US3619076A - Liquid-cooled turbine bucket - Google Patents

Liquid-cooled turbine bucket Download PDF

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Publication number
US3619076A
US3619076A US7805A US3619076DA US3619076A US 3619076 A US3619076 A US 3619076A US 7805 A US7805 A US 7805A US 3619076D A US3619076D A US 3619076DA US 3619076 A US3619076 A US 3619076A
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US
United States
Prior art keywords
spar
cooled turbine
cladding
fluid
cladding means
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
US7805A
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English (en)
Inventor
Paul H Kydd
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
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Publication of US3619076A publication Critical patent/US3619076A/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
    • 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

  • Each blade consists of a central airfoil-shaped spar clad with a sheet of metal having a very high thermal conductivity e.g. copper.
  • the cladding sheet has grooves recessed in the sheet face adjacent the spar, which grooves together with the surface ofthe spar define coolant passages distributed over the surface as dictated by the cooling requirements,
  • Each blade of the instant invention consists of a central airfoil-shaped spar with its outer surface covered with a sheet of metal having a very high thermal conductivity, such as copper.
  • This covering sheet, or cladding has grooves recessed in the face thereof, which is disposed contiguous with and bonded to the outer surface of the spar. These grooves define coolant passages distributed over and close to the surface of the composite blade as dictated by the cooling requirements. These passages are in flow communication with a supply of coolant liquid at the radially inward terminals thereof, the radially outward terminals thereof being open for the discharge of the coolant.
  • FIG. 1 is a transverse sectional view through a liquid-cooled gas turbine showing the rotor disc supporting a turbine bucket constructed in accordance with this invention
  • FIG. 2 is a sectional view taken on line 2-2 of FIG. 1 and FIG. 3 is a sectional view taken on line 33 of FIG. 2.
  • FIG. 1 there is shown part of a gas turbine structure including rotor shaft 11 affixed to the turbine rotor 12 projecting radially from the shaft axis.
  • rotor 12 is composed of three sections; hub 13, rim section 14 and a tapered connecting section 16 between the hub and rim sections.
  • the rim section 14 has a series of transverse recesses 17 formed therein, each of which receives the dovetailing root 18 of a turbine bucket, or blade 19.
  • Cooling action is accomplished in accordance with this invention by spraying a liquid coolant, generally water, at low pressure onto the turbine disc from stationary cooling noules 21, 22 supported on stationary annular discs 23, 24, respectively.
  • a liquid coolant generally water
  • the low pressure water leaving nozzles 21, 22 impinges on the sides of disc 12 in the vicinity of rim section 14 and over the underside of platform portions 26 of each spar 27.
  • each spar 27 is covered by a sheath (about 0.020 inch to about 0.050 inch thick) of a metal such as copper, having very high thermal conductivity.
  • This sheath or cladding also extends down over the upper face of platform portions 26 to provide skirt portions 29 projecting therebelow.
  • the complex shape of this cladding element is preferably formed in two portions 30, 31. These individual parts may be made in a stamping operation providing both the outside surface configuration and the recesses described hereinbelow.
  • the cladding material should be a metal (or alloy) susceptible of stamp forming and having a coefficient of thermal conductivity in excess of about 0.10 caL/cm. degree C.
  • the cladding material will have a coefficient of thermal conductivity in excess of about 0.5 caL/cm. sec. degree C, e.g. copper or aluminum.
  • Skirt portions 29 together with the underside of platform portions 26 define a gutter region 32, which accumulates cooling water nozzles 21, 22.
  • the accumulating liquid cools parts with which it comes in contact while it is retained until it has been accelerated to the prevailing disc rim velocity.
  • this water continually drains from gutter regions 32 in a generally radially outward direction along coolant passages 33 under the influence of centrifugal force to be finally discharged through the open ends 34 thereof.
  • coolant passages 33 may be either in a nonuniform or a uniform arrangement depending upon the cooling requirements. Further, coolant passages 33 need not all have the same transverse cross-sectional area but may be of different sizes to accomplish specific cooling requirements.
  • the passage of cooling water from gutter regions 32 to coolant passages 33 is, of course, controlled by the openings to passages 33 and in this manner these coolant passages serve as their own metering orifices.
  • Each conduit passage 33 consists of a groove recessed in sheets 30, 31 in cooperation with the surface of spar 27 to which cladding sheets 30, 31 are bonded.
  • Adjacent grooves recessed in the inner surface of cladding elements 30, 31 are separated by ribs 36.
  • the outer face of ribs 36 and the outer surface of spar 27 are preferably coated with a brazing metal or alloy.
  • the parts are integrally united through a bond at each rib 36.
  • the bond between cladding elements 30, 31 and spar 27 may be made in other ways, of course, as by welding, soldering, cementing or diffusion bonding.
  • cladding 30, 31 is made of copper sheet
  • the cladding elements and the outer faces of ribs 36 and the surfaces of the spar are gold plated and then brazed together by heating under pressure in a hydrogen furnace.
  • each passageway 33 is made of material having a very high thermal conductivity and the cooling of the outer surface of each bucket 19 is very effective, even when the coolant liquid becomes forced to one side of each passage 33 by body forces during the rotation of the turbine rotor.
  • a fluid-cooled turbine bucket comprising in combination:
  • cladding means covering said stem portion and platform portion extending over the pressure side of said stem portion, the suction side of said stem portion, and the upper face of said platform portion and projecting as a skirt below said platform portion,
  • said cladding means having a plurality of grooves open at both ends and separated by ribs, said grooves being recessed in the inner face of said cladding means and extending from below said platform portion to the distal end of said stem portion,

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US7805A 1970-02-02 1970-02-02 Liquid-cooled turbine bucket Expired - Lifetime US3619076A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US780570A 1970-02-02 1970-02-02

Publications (1)

Publication Number Publication Date
US3619076A true US3619076A (en) 1971-11-09

Family

ID=21728216

Family Applications (1)

Application Number Title Priority Date Filing Date
US7805A Expired - Lifetime US3619076A (en) 1970-02-02 1970-02-02 Liquid-cooled turbine bucket

Country Status (6)

Country Link
US (1) US3619076A (enrdf_load_stackoverflow)
JP (1) JPS545048B1 (enrdf_load_stackoverflow)
DE (1) DE2104482C3 (enrdf_load_stackoverflow)
FR (1) FR2080425A5 (enrdf_load_stackoverflow)
GB (1) GB1307338A (enrdf_load_stackoverflow)
NL (1) NL169627C (enrdf_load_stackoverflow)

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3936227A (en) * 1973-08-02 1976-02-03 General Electric Company Combined coolant feed and dovetailed bucket retainer ring
US3950113A (en) * 1968-10-05 1976-04-13 Daimler-Benz Aktiengesellschaft Turbine blade
US3980411A (en) * 1975-10-20 1976-09-14 United Technologies Corporation Aerodynamic seal for a rotary machine
US4090810A (en) * 1977-03-23 1978-05-23 General Electric Company Liquid-cooled turbine bucket with enhanced heat transfer performance
US4111604A (en) * 1976-07-12 1978-09-05 General Electric Company Bucket tip construction for open circuit liquid cooled turbines
US4119390A (en) * 1976-11-19 1978-10-10 General Electric Company Liquid-cooled, turbine bucket with enhanced heat transfer performance
US4134709A (en) * 1976-08-23 1979-01-16 General Electric Company Thermosyphon liquid cooled turbine bucket
DE2842688A1 (de) * 1977-10-03 1979-04-05 Gen Electric Verfahren zum herstellen zusammengesetzter strukturen fuer wassergekuehlte gasturbinen-komponenten
US4156582A (en) * 1976-12-13 1979-05-29 General Electric Company Liquid cooled gas turbine buckets
US4158526A (en) * 1978-01-09 1979-06-19 General Electric Company Turbine assembly including a rotatable liquid collection ring
US4185369A (en) * 1978-03-22 1980-01-29 General Electric Company Method of manufacture of cooled turbine or compressor buckets
US4653983A (en) * 1985-12-23 1987-03-31 United Technologies Corporation Cross-flow film cooling passages
US4664597A (en) * 1985-12-23 1987-05-12 United Technologies Corporation Coolant passages with full coverage film cooling slot
US4666368A (en) * 1986-05-01 1987-05-19 General Electric Company Swirl nozzle for a cooling system in gas turbine engines
US4669957A (en) * 1985-12-23 1987-06-02 United Technologies Corporation Film coolant passage with swirl diffuser
US4676719A (en) * 1985-12-23 1987-06-30 United Technologies Corporation Film coolant passages for cast hollow airfoils
US4684323A (en) * 1985-12-23 1987-08-04 United Technologies Corporation Film cooling passages with curved corners
US4705455A (en) * 1985-12-23 1987-11-10 United Technologies Corporation Convergent-divergent film coolant passage
US4726735A (en) * 1985-12-23 1988-02-23 United Technologies Corporation Film cooling slot with metered flow
US4738588A (en) * 1985-12-23 1988-04-19 Field Robert E Film cooling passages with step diffuser
WO1999060253A1 (de) * 1998-05-18 1999-11-25 Siemens Aktiengesellschaft Gekühlte turbinenschaufelplattform
US6565312B1 (en) * 2001-12-19 2003-05-20 The Boeing Company Fluid-cooled turbine blades
US6699015B2 (en) 2002-02-19 2004-03-02 The Boeing Company Blades having coolant channels lined with a shape memory alloy and an associated fabrication method
US20070280832A1 (en) * 2006-06-06 2007-12-06 Siemens Power Generation, Inc. Turbine airfoil with floating wall mechanism and multi-metering diffusion technique

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3211139C1 (de) * 1982-03-26 1983-08-11 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Axialturbinenschaufel,insbesondere Axialturbinenlaufschaufel fuer Gasturbinentriebwerke
FR2550978B1 (fr) * 1983-05-26 1989-10-13 Rolls Royce Procede d'application de revetements de surface sur des articles
US8858182B2 (en) 2011-06-28 2014-10-14 United Technologies Corporation Fan blade with sheath

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3075744A (en) * 1960-08-16 1963-01-29 United Aircraft Corp Turbine nozzle vane mounting means
US3446480A (en) * 1966-12-19 1969-05-27 Gen Motors Corp Turbine rotor
US3446481A (en) * 1967-03-24 1969-05-27 Gen Electric Liquid cooled turbine rotor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3075744A (en) * 1960-08-16 1963-01-29 United Aircraft Corp Turbine nozzle vane mounting means
US3446480A (en) * 1966-12-19 1969-05-27 Gen Motors Corp Turbine rotor
US3446481A (en) * 1967-03-24 1969-05-27 Gen Electric Liquid cooled turbine rotor

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3950113A (en) * 1968-10-05 1976-04-13 Daimler-Benz Aktiengesellschaft Turbine blade
US3936227A (en) * 1973-08-02 1976-02-03 General Electric Company Combined coolant feed and dovetailed bucket retainer ring
US3980411A (en) * 1975-10-20 1976-09-14 United Technologies Corporation Aerodynamic seal for a rotary machine
US4111604A (en) * 1976-07-12 1978-09-05 General Electric Company Bucket tip construction for open circuit liquid cooled turbines
US4134709A (en) * 1976-08-23 1979-01-16 General Electric Company Thermosyphon liquid cooled turbine bucket
US4119390A (en) * 1976-11-19 1978-10-10 General Electric Company Liquid-cooled, turbine bucket with enhanced heat transfer performance
US4156582A (en) * 1976-12-13 1979-05-29 General Electric Company Liquid cooled gas turbine buckets
US4090810A (en) * 1977-03-23 1978-05-23 General Electric Company Liquid-cooled turbine bucket with enhanced heat transfer performance
DE2842688A1 (de) * 1977-10-03 1979-04-05 Gen Electric Verfahren zum herstellen zusammengesetzter strukturen fuer wassergekuehlte gasturbinen-komponenten
FR2404486A1 (fr) * 1977-10-03 1979-04-27 Gen Electric Procede de fabrication d'une piece de turbine refroidie par eau
US4158526A (en) * 1978-01-09 1979-06-19 General Electric Company Turbine assembly including a rotatable liquid collection ring
US4185369A (en) * 1978-03-22 1980-01-29 General Electric Company Method of manufacture of cooled turbine or compressor buckets
US4653983A (en) * 1985-12-23 1987-03-31 United Technologies Corporation Cross-flow film cooling passages
US4726735A (en) * 1985-12-23 1988-02-23 United Technologies Corporation Film cooling slot with metered flow
US4738588A (en) * 1985-12-23 1988-04-19 Field Robert E Film cooling passages with step diffuser
US4669957A (en) * 1985-12-23 1987-06-02 United Technologies Corporation Film coolant passage with swirl diffuser
US4676719A (en) * 1985-12-23 1987-06-30 United Technologies Corporation Film coolant passages for cast hollow airfoils
US4684323A (en) * 1985-12-23 1987-08-04 United Technologies Corporation Film cooling passages with curved corners
US4705455A (en) * 1985-12-23 1987-11-10 United Technologies Corporation Convergent-divergent film coolant passage
US4664597A (en) * 1985-12-23 1987-05-12 United Technologies Corporation Coolant passages with full coverage film cooling slot
US4666368A (en) * 1986-05-01 1987-05-19 General Electric Company Swirl nozzle for a cooling system in gas turbine engines
WO1999060253A1 (de) * 1998-05-18 1999-11-25 Siemens Aktiengesellschaft Gekühlte turbinenschaufelplattform
US6565312B1 (en) * 2001-12-19 2003-05-20 The Boeing Company Fluid-cooled turbine blades
US6699015B2 (en) 2002-02-19 2004-03-02 The Boeing Company Blades having coolant channels lined with a shape memory alloy and an associated fabrication method
US6886622B2 (en) 2002-02-19 2005-05-03 The Boeing Company Method of fabricating a shape memory alloy damped structure
US20070280832A1 (en) * 2006-06-06 2007-12-06 Siemens Power Generation, Inc. Turbine airfoil with floating wall mechanism and multi-metering diffusion technique
US7488156B2 (en) 2006-06-06 2009-02-10 Siemens Energy, Inc. Turbine airfoil with floating wall mechanism and multi-metering diffusion technique

Also Published As

Publication number Publication date
DE2104482A1 (de) 1971-08-12
NL7100990A (enrdf_load_stackoverflow) 1971-08-04
DE2104482B2 (de) 1979-09-06
FR2080425A5 (enrdf_load_stackoverflow) 1971-11-12
NL169627B (nl) 1982-03-01
JPS545048B1 (enrdf_load_stackoverflow) 1979-03-13
DE2104482C3 (de) 1980-05-14
GB1307338A (en) 1973-02-21
NL169627C (nl) 1982-08-02

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