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GB1014577A - Gas turbine rotor assembly - Google Patents

Gas turbine rotor assembly

Info

Publication number
GB1014577A
GB1014577A GB31902/64A GB3190264A GB1014577A GB 1014577 A GB1014577 A GB 1014577A GB 31902/64 A GB31902/64 A GB 31902/64A GB 3190264 A GB3190264 A GB 3190264A GB 1014577 A GB1014577 A GB 1014577A
Authority
GB
United Kingdom
Prior art keywords
blades
rotor
shanks
baffle plates
rotor wheel
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
GB31902/64A
Inventor
Doris Jean Harlow
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
Priority to US161736A priority Critical patent/US3266770A/en
Application filed by General Electric Co filed Critical General Electric Co
Priority to GB31902/64A priority patent/GB1014577A/en
Priority to FR984484A priority patent/FR1426933A/en
Publication of GB1014577A publication Critical patent/GB1014577A/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and 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
    • F01D5/02—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
    • F01D5/12—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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

1,014,577. Gas turbine engines. GENERAL ELECTRIC CO. Aug. 5, 1964, No. 31902/64. Headings F1G and FIT. A turbo-machine rotor assembly includes a rotor wheel supporting a plurality of blades, each comprising shank and vane portions between which is a platform; adjacent platforms abut each other, and baffles are secured to the wheel on the up- and downstream sides of the shanks to prevent axial gas flow between the shanks; the baffle plates on one side of the shanks are spaced from the rotor wheel to provide a passage for coolant fluid flow into chambers formed by the shanks and baffle plates, the coolant passing from these chambers to internal cooling passages in the blades; the baffle plates on opposite sides of the rotor wheel are interconnected by damper pins, which seal the joints between adjacent platforms, and which also damp vibrations of the blades. The invention relates particular to aircraft gas turbines. As seen in Fig. 1, the blades are mounted in pairs, each pair of roots 12, 14 sharing a common dovetail 32. The baffles 25, 26 are held by bolts 30 (Fig. 2) at their lower ends, and are spaced from the rotor wheel face by bosses to allow coolant to pass from the space 50 to the blades. The damper pins 41 have a control portion of semi-circular cross section, and end faces of circular form, carrying an elongate diametral shoulder (43 in Fig. 5, not shown); these shoulders engage in elongate slots 40 in the baffle plate peripheries. When nuts are fully tightened on threads 44, the baffle plates are constrained axially, but the damper pins are free to move radially under centrifugal loading. Thus when the rotor is running, the curved surfaces of the damper pins are pressed into tight sealing engagement with the joints between adjacent blades belonging to adjacent pairs. In addition, since the damper pins are loose, and in rubbing contact with the blade at a point well clear of its rigid end, they act as dampers of blade vibration. Since there are no small coolant passages through the rotor wheel, the expense of replacing clogged rotor wheels is avoided.
GB31902/64A 1961-12-22 1964-08-05 Gas turbine rotor assembly Expired GB1014577A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US161736A US3266770A (en) 1961-12-22 1961-12-22 Turbomachine rotor assembly
GB31902/64A GB1014577A (en) 1964-08-05 1964-08-05 Gas turbine rotor assembly
FR984484A FR1426933A (en) 1964-08-05 1964-08-07 Improvements to turbomachine rotors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB31902/64A GB1014577A (en) 1964-08-05 1964-08-05 Gas turbine rotor assembly

Publications (1)

Publication Number Publication Date
GB1014577A true GB1014577A (en) 1965-12-31

Family

ID=10330095

Family Applications (1)

Application Number Title Priority Date Filing Date
GB31902/64A Expired GB1014577A (en) 1961-12-22 1964-08-05 Gas turbine rotor assembly

Country Status (1)

Country Link
GB (1) GB1014577A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0731254A1 (en) * 1995-03-06 1996-09-11 Solar Turbines Incorporated Nozzle and shroud mounting structure
EP2146051A1 (en) * 2008-07-17 2010-01-20 Ansaldo Energia S.P.A. Rotor assembly for a gas turbine, gas turbine including said rotor assembly and method for cooling said rotor assembly
US20160177727A1 (en) * 2013-12-20 2016-06-23 Rolls-Royce Deutschland Ltd & Co Kg Vibration damper
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0731254A1 (en) * 1995-03-06 1996-09-11 Solar Turbines Incorporated Nozzle and shroud mounting structure
US5653580A (en) * 1995-03-06 1997-08-05 Solar Turbines Incorporated Nozzle and shroud assembly mounting structure
EP2146051A1 (en) * 2008-07-17 2010-01-20 Ansaldo Energia S.P.A. Rotor assembly for a gas turbine, gas turbine including said rotor assembly and method for cooling said rotor assembly
US20160177727A1 (en) * 2013-12-20 2016-06-23 Rolls-Royce Deutschland Ltd & Co Kg Vibration damper
US10100643B2 (en) * 2013-12-20 2018-10-16 Rolls-Royce Deutschland Ltd & Co Kg Vibration damper
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

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