EP2520768A1 - Dispositif étanche pour un corps de base de rotor à aubage intégral d'une turbomachine - Google Patents

Dispositif étanche pour un corps de base de rotor à aubage intégral d'une turbomachine Download PDF

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Publication number
EP2520768A1
EP2520768A1 EP11164416A EP11164416A EP2520768A1 EP 2520768 A1 EP2520768 A1 EP 2520768A1 EP 11164416 A EP11164416 A EP 11164416A EP 11164416 A EP11164416 A EP 11164416A EP 2520768 A1 EP2520768 A1 EP 2520768A1
Authority
EP
European Patent Office
Prior art keywords
sealing
sealing elements
blades
bladed rotor
sealing device
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Withdrawn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
EP11164416A
Other languages
German (de)
English (en)
Inventor
Frank Stiehler
Manuel Hein
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
MTU Aero Engines AG
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 MTU Aero Engines GmbH, MTU Aero Engines AG filed Critical MTU Aero Engines GmbH
Priority to EP11164416A priority Critical patent/EP2520768A1/fr
Priority to US13/461,402 priority patent/US9068466B2/en
Publication of EP2520768A1 publication Critical patent/EP2520768A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • F05D2240/55—Seals
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the blade root 6 is formed either as an integral part of the rotor blades 2 or as a separately formed and subsequently joined to the rotor blade 2 component. He is cohesively with its radially inner circumferential surface, for example by means of a Friction welding method connected to a base, not shown, of the base body 4 and has two concave side walls 18, 20, each of which is flush in a base body side peripheral wall 22.
  • the sealing elements 46 are in principle a reshaped sheet-like body, the formerly remote and extending in the longitudinal direction edge portions in sections, the foot sections 56, 58 form. To enable elastic deformation of the sealing elements 46 when subjected to centrifugal force, the formerly remote and now adjacent edge portion sections of each foot section 56, 58 are not merged, so that the foot sections 56, 58 are open and the sealing element 46 has an open profile. As a result, the sealing surfaces 50, 52 can adapt to the wall section 54 contoured, whereby a large area coverage area is achieved and thus a high density or a high seal of the gap 40 is achieved.
  • the support bodies 48 each have a dumbbell-shaped configuration with two end support disks 60, 62, which are connected to one another via a support arm 64. Preferably, they are centrifugally activated and also act with their support plates 60, 62 as axial sealing body for reducing an axial flow of cooling air through the channels 38 from the high pressure side to the low pressure side.
  • an axial passage 102 is formed in the blade roots 6.
  • cooling air can flow into the internal cooling system through bores 104 which are provided peripherally on the side walls 18, 20 of the blade root 6.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP11164416A 2011-05-02 2011-05-02 Dispositif étanche pour un corps de base de rotor à aubage intégral d'une turbomachine Withdrawn EP2520768A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP11164416A EP2520768A1 (fr) 2011-05-02 2011-05-02 Dispositif étanche pour un corps de base de rotor à aubage intégral d'une turbomachine
US13/461,402 US9068466B2 (en) 2011-05-02 2012-05-01 Sealing device, integrally bladed rotor basic body, and turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11164416A EP2520768A1 (fr) 2011-05-02 2011-05-02 Dispositif étanche pour un corps de base de rotor à aubage intégral d'une turbomachine

Publications (1)

Publication Number Publication Date
EP2520768A1 true EP2520768A1 (fr) 2012-11-07

Family

ID=44786196

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11164416A Withdrawn EP2520768A1 (fr) 2011-05-02 2011-05-02 Dispositif étanche pour un corps de base de rotor à aubage intégral d'une turbomachine

Country Status (2)

