US3658439A - Metering of liquid coolant in open-circuit liquid-cooled gas turbines - Google Patents

Metering of liquid coolant in open-circuit liquid-cooled gas turbines Download PDF

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Publication number
US3658439A
US3658439A US93056A US3658439DA US3658439A US 3658439 A US3658439 A US 3658439A US 93056 A US93056 A US 93056A US 3658439D A US3658439D A US 3658439DA US 3658439 A US3658439 A US 3658439A
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Prior art keywords
turbine
coolant
buckets
platform
liquid
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Expired - Lifetime
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US93056A
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English (en)
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Paul H Kydd
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General Electric Co
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General Electric Co
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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
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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

  • PATENTEDAPR 25 I972 SHEET 2 BF 2 Paul MK 12') van 602- ydci is Attorney METERING F LIQUID COOLANT IN OPEN-CIRCUIT LIQUID-COOLED GAS TURBINES BACKGROUND OF THE INVENTION Structural arrangements for the liquid cooling of gas turbine buckets are shown in U.S. Pat. Nos. 3,446,481 Kydd. These patents are incorporated by reference.
  • open-circuit liquid cooling are particularly important for the capability offered thereby for 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 aboutlOO to 200 percent and in 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.
  • the heat flux to the turbine buckets is so high that it is necessary to have a great many coolant channels in each bucket to distribute the coolant uniformly over the bucket surface.
  • the channels will measure about 0.02 X 0.025 inch and be spaced from about 0.052 to 0.071 inch on center over different surface areas of the bucket for a total of about 50 coolant channels per bucket.
  • ultra high temperature gas turbines it is desirable to employ extremely high bucket tip speeds (e.g. l ,5 00-2,000 feet/second) in order to remove large amounts of energy per turbine stage.
  • FIG. 1 is a three-dimensional view partially in cut-away section displaying the relationship of the weir construction as part of individual platform elements relative to the lower ends of the coolant channels of the adjacent turbine bucket;
  • FIG. 2 shows the unified bucket/rotor disk rim construction in combination with improved bucket tip construction for the open-circuit system for cooling this structure and shows portions of the casing related to the bucket tip construction;
  • FIG. 3 is a section taken on line 3-3 of FIG. 2 and FIG. 4 is an offset section taken on line 4-4 of FIG. 3.
  • Turbine bucket consists of a sheet metal skin 11 affixed (e.g. by brazing) to investment cast hollow core 12 having inwith and terminate at a similar manifold (not shown) recessed into core 12. Near the trailing edge of bucket 10 a cross-over conduit (not shown) connects the manifold on the suction side with manifold 14.
  • the root end of core 11 consists of a number of finger-like projections, or tines, 19 of varying length. These projections 19 may present a generally rectangular profile as shown or each tine may be tapered toward the distal end thereof to present a generally triangular profile.
  • Rim 21 of turbine disk 22 has grooves 23 machined therein extending to various depths and having widths matching the different lengths and widths of bucket tines 19 such that tines 19 will fit snuggly into the completed grooves 23 in an interlocking relationship.
  • Triangularly shaped bucket tine profiles provide for improved stress distribution in the joints between tines I9 and grooves 23 in shear and in the tines in tension. However, the rectangular profiles are preferred for ease of manufacture.
  • 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 I9 and grooves 23 regardless of thermal expansion.
  • Conventional brazing alloys having melting points ranging from 700 to l,lO0 C. may be used.
  • Single metals, such as copper, may also be used.
