
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General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US00285633A priority Critical patent/US3804551A/en
Priority to DE2336952A priority patent/DE2336952C2/de
Priority to NL7311237A priority patent/NL7311237A/xx
Priority to GB3882373A priority patent/GB1437618A/en
Priority to NO3395/73A priority patent/NO143880C/no
Priority to FR7331421A priority patent/FR2198052B1/fr
Priority to IT28454/73A priority patent/IT993116B/it
Priority to JP9740073A priority patent/JPS5644241B2/ja
Priority to SU731962218A priority patent/SU670237A3/ru
Application granted granted Critical
Publication of US3804551A publication Critical patent/US3804551A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F05B2240/801—Platforms for stationary or moving blades cooled platforms
    • 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

  • Open-circuit liquid cooling capability is particularly important because it makes feasible increasing the turbine inlet temperature to an operating range of from 2,500 F to at least 3,500 F 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 liquid cooled turbine structures are referred to as ultra high temperature gas turbines.
  • FIG. 1 shows a unified bucket/rotor diskrim construction embodying the means of the instant invention for conducting liquid to the pool/weir structure and power augmentation means of the general type disclosed and claimed in the aforementioned Day application;
  • FIG. 2 is a section taken on line 22 of FIG. 1 (but notto the same scale) showing the interrelationship between the pool, the weir construction and the liquid coolant conducting means of this invention;
  • FIG. 3 is a section taken on line 34-3 of FIG. 2 and FIG. 4 isa section showing the application of the instant invention to dovetailed bucket construction.
  • Turbine bucket 10 consists of metal skin 11 bonded to hollow core 12 having spanwise extending grooves 13a formed in the surfaces thereof.
  • the rectangular cooling channels, or passages, 13 defined by skin 11 and grooves 13a conduct cooling liquid therethrough beneath skin 11.
  • the rectan-. gular cooling channels 13 on the pressure side of bucket 10 are in flow communication with, and terminate at, manifold 14 recessed into core 12.
  • the gas side heat transfer coefficient would be highly desirable. 7
  • the open-circuit coolant discharge from manifold 14 (and, thereby, from the manifold on the suction side) is accomplished via convergent-divergent nozzle 16 described in the aforementioned Day application.
  • Annular collection slot 17 formed in casing 18 receives the liquid component of the coolantfiowdischarge from power augmenter nozzle 16 e.;g. for recirculation thereof.
  • the root end of core 11 consists of a number of finger-like projections, or tines, 19 ,of varying length. These projections 19 may presenta generally rectangular profile as shown or each tine maybe tapered toward the distal-end thereof to present a generally triangular profile.
  • Rim 21 of turbine disk 22 has grooves 23 ma- 'chined thereinv extending to variousdepths separated by ribs 24, the depths and widths of grooves 23 matching the different lengths and widths of bucket tines 19 such that tines 19 will fit snugly therein in an interlocking relationship.
  • brazing alloy is placed in each groove 23 and the buckets are inserted and held in fixed position by a fixture.
  • the fixture is biased to maintain a tight fit between tines 19 and grooves 23 regardless of thermal expansion.
  • Conventional brazing alloys having melting points ranging from 700 to 1,100" C may be used.
  • the assembly (rim with all the buckets properly located) is furnace-brazed to provide an integral structure.
  • Steel alloys may be used for the skin and core, preferably those containing at least 12 percent by weight of chromium for corrosion resistance and heat treatable to achieve high strength.
  • grooves 23 into rim 21 not only provides the requisite configuration for fastening the bucket root and lessens the weight of the rim, but in addition, the ribs 24 between grooves 23 provide areas on the upper surface thereof for attachment thereto of the investment cast platform elements 26, which have concave undersides to accommodate pools 27 of liquid coolant. Support segments 28 are dimensioned and located so that the widths thereof coincide with the widths of ribs 24, when placed in juxtaposition.
  • each weir 29 provides a cylindrical surface (the elements of which extend in the axial direction) following the trace of bucket (FIG. 3) on each side thereof separating a pool 27 from adjacent cooling channels 13.
  • Platform elements 26 are affixed to the rotor rim 21 by the electron beam welding of platform edges 26a and supports 28 to ribs 24 after previously grinding the radially inwardly faces of edges 26a and supports 28 to a radius common to the initial radius of ribs 24.
  • platform construction shown herein consists of individual platform elements other constructions are equally feasible.
  • the platform components may be made integral with each bucket.
  • the weir surfaces distributing coolant to buckets 10 will be formed as part of the platform construction located adjacent each side of each bucket 10.
  • 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 22) and impinges on disk 22.
  • the coolant thereupon moves into gutters 32, 32a defined in part by downwardly extending lip portions 33, 33a.
  • the cooling liquid is retained in the gutters until this liquid has accelerated to the prevailing disk rim velocity.
  • An alternate arrangement (not shown) for conducting liquid coolantfrom gutters 32, 32a to pools 27 would consist of providing internal passageways, which run in the general radial direction, through the outer walls of rim 21 and platform edges 26a, each passageway being in flow communication with a gutter and a pool. Entry to the pool would be made radially outward of the weir surface 29.
  • cooling liquid moves radially outward through cooling channels 13 of any given bucket 10, then depending upon (a) the rate at which coolant is supplied, (b) the desired operating temperature of the bucket, (c) the area of the throat of nozzle 16 and (d) the extent of frictional heating of the coolant within the distribution circuit, some portion of the liquid coolant is converted to the gaseous or vapor state as it absorbs heat from the skin 11 and core 12 of the bucket.
  • the vapor or gas and any remaining liquid coolant pass into manifold 14 and the manifold on the suction face. Thereafter, the flow from the suction face manifold is merged with the flow in manifold 14 (via opening 15) and these combined flows exit therefrom through power augmenter nozzle 16.
  • this exit flow is relied upon for the recovery of reaction energy and is particularly effective when the exit flow is made supersonic.
  • the flow of liquid entering pool 27 should distribute itself therein at a uniform constant low velocity so as not to disturb the surface 36 of pool 27 and performance of the metering function is found to be greatly improved by introducing the liquid coolant beneath the pool surface 36.
  • This entry is accomplished by locating the discharge end 37 of each supply tube 34 radially outward of surface 36, end 37 being spaced away from the underside of platform element 26 by means of tip 38 e.g. a projecting portion of the wall of tube 34 in contact with the base of the concavity containing pool 27. Since the distance from the underside of platform 26 to surface 36 must exceed the distance from the underside of platform 26 to the weir surface 29 by a finite amount (e.g. about 000075 inch) in order for liquid flow to pass over weir 29, end 37 may be radially disposed at the same level as the surface of weir 29 or'at some optimum position radially outward therefrom.
  • each platform element 26 may be made with a single support projection formed on the underside thereof extending generally transverse of ribs 24 for attachment thereto. By proper selection of the shape of this projection an optimum pool geometry for weir flow distribution can be achieved.
  • tips 38 (illustrated in FIG. 3) around the central axes of the tubes 34 to which they are connected is such as to direct the entering liquid so as to cause preferential flow in a controlled manner, i.e. at certain weir stations.
  • the lateral flow of liquid entering at low velocity is encouraged to provide the desired pool depth profile over the extent of pool 27.
  • flow at specific weir stations e.g. adjacent the pressure side leading edge and adjacent the pressure side trailing edge of buckets is increased to compensate for the larger cooling capacity required over these specificturbine bucket surface areas.
  • Preferably supply tubes 34 are located with the axes thereof extending in a radial direction so that the initial velocity of the incoming coolant flow is perpendicular to the bottom of the pool. However, if additional directional effect is required, it may be obtained by introducing a slight (as much as about inclination of the axes of tubes 34 to theradial direction.
  • Tip support 34 need not be made as a single piece as shown, but may, if desired, be in the form of a plurality of spaced tip extensions.
  • the power required to pump the coolant through the cooling circuit may be reduced in part by reducing the mass flow of liquid coolant employed. This in turn results in the vaporization of some or all of the liquid coolant.
  • the volume of the vapor so generated is orders of magnitude larger than the volume of the liquid actually in the cooling channels and the vapor velocities in the cooling channels is very high.
  • these vapor flows can deleteriously influence the coolant liquid flows.
  • any flow of vapor in a direction opposite to the direction of distribution of the liquid flow will slow down the required transit of the liquid coolant. If this occurs, the thickness of the liquid film-in the coolant passages is increased and the high convective heat transfer coefficient to the buckets is reduced.
  • Another advantage of the instant invention in addition to the increased effectiveness of metering of the coolant flow is that by disposing each supply tube 34 with the end 37 thereof below the surface 36 of pool 27, flow of vapor in the upstream direction in the cooling circuit is prevented, while still preserving the downstream flow of coolant liquid.
  • each tube 34 (radially inward of the liquid level) consists essentially of air, hot gas and/or steam.
  • Liquid coolant entering inlet tubes 34 in the rotating system disposes itself over the trailing wall of the tubes 34 as it traverses volume 39, except for portions of the flow, which may tend to splash away from the walls within the confines of tube 34, particularly if the inside surface thereof is roughened, until the coolant liquid reaches the liquid level.
  • the increase of pressure in the coolant circuit upstream of nozzle 16 can be made high enough so that the discharge of vapor through nozzle 16 is at supersonic velocity providing a very substantial force vector in a direction opposite to the direction of rotation of blades 10 effective to recoup at least in part thecoolant pumping losses.
  • a dovetailed bucket made up of metal skin 51 and platform element 52 affixed to bucket core 53 having a dovetail root portion 54 integral therewith.
  • Liquid is supplied from a coolant source (not shown) to gutters 56, 56a via passages 57, 57a extending through rotor 58.
  • Gutters 56, 56a are in flow communication with pools 59, 59a of liquid coolant via liquid coolant conducting tubes 61 having discharge ends 62 and positioning/deflection tips 62.
  • Weirs 64, 64a are formed integral with platform elements 52, 52a.
  • coolant distribution system operation of the coolant distribution system is the same as has been described hereinabove in that liquid coolant distributed over weir surfaces 64, 64a enters slots 66a (grooves in the airfoil surfaces) of bucket 53 for entry into coolant passages 66 defined by skin 51 and slots 66a.
  • the arrangement of cooling channels 66, the collecting manifolds (not shown) and the ejection nozzle (not shown) would be the same as, or similar to the arrangement shown in FIG. 1.
  • the grooved rim rotor with mating bucket root shown in FIGS. 1-3 appear to be more apt to be employed in the construction of small liquid cooled turbines while the dovetailed bucket construction shown in FIG. 4 appear to be more adaptable for use in larger liquid cooled turbine units.
