EP2980359A1 - Joint d'étanchéité de têtes d'aube directrice par rapport à un composant de stator interne - Google Patents

Joint d'étanchéité de têtes d'aube directrice par rapport à un composant de stator interne Download PDF

Info

Publication number
EP2980359A1
EP2980359A1 EP14179072.5A EP14179072A EP2980359A1 EP 2980359 A1 EP2980359 A1 EP 2980359A1 EP 14179072 A EP14179072 A EP 14179072A EP 2980359 A1 EP2980359 A1 EP 2980359A1
Authority
EP
European Patent Office
Prior art keywords
turbine
circumferential groove
sealing ring
outer circumferential
vanes
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Withdrawn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
EP14179072.5A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Radan Dr. Radulovic
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP14179072.5A priority Critical patent/EP2980359A1/fr
Priority to PCT/EP2015/065548 priority patent/WO2016015961A1/fr
Publication of EP2980359A1 publication Critical patent/EP2980359A1/fr
Withdrawn legal-status Critical Current

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the invention relates to an arrangement for sealing vanes of vanes of a row of vanes of a turbine relative to a radially inwardly arranged to the vane row of a stator of the turbine.
  • the invention further relates to a turbine stage for a turbine, comprising at least one row of guide vanes with vanes with radially inner vanes and at least one component of a stator of the turbine arranged radially inward to the row of vanes.
  • the invention relates to a gas turbine having a combustion chamber and a turbine downstream of the combustion chamber, wherein the turbine has a plurality of successively connected turbine stages.
  • WO 2004/057158 A1 discloses a gas turbine having an intake housing, a compressor, a combustion chamber, a turbine and an exhaust housing.
  • the turbine comprises several successive turbine stages.
  • Each turbine stage includes a stator blade row having vanes mounted on a stator of the turbine and a blade row having blades attached to a rotor of the turbine.
  • Each vane is attached via its vane root to an inner shell of the stator.
  • Each vane includes a vane head opposite the vane root, which faces the rotor and is secured to a mounting ring of the stator.
  • the object of the invention is to seal areas of a turbine in which different pressures prevail against each other and at the same time to reduce relative movements between turbine vanes.
  • a region of a turbine which can be traversed by a working medium, are sealed off from a region of the turbine lying radially inward in order to avoid pressure losses and impingement of turbine components not provided for guiding the working medium.
  • the guide vane heads are mechanically coupled in the circumferential direction, as a result of which relative movements between the guide vane heads and the guide vanes can be largely reduced.
  • loads which are introduced in the operation of a suitably equipped turbine via the guide blade feet in an inner casing of the turbine can be reduced, with a reduction of damage, reduced wear, increased service life and / or a possible reduced Design of turbine components is associated.
  • loads introduced during operation of a correspondingly equipped turbine via its guide vane heads in stator components arranged adjacent to the vane heads can be reduced, which also results in a reduction of damage, reduced wear, increased service lives and / or a possible reduced design of turbine components is associated.
  • the arrangement according to the invention can be realized in a new production of a turbine. Because of the minor structural changes, for example compared to the in WO 2004/057158 A1 described turbine, the arrangement can be realized even with relatively little effort in an existing turbine in the course of a corresponding retrofitting, for example by spark erosion using an electrode suitable for this purpose.
  • the inner circumferential groove and the sealing ring are preferably designed such that between the sealing ring and the inner circumferential groove acting in the circumferential direction form fit can be produced.
  • the guide blade heads or guide vanes which are mechanically coupled to one another in the circumferential direction, can also be mechanically coupled to the component in the peripheral direction, whereby mechanical loads acting on the guide vanes, inner housing and / or stator components during operation of a correspondingly equipped turbine can be significantly reduced , which goes along with an optimization of the turbine with regard to the above-mentioned advantages.
