EP0437977A1 - Configuration de jante de disque de turbine - Google Patents

Configuration de jante de disque de turbine Download PDF

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Publication number
EP0437977A1
EP0437977A1 EP90314368A EP90314368A EP0437977A1 EP 0437977 A1 EP0437977 A1 EP 0437977A1 EP 90314368 A EP90314368 A EP 90314368A EP 90314368 A EP90314368 A EP 90314368A EP 0437977 A1 EP0437977 A1 EP 0437977A1
Authority
EP
European Patent Office
Prior art keywords
disk
blade
damper
blades
perimeter
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.)
Withdrawn
Application number
EP90314368A
Other languages
German (de)
English (en)
Inventor
Wesley D. Brown
James R. Mccracken
Peter T. Vercellone
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP0437977A1 publication Critical patent/EP0437977A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/22—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
    • 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
    • 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
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/027—Arrangements for balancing

Definitions

  • This invention relates to gas turbine engine rotors and more particularly to a rim configuration for high pressure turbine rotors.
  • An object of the invention is to provide a turbine rotor construction which brings together sealing, damping and balance features into a single-stage turbine rim configuration.
  • Another object of the invention is to provide a single-stage turbine configuration having a combination of features covering a broad range of requirements for balancing, minimum weight/complexity, leakage control and assembly.
  • a further object of the invention is to provide a turbine rim configuration which provides for individual blade installation and removal, blade-to-blade damping, under-blade balance weights and platform sealing.
  • the invention provides a turbine rotor rim construction for a gas turbine engine including a rotor disk, said disk having a plurality of slots equally spaced around its perimeter, turbine blades positioned within said slots, each blade having a root portion fitting within a disk slot, an airfoil portion extending outwardly from said disk perimeter and a platform portion between said root and said airfoil portions and adjacent said disk perimeter, sealing means installed under the platform portion of adjacent blades for controlling leakage between said blades, characterised by damper means installed on the perimeter of said disk between adjacent blades and under said blade platform portions, and balance weights installed as necessary for any blade between said blade root and said disk slot.
  • the invention provides a method of assembling a turbine rotor, comprising taking a rotor disk having a plurality of slots equally spaced around its perimeter, installing damper means in positions on the perimeter of the disk between the slots, installing turbine blades in the slots, installing sealing means between adjacent blades and under adjacent blade platforms, installing blade retention means, and balancing the rotor by removing the retention means, removing an individual blade from its slot, installing a balance weight to be positioned between the blade root and the disk slot, and replacing the blade and retention means.
  • the feature of individual blade installation and removal permits under-blade weight balancing, replacing conventional riveted-on saddle weights.
  • the rim design does not rely on heavy, life-limited rim sideplates to control cross flow rim leakage, leakage control being maintained through tight clearances between the blade and disk attachment profiles and a blade platform/platform seal.
  • each damper is retained in proper orientation through the use of two cast posts which may be of different size or shape to provide foolproofing during the assembly process.
  • the dampers when positioned close to the disk dead rim surface, allow sufficient clearance to permit the turbine blades to slide into position over the damper.
  • Fig. 1 is an exploded view of a single-stage turbine rotor showing the features of the construction.
  • Fig. 2 is a side view of the rim construction, generally along line 2-2 in Fig. 1, showing a portion of a turbine blade root and rotor disk rim in accordance with the invention.
  • Fig. 3 is a sectional view along line 3-3 of Fig. 2.
  • Fig. 4 is a sectional view along line 4-4 of Fig. 2.
  • FIG. 1 a portion of turbine rotor disk 10 is shown with turbine blades 12 and 14 in assembled position thereon.
  • the figure shows schematically arcuate shaped balance weight 16 and its position within blade slot 18 and under blade root 20, damper 22 and its location between turbine blades and with respect to disk dead rim surface 24, and interplatform seal 26 between and under adjacent blade platforms such as platform 28. It is to be understood that there will be a damper and a seal between each adjacent pair of blades on the turbine disk and a balance weight under blades as necessary to achieve dynamic balance of the turbine rotor stage.
  • Turbine blade 12 shown in Fig. 2 includes airfoil 30, root 20 and platform 32.
  • the blade is mounted on rotor disk 10 and retained in position on the rim of the disk by snap ring 34.
  • Balance weight 16 is shown in position between the underside of root 20 and slot 18 in the disk, the ends of the balance weight fitting within groove 36 in the blade root.
  • Interplatform seal 52 which is of stamped metal and like seal 26, is trapped in position by seal finger 54 and the upper side of damper support 50.
  • the finger and damper support are integral cast portions of blade 12.
  • Rear buttress 56 of the blade is designed to allow the seal to be installed from the rear of rotor disk 10, to the right in Fig. 2, after all of the blades have been assembled into the disk. When installed, approximately 0.15 inches (3.8mm) of the seal protrudes from the disk and blade buttresses providing a visible check on seal installation. Deformation of the seal into the narrow channel along the underside of the adjacent blade platforms provides retention of the seal prior to engine operation. Engine operation molds the thin seal to the contour of the underside of the blade platforms to provide even greater retention and sealing.
  • Fig. 3 is a view of the underside of adjacent blades 12 and 14 along line 3-3 in Fig. 2.
  • Cast seal finger 54 and damper support 50 on blade 12 and cast seal finger 58 and damper support 60 on blade 14 can be seen with interplatform seal 52 in place.
  • Damper 38 also is shown in its position opposite the damper supports.
  • Fig. 4 which is a section along line 4-4 in Fig. 2, shows damper 38 and seal 52 in engine operation position.
  • the top surface of the damper is against the lower side or face of damper support pad 50 on blade 12 and damper support pad 60 on blade 14.
  • the top surface of the seal is against the underside of platform 32 on blade 12 and the underside of platform 62 on blade 14.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP90314368A 1990-01-18 1990-12-28 Configuration de jante de disque de turbine Withdrawn EP0437977A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US46679590A 1990-01-18 1990-01-18
US466795 1990-01-18

Publications (1)

Publication Number Publication Date
EP0437977A1 true EP0437977A1 (fr) 1991-07-24

Family

ID=23853134

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90314368A Withdrawn EP0437977A1 (fr) 1990-01-18 1990-12-28 Configuration de jante de disque de turbine

Country Status (2)

Country Link
EP (1) EP0437977A1 (fr)
JP (1) JPH04214901A (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4300773C1 (de) * 1993-01-14 1993-11-18 Mtu Muenchen Gmbh Einrichtung zur axialen Laufschaufelsicherung und zur Beseitigung von Rotorunwuchten für axial durchströmte Verdichter oder Turbinen
WO1994012772A1 (fr) * 1992-11-24 1994-06-09 United Technologies Corporation Joint d'etancheite pour aubes d'une turbine a gaz
US5460489A (en) * 1994-04-12 1995-10-24 United Technologies Corporation Turbine blade damper and seal
EP1617044A1 (fr) * 2004-07-13 2006-01-18 General Electric Company Aube mobile de turbine amincie de manière sélective
EP2157283A1 (fr) * 2008-08-18 2010-02-24 Siemens Aktiengesellschaft Fixation d'aube avec élément d'amortissement pour une turbomachine
FR2970033A1 (fr) * 2011-01-04 2012-07-06 Turbomeca Procede d'amortissement de pale de turbine a gaz et amortisseur de vibration de mise en oeuvre
EP2848770A1 (fr) * 2013-09-17 2015-03-18 MTU Aero Engines GmbH Pale de rotor d'une turbomachine axiale et élément d'amortissement
US9810087B2 (en) 2015-06-24 2017-11-07 United Technologies Corporation Reversible blade rotor seal with protrusions
US9810075B2 (en) 2015-03-20 2017-11-07 United Technologies Corporation Faceted turbine blade damper-seal
US10253642B2 (en) 2013-09-16 2019-04-09 United Technologies Corporation Gas turbine engine with disk having periphery with protrusions
US10301958B2 (en) 2013-09-17 2019-05-28 United Technologies Corporation Gas turbine engine with seal having protrusions
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
EP3885533A1 (fr) * 2020-03-25 2021-09-29 General Electric Company Aube rotorique pour une turbomachine et turbomachine associée

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8186954B2 (en) * 2008-09-30 2012-05-29 General Electric Company Gas turbine engine rotor and balance weight therefor
JP6272044B2 (ja) * 2014-01-17 2018-01-31 三菱重工業株式会社 動翼体のシール構造、動翼体及び回転機械

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2843356A (en) * 1954-04-05 1958-07-15 Gen Electric Turbo-machine rotor assembly
US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
DE2743563A1 (de) * 1976-09-30 1978-04-06 Gen Electric Abdeckplattendaempfungsaufbau
GB2111130A (en) * 1981-12-14 1983-06-29 United Technologies Corp Blade to blade vibration damper
US4422827A (en) * 1982-02-18 1983-12-27 United Technologies Corporation Blade root seal
US4505642A (en) * 1983-10-24 1985-03-19 United Technologies Corporation Rotor blade interplatform seal
EP0314606A2 (fr) * 1987-10-27 1989-05-03 United Technologies Corporation Dispositif d'équilibrage avec passage d'air intégré pour turbines
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2843356A (en) * 1954-04-05 1958-07-15 Gen Electric Turbo-machine rotor assembly
US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
DE2743563A1 (de) * 1976-09-30 1978-04-06 Gen Electric Abdeckplattendaempfungsaufbau
GB2111130A (en) * 1981-12-14 1983-06-29 United Technologies Corp Blade to blade vibration damper
US4422827A (en) * 1982-02-18 1983-12-27 United Technologies Corporation Blade root seal
US4505642A (en) * 1983-10-24 1985-03-19 United Technologies Corporation Rotor blade interplatform seal
EP0314606A2 (fr) * 1987-10-27 1989-05-03 United Technologies Corporation Dispositif d'équilibrage avec passage d'air intégré pour turbines
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994012772A1 (fr) * 1992-11-24 1994-06-09 United Technologies Corporation Joint d'etancheite pour aubes d'une turbine a gaz
DE4300773C1 (de) * 1993-01-14 1993-11-18 Mtu Muenchen Gmbh Einrichtung zur axialen Laufschaufelsicherung und zur Beseitigung von Rotorunwuchten für axial durchströmte Verdichter oder Turbinen
EP0610668A1 (fr) * 1993-01-14 1994-08-17 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Dispositif pour le verrouillage d'aubes de rotor à entrée axiale et pour l'élimination du déséquilibre du rotor
US5425621A (en) * 1993-01-14 1995-06-20 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Device for axially securing moving blades and for eliminating rotor unbalances for axial-flow compressors or turbines
US5460489A (en) * 1994-04-12 1995-10-24 United Technologies Corporation Turbine blade damper and seal
EP1617044A1 (fr) * 2004-07-13 2006-01-18 General Electric Company Aube mobile de turbine amincie de manière sélective
US7121802B2 (en) 2004-07-13 2006-10-17 General Electric Company Selectively thinned turbine blade
EP2157283A1 (fr) * 2008-08-18 2010-02-24 Siemens Aktiengesellschaft Fixation d'aube avec élément d'amortissement pour une turbomachine
WO2010020568A1 (fr) * 2008-08-18 2010-02-25 Siemens Aktiengesellschaft Fixation d'aube avec élément d'amortissement pour une turbomachine
WO2012093217A1 (fr) * 2011-01-04 2012-07-12 Turbomeca Procede d'amortissement de pale de turbine a gaz et amortisseur de vibration de mise en œuvre
FR2970033A1 (fr) * 2011-01-04 2012-07-06 Turbomeca Procede d'amortissement de pale de turbine a gaz et amortisseur de vibration de mise en oeuvre
CN103282604A (zh) * 2011-01-04 2013-09-04 涡轮梅坎公司 燃气涡轮叶片的减振方法和实施该方法所用的减振器
CN103282604B (zh) * 2011-01-04 2016-01-06 涡轮梅坎公司 燃气涡轮叶片的减振方法和实施该方法所用的减振器
US10138756B2 (en) 2011-01-04 2018-11-27 Safran Helicopter Engines Method for damping a gas-turbine blade, and vibration damper for implementing same
US10253642B2 (en) 2013-09-16 2019-04-09 United Technologies Corporation Gas turbine engine with disk having periphery with protrusions
EP2848770A1 (fr) * 2013-09-17 2015-03-18 MTU Aero Engines GmbH Pale de rotor d'une turbomachine axiale et élément d'amortissement
US10301958B2 (en) 2013-09-17 2019-05-28 United Technologies Corporation Gas turbine engine with seal having protrusions
US9810075B2 (en) 2015-03-20 2017-11-07 United Technologies Corporation Faceted turbine blade damper-seal
US9810087B2 (en) 2015-06-24 2017-11-07 United Technologies Corporation Reversible blade rotor seal with protrusions
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
EP3885533A1 (fr) * 2020-03-25 2021-09-29 General Electric Company Aube rotorique pour une turbomachine et turbomachine associée

Also Published As

Publication number Publication date
JPH04214901A (ja) 1992-08-05

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