  • the assembly (the 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 2 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 area on the upper surfaces thereof for attachment thereto of investment cast platform elements 26 having cooling channels 27 and 28 formed therein. Platform elements 26 may also be prepared by other methods, such as, by coining.
  • the cooling channels 27 are in juxtaposition with grooves 23 and cooling channels 28 interconnect the cooling channels 27 as shown.
  • the separating walls 29 between cooling channels 27 are dimensioned to coincide with the width of juxtaposed ribs 24.
  • the improved structure for metering of the liquid coolant is provided during the preparation of platform elements 26 by accurately grinding each edge rib 31 to the radius of the outer diameter of the ribs 24 thereby providing a cylindrical surface (the elements of which extend in the axial direction) following bucket 10 on each side thereof adjacent the cooling channels 13.
  • all portions of those cylindrical surfaces receiving coolant from a common distribution path must be accurately located equidistant from the axis of rotation.
  • these edge ribs 31 will function a weirs over which the cooling fluid can distribute uniformly into the bucket cooling channels 13 of each bucket uniform sheet.
  • Ribs 24 are each provided with relief cuts 24a to ensure a clear supply path for the coolant along the length of ribs 31 to grooves 13a leading to channels 13.
  • Platform elements 26 are affixed to the rotor rim by the electron beam welding of separating walls 29 to ribs 24 after previously grinding the distal face of each wall 29 to a radius common to the outer diameter of ribs 24.
  • platform construction shown herein consists of individual platform elements prepared separate from buckets 10 and from each other, other constructions are equally feasible.
  • the platform components may be made integral with each bucket or a single continuous platform having holes cut therein to accommodate buckets 10 may be used.
  • 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 (now 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 accumulates in gutters 32, 32a (cooling the rim portions with which it comes into contact) being retained therein until this liquid has accelerated to the prevailing disk rim velocity.
  • lt is critical that the portions of gutters 32, 32a draining into holes 34, 34a be machined to very close tolerances to ensure equidistance thereof from the center of rotation whereby coolant distribution to holes 34, 34a will be substantially equal.
  • a set of six holes 34 provides the coolant for the coolant channels in the suction side of one bucket and in the adjacent pressure side of the next bucket.
  • the pair of edge ribs 31 receiving coolant from such a common source of holes 34 (regardless of whether they are formed in the same platform element as shown herein, or not) must present weir surfaces all points along which are equidistant from the center of rotation to ensure equal distribution of coolant.
  • cooling liquid moves through cooling channels 13 of any given bucket a large portion) or substantially all of the cooling fluid, depending upon the rate of flow) is converted to the gaseous or vapor state as it absorbs heat from the skin ll and core 12 of the bucket.
  • cooling chan nels 13 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 manifold is merged with the flow in manifold 14 and the combined flows exit therefrom via opening 16 into collection slot 17 to complete the opencircuit cooling path.
  • radius of the outer diameter of ribs 24 may be employed, if desired, so long as all portions of those cylindrical surfaces receiving coolant from a common upstream distribution path are located equidistant from the axis of rotation.
  • each cooling channel must extend to a location adjacent the straight weir, so that the liquid coolant traversing the accurated ground cylindrical surface of the weir (located in accordance with this invention) will be fed directly to the coolant channels or extensions thereof.
  • 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 and platform means affixed to the outer rim thereof, 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 platform adjacent said turbine disk for introducing liquid coolant within said turbine in a radially outward direction into open-circuit distribution paths by which said coolant traverses surface area of said rim and said platform means, passes into cooling channels in said buckets and exits from said channels in a radially outward direction, the improvement comprising:

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Separation By Low-Temperature Treatments (AREA)
US93056A 1970-11-27 1970-11-27 Metering of liquid coolant in open-circuit liquid-cooled gas turbines Expired - Lifetime US3658439A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US9305670A 1970-11-27 1970-11-27

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Country Status (8)

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US (1) US3658439A (de)
JP (1) JPS5514241B1 (de)
DE (1) DE2158242C3 (de)
FR (1) FR2115419B1 (de)
GB (1) GB1327317A (de)
IT (1) IT941373B (de)
NL (1) NL169770C (de)
NO (1) NO134226C (de)

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3816022A (en) * 1972-09-01 1974-06-11 Gen Electric Power augmenter bucket tip construction for open-circuit liquid cooled turbines
US3844679A (en) * 1973-03-28 1974-10-29 Gen Electric Pressurized serpentine cooling channel construction for open-circuit liquid cooled turbine buckets
US3849025A (en) * 1973-03-28 1974-11-19 Gen Electric Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets
US3856433A (en) * 1973-08-02 1974-12-24 Gen Electric Liquid cooled turbine bucket with dovetailed attachment
US3967353A (en) * 1974-07-18 1976-07-06 General Electric Company Gas turbine bucket-root sidewall piece seals
US4017210A (en) * 1976-02-19 1977-04-12 General Electric Company Liquid-cooled turbine bucket with integral distribution and metering system
US4111604A (en) * 1976-07-12 1978-09-05 General Electric Company Bucket tip construction for open circuit liquid cooled turbines
US4212587A (en) * 1978-05-30 1980-07-15 General Electric Company Cooling system for a gas turbine using V-shaped notch weirs
US4218178A (en) * 1978-03-31 1980-08-19 General Motors Corporation Turbine vane structure
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
US4285634A (en) * 1978-08-09 1981-08-25 Motoren-Und Turbinen-Union Munchen Gmbh Composite ceramic gas turbine blade
FR2488327A1 (fr) * 1980-08-08 1982-02-12 Gen Electric Systeme perfectionne de refroidissement par agent liquide des aubes d'une turbine a gaz
US4453888A (en) * 1981-04-01 1984-06-12 United Technologies Corporation Nozzle for a coolable rotor blade
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
US4784572A (en) * 1987-10-14 1988-11-15 United Technologies Corporation Circumferentially bonded rotor
US4813848A (en) * 1987-10-14 1989-03-21 United Technologies Corporation Turbine rotor disk and blade assembly
US5122033A (en) * 1990-11-16 1992-06-16 Paul Marius A Turbine blade unit
US5177954A (en) * 1984-10-10 1993-01-12 Paul Marius A Gas turbine engine with cooled turbine blades
GB2411697A (en) * 2004-03-06 2005-09-07 Rolls Royce Plc Cooling arrangement for rim of turbine disc.
CN101852095A (zh) * 2010-04-16 2010-10-06 沈泉贵 转子内扩容汽轮机
US8047789B1 (en) 2007-10-19 2011-11-01 Florida Turbine Technologies, Inc. Turbine airfoil
US8366394B1 (en) * 2010-10-21 2013-02-05 Florida Turbine Technologies, Inc. Turbine blade with tip rail cooling channel
RU2500893C1 (ru) * 2012-08-07 2013-12-10 Открытое акционерное общество "Всероссийский дважды ордена Трудового Красного Знамени теплотехнический научно-исследовательский институт" Система жидкостного охлаждения лопаток высокотемпературных ступеней энергетической газовой турбины
US20160061043A1 (en) * 2014-09-03 2016-03-03 General Electric Company Turbine bucket
US20160153284A1 (en) * 2010-12-24 2016-06-02 Rolls-Royce North American Technologies, Inc. Gas turbine engine flow path member
US20170044903A1 (en) * 2015-08-13 2017-02-16 General Electric Company Rotating component for a turbomachine and method for providing cooling of a rotating component
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
US20190120064A1 (en) * 2017-10-24 2019-04-25 United Technologies Corporation Airfoil cooling circuit
US10508554B2 (en) 2015-10-27 2019-12-17 General Electric Company Turbine bucket having outlet path in shroud

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3804551A (en) * 1972-09-01 1974-04-16 Gen Electric System for the introduction of coolant into open-circuit cooled turbine buckets
GB2259118B (en) * 1991-08-24 1995-06-21 Rolls Royce Plc Aerofoil cooling

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2991973A (en) * 1954-10-18 1961-07-11 Parsons & Marine Eng Turbine Cooling of bodies subject to a hot gas stream
US3446482A (en) * 1967-03-24 1969-05-27 Gen Electric Liquid cooled turbine rotor

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3446481A (en) * 1967-03-24 1969-05-27 Gen Electric Liquid cooled turbine rotor

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2991973A (en) * 1954-10-18 1961-07-11 Parsons & Marine Eng Turbine Cooling of bodies subject to a hot gas stream
US3446482A (en) * 1967-03-24 1969-05-27 Gen Electric Liquid cooled turbine rotor