Country Link
US (1) US9068466B2 (fr)
EP (1) EP2520768A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2984290A4 (fr) * 2013-04-12 2016-06-22 United Technologies Corp Rotor à aubage intégré
US10920617B2 (en) 2018-08-17 2021-02-16 Raytheon Technologies Corporation Gas turbine engine seal ring assembly
US11149651B2 (en) 2019-08-07 2021-10-19 Raytheon Technologies Corporation Seal ring assembly for a gas turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3003893B1 (fr) * 2013-04-02 2017-12-29 Snecma Aube de turbomachine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3751183A (en) * 1971-12-02 1973-08-07 Gen Electric Interblade baffle and damper
GB2016092A (en) * 1978-03-08 1979-09-19 Snecma Blade-retainer for the rotor of a turbo machine particularly an axial flow turbine
US5143517A (en) * 1990-08-08 1992-09-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation"S.N.E.M.C.A." Turbofan with dynamic vibration damping
GB2344383A (en) * 1998-12-01 2000-06-07 Rolls Royce Plc Damping vibration of gas turbine engine blades
DE102007037208A1 (de) * 2007-08-07 2009-02-19 Mtu Aero Engines Gmbh Turbinenschaufel mit zumindest einer Einsatzhülse zum Kühlen der Turbinenschaufel
CH698921B1 (de) * 2006-11-10 2009-12-15 Alstom Technology Ltd Strömungsmaschine.
DE102009007468A1 (de) 2009-02-04 2010-08-19 Mtu Aero Engines Gmbh Integral beschaufelte Rotorscheibe für eine Turbine
DE102009011965A1 (de) * 2009-03-05 2010-09-09 Mtu Aero Engines Gmbh Integral beschaufelter Rotor für eine Strömungsmaschine
DE102009011879A1 (de) * 2009-03-05 2010-09-16 Mtu Aero Engines Gmbh Integral beschaufelter Rotor und Verfahren zur Herstellung eines integral beschaufelten Rotors

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US6932575B2 (en) * 2003-10-08 2005-08-23 United Technologies Corporation Blade damper
US7121800B2 (en) * 2004-09-13 2006-10-17 United Technologies Corporation Turbine blade nested seal damper assembly

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3751183A (en) * 1971-12-02 1973-08-07 Gen Electric Interblade baffle and damper
GB2016092A (en) * 1978-03-08 1979-09-19 Snecma Blade-retainer for the rotor of a turbo machine particularly an axial flow turbine
US5143517A (en) * 1990-08-08 1992-09-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation"S.N.E.M.C.A." Turbofan with dynamic vibration damping
GB2344383A (en) * 1998-12-01 2000-06-07 Rolls Royce Plc Damping vibration of gas turbine engine blades
CH698921B1 (de) * 2006-11-10 2009-12-15 Alstom Technology Ltd Strömungsmaschine.
DE102007037208A1 (de) * 2007-08-07 2009-02-19 Mtu Aero Engines Gmbh Turbinenschaufel mit zumindest einer Einsatzhülse zum Kühlen der Turbinenschaufel
DE102009007468A1 (de) 2009-02-04 2010-08-19 Mtu Aero Engines Gmbh Integral beschaufelte Rotorscheibe für eine Turbine
DE102009011965A1 (de) * 2009-03-05 2010-09-09 Mtu Aero Engines Gmbh Integral beschaufelter Rotor für eine Strömungsmaschine
DE102009011879A1 (de) * 2009-03-05 2010-09-16 Mtu Aero Engines Gmbh Integral beschaufelter Rotor und Verfahren zur Herstellung eines integral beschaufelten Rotors

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2984290A4 (fr) * 2013-04-12 2016-06-22 United Technologies Corp Rotor à aubage intégré
US10458265B2 (en) 2013-04-12 2019-10-29 United Technologies Corporation Integrally bladed rotor
US10920617B2 (en) 2018-08-17 2021-02-16 Raytheon Technologies Corporation Gas turbine engine seal ring assembly
US11149651B2 (en) 2019-08-07 2021-10-19 Raytheon Technologies Corporation Seal ring assembly for a gas turbine engine

Also Published As

Publication number Publication date
US20120282098A1 (en) 2012-11-08
US9068466B2 (en) 2015-06-30

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Owner name: MTU AERO ENGINES GMBH

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