  • an axial width of the sealing ring in the circumferential direction and an axial width of the outer circumferential groove or inner circumferential groove in the circumferential direction vary in a complementary manner to the axial width of the sealing ring.
  • the variation of the axial width of the sealing ring and the outer circumferential groove or inner Circumferential groove may have a steady or a sudden course in the circumferential direction.
  • At least one axial end face of the sealing ring comprises a toothing which is symmetrical in particular to the longitudinal axis of the sealing ring and at least one axial side face of the outer circumferential groove or inner circumferential groove cooperating with the axial end face of the sealing ring has a toothing formed complementary to the toothing of the axial end face of the sealing ring.
  • the teeth may have inclined or perpendicular to the circumferential direction extending tooth flanks.
  • the toothing on the sealing ring can be realized by a zigzag-shaped course of the sealing ring in the circumferential direction. It can also be formed correspondingly both axial end faces of the sealing ring or both axial side surfaces of the outer circumferential groove or inner circumferential groove.
  • the two axial end faces of the sealing ring may be formed symmetrically with respect to a transverse plane of the sealing ring.
  • the outer circumferential groove is preferably arranged on a radially inwardly projecting, with respect to a flow direction of the working blade surrounding the nozzle row upstream peripheral ring of the outer ring. In this way, a sealing of regions of the turbine according to the invention with different pressure takes place at an upstream, earliest possible section of the respective turbine stage.
  • the turbine stage may also have two or more rows of vanes, radially inner components and / or arrangements.
  • the component of the stator may be arranged in a transition region of a gas turbine from a combustion chamber of the gas turbine into the turbine.
  • the gas turbine according to the invention comprises at least one combustion chamber and at least one turbine downstream of the combustion chamber, wherein the turbine has a plurality of turbine stages connected in series, and wherein at least one turbine stage according to the aforementioned embodiment is formed.
  • the gas turbine may also have two or more combustors and / or turbines.
  • At least one first turbine stage connected directly downstream of the combustion chamber is designed in accordance with the aforementioned embodiment.
  • this area of a gas turbine relatively large pressure differences between a turbine section leading to a working medium and a further turbine section located radially inside and outside this turbine section can prevail, which makes the equipment of the gas turbine with the turbine stage according to the invention or the arrangement mentioned above meaningful.
  • Also occur in this area of a gas turbine or its turbine relatively high heat loads and thus large thermal expansion, which can be collected in the circumferential direction via the producible with the above arrangement positive engagement between the sealing ring and the outer circumferential groove or inner circumferential groove to the turbine stage or Turbine rugged design.
  • FIG. 1 shows a sectional view of a detail of an embodiment of a gas turbine according to the invention 1.
  • the gas turbine 1 comprises a combustion chamber 2 and the combustion chamber 2 downstream turbine 3, wherein the turbine 3 has a plurality of successively connected turbine stages 4, of which FIG. 1 only the first turbine stage 4 connected directly downstream of the combustion chamber 2 is shown.
  • the first turbine stage 4 comprises a stator blade row 5 of individual radially arranged guide vanes 6 with radially inner guide blade heads 7. Furthermore, the first turbine stage 4 comprises a rotor blade row 8 with radially arranged rotor blades 9 which are fastened to a rotor 10 of the gas turbine 1. In addition, the first turbine stage 4 comprises a component 11 of a stator 12 of the turbine 3 which is arranged radially inwards to the row of guide blades 5. Furthermore, the first turbine stage 4 comprises an arrangement 13 for sealing the guide vane heads 7 of the guide vanes 6 of the vane row 5 of the turbine 3 with respect to the radially inwardly arranged to the vane row 5 component 11 of the stator 12 of the turbine 3rd
  • the arrangement 13 comprises an inner circumferential groove 14 arranged radially on the outside of the component 11, an outer peripheral groove 17 formed on the individual guide blade heads 7 radially inwardly on an outer ring 16 formed by the guide blade heads 7 and one each partially inside the outer circumferential groove 17 and the sealing ring 18 are formed such that between the sealing ring 18 and the outer circumferential groove 17 a circumferentially acting positive connection is made, as for example more accurate FIG. 4 can be seen.
  • the inner circumferential groove 14 and the sealing ring 18 may be formed such that between the sealing ring 18 and the inner circumferential groove 14 a force acting in the circumferential direction positive connection is made.
  • each vane 6 is arranged at a radially inwardly projecting, with respect to a direction indicated by the arrow 21 flow direction of the vane row 5 flowing around the working medium upstream annular segment 22 of the respective vane head 7.
  • the ring segments 22 form on the outer ring 16 a radially inwardly projecting, with respect to the flow direction of the guide vane row 5 flowing around the working medium upstream peripheral ring 27, on which the outer circumferential groove 17 is arranged.
  • FIG. 2 4 shows a perspective view of a guide vane 6 of an embodiment of a turbine stage 4 according to the invention, not shown.
  • the vane 6 comprises the radially inner vane head 7, a radially outer vane foot 19 and an airfoil 20 arranged between the vane head 7 and the vane foot 19 is at a radially inwardly projecting, with respect to a direction indicated by the arrow 21 Flow direction of the guide vane 6 flowing around the working medium upstream ring segment 22 of the vane head 7 is arranged. This is accordingly FIG.
  • FIG. 3 shows a side view of a detail of in FIG. 2 shown guide vane 6 in the region of its vane head 7 and its ring segment 22 with a sealing ring 18 arranged thereon.
  • the sealing ring 18 is arranged with a radially outer portion within the groove 15.
  • a circumferential broadening 28 is arranged, which is positively inserted into an inner circumferential groove which is wider than the groove 15 is formed.
  • FIG. 4 shows a sectional view of the in FIG. 3 shown details of the guide vane 6 with a sealing ring 18 arranged thereon.
  • the sectional plane IV-IV is corresponding FIG. 3 selected.
  • An axial width of the sealing ring 18 varies in the circumferential direction and an axial width of the groove 15 and thus the outer circumferential groove of the outer ring, not shown, varies in the circumferential direction complementary to the axial width of the sealing ring 18.
  • the arranged on the component of the stator inner circumferential groove corresponding to the outer circumferential groove 17 be formed.
  • both axial end faces 23 and 24 of the sealing ring 18 have a toothing which is symmetrical to the longitudinal axis of the sealing ring 18 and has tooth flanks running obliquely to the circumferential direction.
  • the respectively cooperating with an axial end face 23 and 24 of the sealing ring 18 axial side surface 25 and 26 of the groove 15 and thereby the outer circumferential groove has a complementary to the toothing of the respective axial end face 23 and 24 of the sealing ring 18 formed on teeth.
  • the respective with an axial end face 23 and 24 of the sealing ring 18 cooperating axial side surface of the inner circumferential groove of the stator, not shown, may also have a complementary to the toothing of the respective axial end face 23 and 24 of the sealing ring 18 formed toothing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14179072.5A 2014-07-30 2014-07-30 Joint d'étanchéité de têtes d'aube directrice par rapport à un composant de stator interne Withdrawn EP2980359A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14179072.5A EP2980359A1 (fr) 2014-07-30 2014-07-30 Joint d'étanchéité de têtes d'aube directrice par rapport à un composant de stator interne
PCT/EP2015/065548 WO2016015961A1 (fr) 2014-07-30 2015-07-08 Garniture d'étanchéité de têtes de pale directrice par rapport à un composant intérieur solidaire en rotation d'une turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14179072.5A EP2980359A1 (fr) 2014-07-30 2014-07-30 Joint d'étanchéité de têtes d'aube directrice par rapport à un composant de stator interne