  • This invention has been illustrated in connection with a liquid cooled gas turbine, but application, can be made thereof to any liquid cooled rotor system, e.g. a compressor, which would in essence comprise the general structure shown herein operated in reverse to work on a gas instead of having gaseous working fluid work on the rotor disk via the buckets.
  • 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 with platform structure disposed therebetween, said buckets receiving a driving force from 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 rotation of said turbine disk, means located radially inward of said platform structure for introducing liquid coolant within said turbine in a radially outward direction into openended coolant distribution circuits, each open-ended coolant distribution circuit comprising cooling channels extending beneath the airfoil surfaces of and in a generally radial direction along each of said buckets, metering means located beneath said platform structure in flow communication with said cooling channels and a manifold and discharge portion located in the .tip region of each of said buckets in flow communication with the
  • each conducting means is a tube having at least one protrusion at the discharge end thereof, said at least one protrusion being in contact with the base of the concavity in the underside of the platform structure.
  • each conducting means places an annular gutter in flow communication with the concavity in the underside of each platform structure, said annulargu'tter being located so as to receive liquid coolant from the means for introducing liquid coolant.
  • a poweraugmenting nozzle comprises the discharge portion of each open-ended coolant distribution circuit.
  • a rotor disk is mounted on a shaft rotatably supported in a casing, said rotor disk extending substantially perpendicular to the axis of said shaft and having buckets affixed to the outer rim thereof with platform structure disposed therebetween, means located radially inward of said platform structure for introducing liquid coolant within said rotor system in a radially outward direction into open-ended coolant distribution circuits, each openended coolant distribution circuit comprising subsurface cooling channels extending generally radially of each of said buckets and metering means located beneath said platform structure in flow communication with said cooling channels whereby coolant passes to the underside of said platform structure, is metering into and proceeds through said cooling channels and discharges from said cooling channels, the improvement comprising:
  • each conducting means is a tube having at least one protrusion at the discharge end thereof, said at least one protrusion being in contact with the base of the concavity in the underside of the platform structure.
  • each conducting means places an annular gutter in flow communication with the concavity in the underside of each platform structure, said annular gutter being located so as to receive liquid coolant from the means for introducing liquid coolant.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Motor Or Generator Cooling System (AREA)
  • Centrifugal Separators (AREA)
US00285633A 1972-09-01 1972-09-01 System for the introduction of coolant into open-circuit cooled turbine buckets Expired - Lifetime US3804551A (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
US00285633A US3804551A (en) 1972-09-01 1972-09-01 System for the introduction of coolant into open-circuit cooled turbine buckets
DE2336952A DE2336952C2 (de) 1972-09-01 1973-07-20 Flüssigkeitsgekühlte Gasturbine
NL7311237A NL7311237A (it) 1972-09-01 1973-08-15
GB3882373A GB1437618A (en) 1972-09-01 1973-08-16 Liquid cooled rotor system
NO3395/73A NO143880C (no) 1972-09-01 1973-08-29 Anordning ved et vaeskekjoelt rotorsystem.
FR7331421A FR2198052B1 (it) 1972-09-01 1973-08-30
IT28454/73A IT993116B (it) 1972-09-01 1973-08-31 Sistema per introdurre liquido refrigerante nelle palette di turbine raffreddate con liquido a circuito aperto
JP9740073A JPS5644241B2 (it) 1972-09-01 1973-08-31
SU731962218A SU670237A3 (ru) 1972-09-01 1973-08-31 Ротор с жидкостным охлаждением

