EP1898050A2 - Système d'amortissement et d'étanchéité pour aubes de turbines - Google Patents

Système d'amortissement et d'étanchéité pour aubes de turbines Download PDF

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Publication number
EP1898050A2
EP1898050A2 EP07112566A EP07112566A EP1898050A2 EP 1898050 A2 EP1898050 A2 EP 1898050A2 EP 07112566 A EP07112566 A EP 07112566A EP 07112566 A EP07112566 A EP 07112566A EP 1898050 A2 EP1898050 A2 EP 1898050A2
Authority
EP
European Patent Office
Prior art keywords
sealing
damping
damping element
friction
platform
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.)
Granted
Application number
EP07112566A
Other languages
German (de)
English (en)
Other versions
EP1898050A3 (fr
EP1898050B1 (fr
Inventor
Richard Whitton
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1898050A2 publication Critical patent/EP1898050A2/fr
Publication of EP1898050A3 publication Critical patent/EP1898050A3/fr
Application granted granted Critical
Publication of EP1898050B1 publication Critical patent/EP1898050B1/fr
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the invention relates to a turbine blade damping and sealing system comprising a centrifugal force held between opposing surfaces of adjacent platforms of the gas turbine engine blades mounted on the rotor, a straight three-sided prism having equal sized side faces forming a sealing and damping element.
  • Gas turbine engines have rotor disks with circumferentially mounted, radially extending blades consisting of a blade root, a platform, and an airfoil.
  • rotor disks with circumferentially mounted, radially extending blades consisting of a blade root, a platform, and an airfoil.
  • sealing elements are known, which are formed in cross-section specifically to the shape of the remaining space between the platforms and must be used in a special orientation in this room. Accordingly consuming the assembly and incorrect alignment of the sealing element limits its sealing and damping effect considerably.
  • the precisely matched form of sealing element and platform gap requires a considerable manufacturing effort.
  • sealing and damping elements with circular cross-sectional area, which invest in any orientation under the action of centrifugal force on the side edges of the two adjacent platforms.
  • round sealing and damping elements wear relatively quickly, so that the sealing and damping effect wears off and the sealing and damping elements must be replaced with considerable effort.
  • the invention has for its object to provide a sealing and damping system for turbine blades, which has a high sealing and damping effect and requires little installation and repair.
  • the core of the invention is the formation of a trained as a three-sided prism sealing and damping element with convex side surfaces, which allow a slight pivoting movement of the sealing element during operation and thus act as an enlarged friction surfaces.
  • the resulting increased friction results in improved vibration damping.
  • the friction-related wear leads to a mutual adaptation of the mutually connected contact surfaces.
  • manufacturing tolerances are compensated and achieved a further improved vibration damping and sealing effect. Due to the automatic mutual adaptation of the sealing or friction surfaces manufacturing inaccuracies are compensated.
  • the friction occurring due to wear can be considered constructively.
  • the manufacturing and repair costs are therefore low.
  • the opposite sealing surface of the adjacent blade platforms form an acute-angled gap into which the sealing and damping element is automatically pressed under the action of centrifugal force and rests with two curved friction surfaces on the gap surfaces.
  • a rotor disk 3 consisting of a blade root 5, a blade platform 6 and an airfoil 7, is arranged between two stator blades 1 spaced apart in the flow direction.
  • two adjoining platforms 6a, 6b of adjacent turbine blades 4 can be seen.
  • the right in the drawing platform 6a has a recess 8 in which a sealing and damping element 9 is held loose.
  • the open side of the recess 8 is - leaving a very narrow gap 10 a flat, substantially vertical platform edge 11 of the other platform 6b opposite and prevents falling out of the sealing and damping element 9 from the recess 8.
  • the recess 8 has an obliquely top extending sealing surface 12.
  • the sealing and damping element 9 is a straight component with the cross section of an equilateral triangle, but with rounded longitudinal edges 13 and with between the longitudinal edges 13 convexly curved - convex - friction surfaces 14 (sealing and damping surfaces, side surfaces).
  • sealing and damping element 9 applies due to the centrifugal force during rotation of the rotor 2 with its convex curved surfaces 14 to the vertical platform edge 11 and the inclined sealing surface 12 at. A rotation of the sealing and damping element 9 about its longitudinal axis is therefore not possible.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07112566A 2006-09-01 2007-07-16 Système d'amortissement et d'étanchéité pour aubes de turbines Ceased EP1898050B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006041322A DE102006041322A1 (de) 2006-09-01 2006-09-01 Dämpfungs- und Dichtungssystem für Turbinenschaufeln

Publications (3)

Publication Number Publication Date
EP1898050A2 true EP1898050A2 (fr) 2008-03-12
EP1898050A3 EP1898050A3 (fr) 2010-07-07
EP1898050B1 EP1898050B1 (fr) 2011-09-07

Family

ID=38969468

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07112566A Ceased EP1898050B1 (fr) 2006-09-01 2007-07-16 Système d'amortissement et d'étanchéité pour aubes de turbines

Country Status (3)

Country Link
US (1) US20090136350A1 (fr)
EP (1) EP1898050B1 (fr)
DE (1) DE102006041322A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012072069A1 (fr) * 2010-11-30 2012-06-07 Mtu Aero Engines Gmbh Moyen d'amortissement pour amortir le mouvement d'une aube d'une turbomachine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9045992B2 (en) 2010-06-28 2015-06-02 Herakles Turbomachine blades or vanes having complementary even/odd geometry
FR2961845B1 (fr) * 2010-06-28 2013-06-28 Snecma Propulsion Solide Aube de turbomachine a geometrie complementaire paire/impaire et son procede de fabrication
US9810075B2 (en) 2015-03-20 2017-11-07 United Technologies Corporation Faceted turbine blade damper-seal

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1549152A (en) * 1977-01-11 1979-08-01 Rolls Royce Rotor stage for a gas trubine engine
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4537024A (en) * 1979-04-23 1985-08-27 Solar Turbines, Incorporated Turbine engines
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
US5156528A (en) * 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
GB9609721D0 (en) * 1996-05-09 1996-07-10 Rolls Royce Plc Vibration damping
US5749705A (en) * 1996-10-11 1998-05-12 General Electric Company Retention system for bar-type damper of rotor blade
JP3462695B2 (ja) * 1997-03-12 2003-11-05 三菱重工業株式会社 ガスタービン動翼シール板
JP2002544431A (ja) * 1999-05-12 2002-12-24 シーメンス アクチエンゲゼルシヤフト 特にタービンにおける隙間を塞ぐパッキンおよびタービン
DE10014198A1 (de) * 2000-03-22 2001-09-27 Alstom Power Nv Beschaufelung mit Dämpfungselementen
DE10022244A1 (de) * 2000-05-08 2001-11-15 Alstom Power Nv Schaufelanordnung mit Dämpfungselementen
US6851932B2 (en) * 2003-05-13 2005-02-08 General Electric Company Vibration damper assembly for the buckets of a turbine
JP2005233141A (ja) * 2004-02-23 2005-09-02 Mitsubishi Heavy Ind Ltd 動翼およびその動翼を用いたガスタービン
US7534090B2 (en) * 2006-06-13 2009-05-19 General Electric Company Enhanced bucket vibration system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012072069A1 (fr) * 2010-11-30 2012-06-07 Mtu Aero Engines Gmbh Moyen d'amortissement pour amortir le mouvement d'une aube d'une turbomachine
US9506372B2 (en) 2010-11-30 2016-11-29 Mtu Aero Engines Gmbh Damping means for damping a blade movement of a turbomachine

Also Published As

Publication number Publication date
EP1898050A3 (fr) 2010-07-07
DE102006041322A1 (de) 2008-04-24
US20090136350A1 (en) 2009-05-28
EP1898050B1 (fr) 2011-09-07

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