GB1161297A - Turbomachine Rotors - Google Patents

Turbomachine Rotors

Info

Publication number
GB1161297A
GB1161297A GB38971/67A GB3897167A GB1161297A GB 1161297 A GB1161297 A GB 1161297A GB 38971/67 A GB38971/67 A GB 38971/67A GB 3897167 A GB3897167 A GB 3897167A GB 1161297 A GB1161297 A GB 1161297A
Authority
GB
United Kingdom
Prior art keywords
rim
liner
passages
holes
blades
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
Application number
GB38971/67A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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 Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB1161297A publication Critical patent/GB1161297A/en
Expired legal-status Critical Current

Links

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—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
    • F01D5/187—Convection 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,161,297. Turbine rotors. GENERAL MOTORS CORP. Aug.24, 1967 [Dec. 19, 1966], No.38971/67. Heading F1T. Blades 14 are retained on a gas turbine or like rotor 7 by the sliding engagement of the root portions of the blades in aerofoil shaped holes 17 passing through the rotor rim 10 and by two circumferentially extending locking rings 33, 34 passing through holes 31, 32 in the blade roots and engaging grooves 35, 36 in the rim 10. Annular cover plates 41, 42 bolted to the faces of the rotor 7 have lugs (91, 92, Fig. 4, not shown), which engage gaps (38) in the respective rings 33, 34 to prevent circumferential movement of the rings. The upstream plate 41 is ribbed at 47 to define passages 49 for the flow of cooling air from a pipe 51 to an annular chamber 59. A portion of this air flows from chamber 59 through ports 65 to an annular chamber 66 defined between the rim 10 and a thin sheet metal ring 62 welded to the rim. Projections 61 on the ring 62 or rim 10 assist cooling as the air flows from chamber 66 to exhaust through ports 67 in the ring 62 adjacent the blade trailing edges. Leakage of air is prevented by continuous lands 68 around the aerofoil holes 17. A further portion of the air flows from chamber 59 through passages 60 in the rim 10 to enter the interiors of the blades 14 through gaps 24 between the two parts 21, 21' of root blocks mounted within the blades. Each blade comprises a liner 19 around which is wrapped an outer skin 18 spaced therefrom by projections 71 to form passages 85. The tip of the liner 19 is closed (at 77, Fig. 2, not shown), so that the cooling air entering the liner through gap 24 flows through radially spaced holes 78 at the leading edge of the liner to impinge upon the skin 18 before flowing rearwardly through passages 85 to exit through slots 82 at the blade trailing edge. The tip of the skin 18 is open so that some air from passages 85 exhausts through the tip past radial ribs (73) on the skin. Holes corresponding to 78 may also be provided in the liner 19 adjacent the trailing edge.
GB38971/67A 1966-12-19 1967-08-24 Turbomachine Rotors Expired GB1161297A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US60279566A 1966-12-19 1966-12-19

Publications (1)

Publication Number Publication Date
GB1161297A true GB1161297A (en) 1969-08-13

Family

ID=24412840

Family Applications (2)

Application Number Title Priority Date Filing Date
GB3972/67A Expired GB1161298A (en) 1966-12-19 1967-08-24 Turbomachine Rotors
GB38971/67A Expired GB1161297A (en) 1966-12-19 1967-08-24 Turbomachine Rotors

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GB3972/67A Expired GB1161298A (en) 1966-12-19 1967-08-24 Turbomachine Rotors

Country Status (3)

Country Link
US (1) US3446480A (en)
DE (1) DE1601568A1 (en)
GB (2) GB1161298A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996006266A1 (en) * 1994-08-24 1996-02-29 Westinghouse Electric Corporation Gas turbine blade with cooled platform

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1801475B2 (en) * 1968-10-05 1971-08-12 Daimler Benz Ag, 7000 Stuttgart AIR-COOLED TURBINE BLADE
US3619076A (en) * 1970-02-02 1971-11-09 Gen Electric Liquid-cooled turbine bucket
US3697192A (en) * 1970-05-07 1972-10-10 United Aircraft Corp Hollow turbine blade
US3747182A (en) * 1970-05-07 1973-07-24 United Aircraft Corp Method of fabricating a hollow turbine blade having an insert therein
US3709632A (en) * 1971-02-12 1973-01-09 Gen Motors Corp Blade tip closure
US3709631A (en) * 1971-03-18 1973-01-09 Caterpillar Tractor Co Turbine blade seal arrangement
US3846041A (en) * 1972-10-31 1974-11-05 Avco Corp Impingement cooled turbine blades and method of making same
US3858290A (en) * 1972-11-21 1975-01-07 Avco Corp Method of making inserts for cooled turbine blades
GB1550368A (en) * 1975-07-16 1979-08-15 Rolls Royce Laminated materials
WO1999060253A1 (en) * 1998-05-18 1999-11-25 Siemens Aktiengesellschaft Cooled turbine blade platform
EP1923536A1 (en) * 2006-11-17 2008-05-21 Siemens Aktiengesellschaft Liner in a cooling channel of a turbine blade
EP2706242A1 (en) * 2012-09-11 2014-03-12 Techspace Aero S.A. Fixing of blades on an axial compressor drum
EP2735707B1 (en) * 2012-11-27 2017-04-05 Safran Aero Boosters SA Axial turbomachine guide nozzle with segmented inner shroud and corresponding compressor
EP3232001A1 (en) * 2016-04-15 2017-10-18 Siemens Aktiengesellschaft Rotor blade for a turbine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2601969A (en) * 1946-01-25 1952-07-01 United Specialties Co Turbine wheel
US2779565A (en) * 1948-01-05 1957-01-29 Bruno W Bruckmann Air cooling of turbine blades
US2840299A (en) * 1952-09-22 1958-06-24 Thompson Prod Inc Axial flow compressor rotor
BE551145A (en) * 1955-09-26
US2888243A (en) * 1956-10-22 1959-05-26 Pollock Robert Stephen Cooled turbine blade

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996006266A1 (en) * 1994-08-24 1996-02-29 Westinghouse Electric Corporation Gas turbine blade with cooled platform

Also Published As

Publication number Publication date
US3446480A (en) 1969-05-27
DE1601568A1 (en) 1970-08-27
GB1161298A (en) 1969-08-13

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees