EP1898050B1 - Système d'amortissement et d'étanchéité pour aubes de turbines - Google Patents
Système d'amortissement et d'étanchéité pour aubes de turbines Download PDFInfo
- Publication number
- EP1898050B1 EP1898050B1 EP07112566A EP07112566A EP1898050B1 EP 1898050 B1 EP1898050 B1 EP 1898050B1 EP 07112566 A EP07112566 A EP 07112566A EP 07112566 A EP07112566 A EP 07112566A EP 1898050 B1 EP1898050 B1 EP 1898050B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sealing
- damping
- damping element
- platform
- sealing system
- 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 - Fee Related
Links
Images
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.
- Fig. 1 is between two spaced in the direction of flow stator blades 1, a rotor 2 with attached to the circumference of a rotor disk 3 turbine blades 4, consisting of a blade root 5, a blade platform 6 and an airfoil 7, respectively.
- a rotor 2 with attached to the circumference of a rotor disk 3 turbine blades 4, consisting of a blade root 5, a blade platform 6 and an airfoil 7, respectively.
- two adjacent 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)
Claims (4)
- Système d'amortissement et d'étanchéité pour aubes de turbines, comprenant un élément d'étanchéité et d'amortissement (9) qui forme un prisme droit à base triangulaire avec faces latérales égales (14) et est maintenu par la force centrifuge entre des surfaces opposées (11, 12) de plateformes voisines (6a, 6b) des aubes (4) fixées au rotor d'un moteur à turbine à gaz, caractérisé en ce que les faces latérales de l'élément d'étanchéité et d'amortissement (9) sont conçues en tant que surfaces de frottement convexes (14) afin d'obtenir un léger mouvement oscillant et un accroissement de l'effet de frottement.
- Système d'amortissement et d'étanchéité selon la revendication n°1, caractérisé en ce que les surfaces opposées (11, 12) forment un interstice (10) cunéiforme acutangle fixant de manière flottante l'élément d'étanchéité et d'amortissement (9).
- Système d'amortissement et d'étanchéité selon la revendication n° 2, caractérisé en ce que l'interstice (10) est formé par un bord de plateforme rectiligne (11) d'une plateforme (6b) et par une surface d'étanchéité oblique (12) dans un évidement (8) de l'autre plateforme (6a).
- Système d'amortissement et d'étanchéité selon la revendication n° 1, caractérisé en ce que les arêtes longitudinales de l'élément d'étanchéité et d'amortissement (9) sont arrondies.
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 EP1898050A2 (fr) | 2008-03-12 |
EP1898050A3 EP1898050A3 (fr) | 2010-07-07 |
EP1898050B1 true EP1898050B1 (fr) | 2011-09-07 |
Family
ID=38969468
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07112566A Expired - Fee Related 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) |
Families Citing this family (4)
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 |
DE102010052965B4 (de) | 2010-11-30 | 2014-06-12 | MTU Aero Engines AG | Dämpfungsmittel zum Dämpfen einer Schaufelbewegung einer Turbomaschine |
US9810075B2 (en) | 2015-03-20 | 2017-11-07 | United Technologies Corporation | Faceted turbine blade damper-seal |
Family Cites Families (15)
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 |
WO2000070192A1 (fr) * | 1999-05-12 | 2000-11-23 | Siemens Aktiengesellschaft | Garniture pour l'etancheification d'une fente, en particulier d'une turbine, et turbine |
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 |
-
2006
- 2006-09-01 DE DE102006041322A patent/DE102006041322A1/de not_active Withdrawn
-
2007
- 2007-07-16 EP EP07112566A patent/EP1898050B1/fr not_active Expired - Fee Related
- 2007-09-04 US US11/896,508 patent/US20090136350A1/en not_active Abandoned
Also Published As
Publication number | Publication date |
---|---|
EP1898050A2 (fr) | 2008-03-12 |
DE102006041322A1 (de) | 2008-04-24 |
EP1898050A3 (fr) | 2010-07-07 |
US20090136350A1 (en) | 2009-05-28 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2094946B1 (fr) | Ensemble d'aubes | |
DE10350627B4 (de) | Turbinenrotor- und Schaufelanordnung, Vorspannfedersegment und zugehöriges Verfahren für Dampfturbinenschaufeln der Reaktionsbauart | |
WO2007113149A1 (fr) | Aube directrice de turbomachine, notamment de turbine à vapeur | |
EP3324002B1 (fr) | Système d'étanchéité pour une turbomachine et turbomachine axiale | |
EP3999717B1 (fr) | Élément intermédiaire pour une connexion aube-disque de rotor pour le rotor d'une turbomachine, rotor pour une turbomachine et turbomachine | |
EP1898050B1 (fr) | Système d'amortissement et d'étanchéité pour aubes de turbines | |
DE102006029379B3 (de) | Schaufelrad | |
EP2310634B1 (fr) | Système d'aubes mobiles pour une rangée d'aubes mobiles d'une turbomachine | |
EP2410132B1 (fr) | Aube de compresseur d'une turbine à gaz équipée d'une structure du bord d'attaque autoaiguisante | |
EP3312388B1 (fr) | Pièce de rotor, compresseur, turbine et procédé de fabrication associés | |
EP3379037B1 (fr) | Étanchéité sur une bague intérieure d'une couronne d'aubes directrices | |
DE102009004792B4 (de) | Dämpfungselement (Reibdämpfer) mit Dichtungsfunktion für Turbinenlaufschaufeln | |
DE102017204243A1 (de) | Dichtfin mit zumindest einer gewölbten Seitenflanke | |
EP2860356B1 (fr) | Turbomachine | |
WO2000057030A1 (fr) | Aube de turbomachine | |
DE19823157A1 (de) | Einrichtung zur Befestigung der Laufschaufeln axial durchströmter Turbomaschinen | |
EP3183430B1 (fr) | Aube mobile de turbine | |
WO2003100220A1 (fr) | Dispositif de securite axial pour aubes mobiles | |
EP3232004A1 (fr) | Aube rotorique pour une turbomachine thermique | |
EP0108997A1 (fr) | Soupape à plateau avec bras d'articulation situés hors du centre | |
EP3246521B1 (fr) | Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile | |
WO2013132055A1 (fr) | Turbomachine radiale comprenant un élément de réduction de tourbillonnement | |
DE2845199C2 (de) | Schaufelrad für eine Gasturbine | |
EP1496196A1 (fr) | Turbine à vapeur | |
CH446396A (de) | Beschaufelter Läufer für Turbomaschinen und Verfahren zu seiner Herstellung |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK YU |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK RS |
|
17P | Request for examination filed |
Effective date: 20100720 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
AKX | Designation fees paid |
Designated state(s): DE FR GB |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F01D 5/22 20060101ALI20110228BHEP Ipc: F01D 5/26 20060101ALI20110228BHEP Ipc: F01D 11/00 20060101ALI20110228BHEP Ipc: F01D 5/16 20060101AFI20110228BHEP |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 502007008084 Country of ref document: DE Effective date: 20111103 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20120611 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502007008084 Country of ref document: DE Effective date: 20120611 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 10 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 11 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 12 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20190725 Year of fee payment: 13 Ref country code: DE Payment date: 20190729 Year of fee payment: 13 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20190729 Year of fee payment: 13 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 502007008084 Country of ref document: DE |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20200716 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20200716 Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20200731 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210202 |