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Application Number Priority Date Filing Date Title
US00285633A US3804551A (en) 1972-09-01 1972-09-01 System for the introduction of coolant into open-circuit cooled turbine buckets

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US3804551A true US3804551A (en) 1974-04-16

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US00285633A Expired - Lifetime US3804551A (en) 1972-09-01 1972-09-01 System for the introduction of coolant into open-circuit cooled turbine buckets

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US (1) US3804551A (it)
JP (1) JPS5644241B2 (it)
DE (1) DE2336952C2 (it)
FR (1) FR2198052B1 (it)
GB (1) GB1437618A (it)
IT (1) IT993116B (it)
NL (1) NL7311237A (it)
NO (1) NO143880C (it)
SU (1) SU670237A3 (it)

Cited By (33)

* 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
US4090810A (en) * 1977-03-23 1978-05-23 General Electric Company Liquid-cooled turbine bucket with enhanced heat transfer performance
US4119390A (en) * 1976-11-19 1978-10-10 General Electric Company Liquid-cooled, turbine bucket with enhanced heat transfer performance
US4130373A (en) * 1976-11-15 1978-12-19 General Electric Company Erosion suppression for liquid-cooled gas turbines
US4212587A (en) * 1978-05-30 1980-07-15 General Electric Company Cooling system for a gas turbine using V-shaped notch weirs
US4242045A (en) * 1979-06-01 1980-12-30 General Electric Company Trap seal for open circuit liquid cooled turbines
US4244676A (en) * 1979-06-01 1981-01-13 General Electric Company Cooling system for a gas turbine using a cylindrical insert having V-shaped notch weirs
US4260336A (en) * 1978-12-21 1981-04-07 United Technologies Corporation Coolant flow control apparatus for rotating heat exchangers with supercritical fluids
US4350473A (en) * 1980-02-22 1982-09-21 General Electric Company Liquid cooled counter flow turbine bucket
US4512715A (en) * 1980-07-22 1985-04-23 Electric Power Research Institute, Inc. Method and means for recapturing coolant in a gas turbine
US4531889A (en) * 1980-08-08 1985-07-30 General Electric Co. Cooling system utilizing flow resistance devices to distribute liquid coolant to air foil distribution channels
US4543781A (en) * 1981-06-17 1985-10-01 Rice Ivan G Annular combustor for gas turbine
US4545197A (en) * 1978-10-26 1985-10-08 Rice Ivan G Process for directing a combustion gas stream onto rotatable blades of a gas turbine
US4565490A (en) * 1981-06-17 1986-01-21 Rice Ivan G Integrated gas/steam nozzle
US4835958A (en) * 1978-10-26 1989-06-06 Rice Ivan G Process for directing a combustion gas stream onto rotatable blades of a gas turbine
US5030060A (en) * 1988-10-20 1991-07-09 The United States Of America As Represented By The Secretary Of The Air Force Method and apparatus for cooling high temperature ceramic turbine blade portions
EP0860587A2 (en) * 1997-02-21 1998-08-26 Mitsubishi Heavy Industries, Ltd. Connector for the transfer of a cooling fluid from a rotor disc to a turbomachine blade
EP0890710A2 (en) * 1997-07-07 1999-01-13 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade steam cooling system
WO1999060253A1 (de) * 1998-05-18 1999-11-25 Siemens Aktiengesellschaft Gekühlte turbinenschaufelplattform
EP1087102A2 (en) * 1999-09-24 2001-03-28 General Electric Company Gas turbine bucket with impingement cooled platform
US6554570B2 (en) * 2000-08-12 2003-04-29 Rolls-Royce Plc Turbine blade support assembly and a turbine assembly
WO2004038179A1 (en) * 2002-10-24 2004-05-06 Pratt & Whitney Canada Corp. Passively cooled blade platform
US20050042096A1 (en) * 2001-12-10 2005-02-24 Kenneth Hall Thermally loaded component
US20100135772A1 (en) * 2006-08-17 2010-06-03 Siemens Power Generation, Inc. Turbine airfoil cooling system with platform cooling channels with diffusion slots
DE19926949B4 (de) * 1999-06-14 2011-01-05 Alstom Kühlungsanordnung für Schaufeln einer Gasturbine
CH704716A1 (de) * 2011-03-22 2012-09-28 Alstom Technology Ltd Rotorscheibe für eine Turbine sowie Rotor und Turbine mit einer solchen Rotorscheibe.
US8622701B1 (en) * 2011-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade platform with impingement cooling
US20160061043A1 (en) * 2014-09-03 2016-03-03 General Electric Company Turbine bucket
US20170114648A1 (en) * 2015-10-27 2017-04-27 General Electric Company Turbine bucket having cooling passageway
US9885243B2 (en) 2015-10-27 2018-02-06 General Electric Company Turbine bucket having outlet path in shroud
US9982542B2 (en) 2014-07-21 2018-05-29 United Technologies Corporation Airfoil platform impingement cooling holes
US10508554B2 (en) 2015-10-27 2019-12-17 General Electric Company Turbine bucket having outlet path in shroud
US20200332669A1 (en) * 2019-04-16 2020-10-22 Pratt & Whitney Canada Corp. Turbine stator outer shroud cooling fins

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US4111604A (en) * 1976-07-12 1978-09-05 General Electric Company Bucket tip construction for open circuit liquid cooled turbines
GB2082257B (en) * 1980-08-08 1984-02-15 Gen Electric Liquid coolant distribution systems for gas turbines
EP0340149B1 (en) * 1988-04-25 1993-05-19 United Technologies Corporation Dirt removal means for air cooled blades
DE19921644B4 (de) * 1999-05-10 2012-01-05 Alstom Kühlbare Schaufel für eine Gasturbine
DE19963099B4 (de) 1999-12-24 2014-01-02 Alstom Technology Ltd. Kühlluftbohrungen in Gasturbinenkomponenten