Publications (1)

Publication Number Publication Date
EP2980359A1 true EP2980359A1 (fr) 2016-02-03

Family

ID=51260648

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14179072.5A Withdrawn EP2980359A1 (fr) 2014-07-30 2014-07-30 Joint d'étanchéité de têtes d'aube directrice par rapport à un composant de stator interne

Country Status (2)

Country Link
EP (1) EP2980359A1 (fr)
WO (1) WO2016015961A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4345255A1 (fr) * 2022-09-30 2024-04-03 RTX Corporation Joint d'air extérieur d'aube avec bague de retenue

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1534660A (en) * 1976-05-05 1978-12-06 Stal Laval Turbin Ab Sealing arrangement in a gas turbine
US4379560A (en) * 1981-08-13 1983-04-12 Fern Engineering Turbine seal
WO2004057158A1 (fr) 2002-12-19 2004-07-08 Siemens Aktiengesellschaft Turbine, dispositif de fixation pour aubes fixes et procede de demontage des aubes fixes d'une turbine
EP2351910A2 (fr) * 2010-01-06 2011-08-03 General Electric Company Dispositif d'étanchéité de composants stationnaires de turbine à vapeur

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1534660A (en) * 1976-05-05 1978-12-06 Stal Laval Turbin Ab Sealing arrangement in a gas turbine
US4379560A (en) * 1981-08-13 1983-04-12 Fern Engineering Turbine seal
WO2004057158A1 (fr) 2002-12-19 2004-07-08 Siemens Aktiengesellschaft Turbine, dispositif de fixation pour aubes fixes et procede de demontage des aubes fixes d'une turbine
EP2351910A2 (fr) * 2010-01-06 2011-08-03 General Electric Company Dispositif d'étanchéité de composants stationnaires de turbine à vapeur

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4345255A1 (fr) * 2022-09-30 2024-04-03 RTX Corporation Joint d'air extérieur d'aube avec bague de retenue

Also Published As

Publication number Publication date
WO2016015961A1 (fr) 2016-02-04

Similar Documents

Publication Publication Date Title
DE102016125189B4 (de) Turbolader
DE102015101156A1 (de) Laufschaufel mit hoher Sehnenlänge, zwei Teilspannweiten-Dämpferelementen und gekrümmtem Schwalbenschwanz
EP2918913B1 (fr) Chambre de combustion d'une turbine à gaz
EP2179143B1 (fr) Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz
EP2647795A1 (fr) Système d'étanchéité pour turbomachine
EP3404210A1 (fr) Segment de grille d'aubes d'une turbomachine avec paroi de plateforme non-axisymétrique , grille d'aubes, canal d'aube, plateforme, turbomachine associés
EP2818724B1 (fr) Turbomachine et procédé
EP2799776A1 (fr) Joint de brûleur pour tête de chambre de combustion de turbines à gaz et bouclier thermique
DE102014204476A1 (de) Brennkammer einer Gasturbine
EP2746533A1 (fr) Grille d'aube et turbomachine
EP3273001A2 (fr) Procédé de fabrication d'un élément d'aube en tandem
CH701927B1 (de) Statoranordnung, Kompressor und Gasturbinenmotor.
DE102007015669A1 (de) Turbomaschine
EP2871325B1 (fr) Virole interne d'une turbomachine et distributeur
EP3287611A1 (fr) Turbine à gaz et procédé de suspension d'un segment d'aube de guidage d'une turbine à gaz
EP2526263B1 (fr) Système de boîtier pour une turbomachine axiale
EP3587739A1 (fr) Agencement d' anneau de carter pour une turbomachine
EP3056684B1 (fr) Bague intérieure séparée axialement pour une turbomachine, un stator et groupe motopropulseur
EP2980359A1 (fr) Joint d'étanchéité de têtes d'aube directrice par rapport à un composant de stator interne
DE102010055435B4 (de) Innendeckband einer Gasturbine sowie Verfahren zur Herstellung eines Innendeckbandes
DE102011084125A1 (de) Schaufelsegment und Strömungsmaschine
DE102011052037A1 (de) Strömungsteileranordnung für Dampfturboantrieb und Verfahren
EP3551850B1 (fr) Procédé de modification d'une turbine
DE102014222320A1 (de) Brennkammerwand einer Gasturbine mit Kühlung für einen Mischluftlochrand
EP3022395B1 (fr) Elément d'insertion et turbine à gaz

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: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20160804