Cited By (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3816022A (en) * 1972-09-01 1974-06-11 Gen Electric Power augmenter bucket tip construction for open-circuit liquid cooled turbines
US3844679A (en) * 1973-03-28 1974-10-29 Gen Electric Pressurized serpentine cooling channel construction for open-circuit liquid cooled turbine buckets
US3849025A (en) * 1973-03-28 1974-11-19 Gen Electric Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets
US3856433A (en) * 1973-08-02 1974-12-24 Gen Electric Liquid cooled turbine bucket with dovetailed attachment
US3967353A (en) * 1974-07-18 1976-07-06 General Electric Company Gas turbine bucket-root sidewall piece seals
US4017210A (en) * 1976-02-19 1977-04-12 General Electric Company Liquid-cooled turbine bucket with integral distribution and metering system
US4111604A (en) * 1976-07-12 1978-09-05 General Electric Company Bucket tip construction for open circuit liquid cooled turbines
US4218178A (en) * 1978-03-31 1980-08-19 General Motors Corporation Turbine vane structure
US4212587A (en) * 1978-05-30 1980-07-15 General Electric Company Cooling system for a gas turbine using V-shaped notch weirs
US4285634A (en) * 1978-08-09 1981-08-25 Motoren-Und Turbinen-Union Munchen Gmbh Composite ceramic gas turbine blade
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
FR2488327A1 (fr) * 1980-08-08 1982-02-12 Gen Electric Systeme perfectionne de refroidissement par agent liquide des aubes d'une turbine a gaz
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
US4453888A (en) * 1981-04-01 1984-06-12 United Technologies Corporation Nozzle for a coolable rotor blade
US5177954A (en) * 1984-10-10 1993-01-12 Paul Marius A Gas turbine engine with cooled turbine blades
US4784572A (en) * 1987-10-14 1988-11-15 United Technologies Corporation Circumferentially bonded rotor
US4813848A (en) * 1987-10-14 1989-03-21 United Technologies Corporation Turbine rotor disk and blade assembly
US5122033A (en) * 1990-11-16 1992-06-16 Paul Marius A Turbine blade unit
GB2411697A (en) * 2004-03-06 2005-09-07 Rolls Royce Plc Cooling arrangement for rim of turbine disc.
GB2411697B (en) * 2004-03-06 2006-06-21 Rolls Royce Plc A turbine having a cooling arrangement
US7374400B2 (en) 2004-03-06 2008-05-20 Rolls-Royce Plc Turbine blade arrangement
US20050196278A1 (en) * 2004-03-06 2005-09-08 Rolls-Royce Plc Turbine blade arrangement
US8047789B1 (en) 2007-10-19 2011-11-01 Florida Turbine Technologies, Inc. Turbine airfoil
CN101852095A (zh) * 2010-04-16 2010-10-06 沈泉贵 转子内扩容汽轮机
CN101852095B (zh) * 2010-04-16 2012-12-26 沈泉贵 转子内扩容汽轮机
US8366394B1 (en) * 2010-10-21 2013-02-05 Florida Turbine Technologies, Inc. Turbine blade with tip rail cooling channel
US20160153284A1 (en) * 2010-12-24 2016-06-02 Rolls-Royce North American Technologies, Inc. Gas turbine engine flow path member
US9982541B2 (en) * 2010-12-24 2018-05-29 Rolls-Royce North American Technologies Inc. Gas turbine engine flow path member
RU2500893C1 (ru) * 2012-08-07 2013-12-10 Открытое акционерное общество "Всероссийский дважды ордена Трудового Красного Знамени теплотехнический научно-исследовательский институт" Система жидкостного охлаждения лопаток высокотемпературных ступеней энергетической газовой турбины
US9835087B2 (en) * 2014-09-03 2017-12-05 General Electric Company Turbine bucket
US20160061043A1 (en) * 2014-09-03 2016-03-03 General Electric Company Turbine bucket
US20170044903A1 (en) * 2015-08-13 2017-02-16 General Electric Company Rotating component for a turbomachine and method for providing cooling of a rotating component
US9885243B2 (en) 2015-10-27 2018-02-06 General Electric Company Turbine bucket having outlet path in shroud
US20170114648A1 (en) * 2015-10-27 2017-04-27 General Electric Company Turbine bucket having cooling passageway
US10156145B2 (en) * 2015-10-27 2018-12-18 General Electric Company Turbine bucket having cooling passageway
US10508554B2 (en) 2015-10-27 2019-12-17 General Electric Company Turbine bucket having outlet path in shroud
US11078797B2 (en) 2015-10-27 2021-08-03 General Electric Company Turbine bucket having outlet path in shroud
US20190120064A1 (en) * 2017-10-24 2019-04-25 United Technologies Corporation Airfoil cooling circuit
US11480057B2 (en) * 2017-10-24 2022-10-25 Raytheon Technologies Corporation Airfoil cooling circuit

Also Published As

Publication number Publication date
FR2115419A1 (de) 1972-07-07
NO134226C (de) 1976-09-01
IT941373B (it) 1973-03-01
GB1327317A (en) 1973-08-22
NL169770C (nl) 1982-08-16
JPS5514241B1 (de) 1980-04-15
FR2115419B1 (de) 1976-03-26
NL7116204A (de) 1972-05-30
DE2158242B2 (de) 1980-05-08
DE2158242A1 (de) 1972-05-31
NL169770B (nl) 1982-03-16
DE2158242C3 (de) 1981-01-08
NO134226B (de) 1976-05-24

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