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DE1801475A1 (de) * 1968-10-05 1970-04-30 Daimler Benz Ag Turbinenschaufel
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US2991973A (en) * 1954-10-18 1961-07-11 Parsons & Marine Eng Turbine Cooling of bodies subject to a hot gas stream
US2931623A (en) * 1957-05-02 1960-04-05 Orenda Engines Ltd Gas turbine rotor assembly
US3446482A (en) * 1967-03-24 1969-05-27 Gen Electric Liquid cooled turbine rotor
US3446481A (en) * 1967-03-24 1969-05-27 Gen Electric Liquid cooled turbine rotor
DE1801475A1 (de) * 1968-10-05 1970-04-30 Daimler Benz Ag Turbinenschaufel
US3736071A (en) * 1970-11-27 1973-05-29 Gen Electric Bucket tip/collection slot combination for open-circuit liquid-cooled gas turbines

Cited By (44)

* 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
US4130373A (en) * 1976-11-15 1978-12-19 General Electric Company Erosion suppression for liquid-cooled gas turbines
US4119390A (en) * 1976-11-19 1978-10-10 General Electric Company Liquid-cooled, turbine bucket with enhanced heat transfer performance
US4090810A (en) * 1977-03-23 1978-05-23 General Electric Company Liquid-cooled turbine bucket with enhanced heat transfer performance
US4212587A (en) * 1978-05-30 1980-07-15 General Electric Company Cooling system for a gas turbine using V-shaped notch weirs
US4545197A (en) * 1978-10-26 1985-10-08 Rice Ivan G Process for directing a combustion gas stream onto rotatable blades of a gas turbine
US4835958A (en) * 1978-10-26 1989-06-06 Rice Ivan G Process for directing a combustion gas stream onto rotatable blades of a gas turbine
US4260336A (en) * 1978-12-21 1981-04-07 United Technologies Corporation Coolant flow control apparatus for rotating heat exchangers with supercritical fluids
US4242045A (en) * 1979-06-01 1980-12-30 General Electric Company Trap seal for open circuit liquid cooled turbines
US4244676A (en) * 1979-06-01 1981-01-13 General Electric Company Cooling system for a gas turbine using a cylindrical insert having V-shaped notch weirs
US4350473A (en) * 1980-02-22 1982-09-21 General Electric Company Liquid cooled counter flow turbine bucket
US4512715A (en) * 1980-07-22 1985-04-23 Electric Power Research Institute, Inc. Method and means for recapturing coolant in a gas turbine
US4531889A (en) * 1980-08-08 1985-07-30 General Electric Co. Cooling system utilizing flow resistance devices to distribute liquid coolant to air foil distribution channels
US4565490A (en) * 1981-06-17 1986-01-21 Rice Ivan G Integrated gas/steam nozzle
US4543781A (en) * 1981-06-17 1985-10-01 Rice Ivan G Annular combustor for gas turbine
US5030060A (en) * 1988-10-20 1991-07-09 The United States Of America As Represented By The Secretary Of The Air Force Method and apparatus for cooling high temperature ceramic turbine blade portions
EP0860587A2 (en) * 1997-02-21 1998-08-26 Mitsubishi Heavy Industries, Ltd. Connector for the transfer of a cooling fluid from a rotor disc to a turbomachine blade
EP0860587A3 (en) * 1997-02-21 2001-03-21 Mitsubishi Heavy Industries, Ltd. Connector for the transfer of a cooling fluid from a rotor disc to a turbomachine blade
EP0890710A2 (en) * 1997-07-07 1999-01-13 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade steam cooling system
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Also Published As

Publication number Publication date
DE2336952A1 (de) 1974-03-14
NO143880B (no) 1981-01-19
JPS4992413A (it) 1974-09-03
JPS5644241B2 (it) 1981-10-19
FR2198052B1 (it) 1974-11-08
IT993116B (it) 1975-09-30
GB1437618A (en) 1976-06-03
NL7311237A (it) 1974-03-05
FR2198052A1 (it) 1974-03-29
NO143880C (no) 1981-04-29
SU670237A3 (ru) 1979-06-25
DE2336952C2 (de) 1983-12-15

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