[go: up one dir, main page]

EP3686398B1 - Joint d'étanchéité pour une turbine à gaz - Google Patents

Joint d'étanchéité pour une turbine à gaz Download PDF

Info

Publication number
EP3686398B1
EP3686398B1 EP19425005.6A EP19425005A EP3686398B1 EP 3686398 B1 EP3686398 B1 EP 3686398B1 EP 19425005 A EP19425005 A EP 19425005A EP 3686398 B1 EP3686398 B1 EP 3686398B1
Authority
EP
European Patent Office
Prior art keywords
seal member
seal assembly
spring
plate portion
seal
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.)
Active
Application number
EP19425005.6A
Other languages
German (de)
English (en)
Other versions
EP3686398A1 (fr
Inventor
Luca Cerasi
Marcel König
Stefano Elli
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.)
Ansaldo Energia Switzerland AG
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia Switzerland AG
Ansaldo Energia SpA
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 Ansaldo Energia Switzerland AG, Ansaldo Energia SpA filed Critical Ansaldo Energia Switzerland AG
Priority to EP19425005.6A priority Critical patent/EP3686398B1/fr
Priority to CN202010074161.0A priority patent/CN111502773B/zh
Publication of EP3686398A1 publication Critical patent/EP3686398A1/fr
Application granted granted Critical
Publication of EP3686398B1 publication Critical patent/EP3686398B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • 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
    • F05D2240/57—Leaf 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Definitions

  • the present invention relates to a seal assembly for use in a gas turbine power plant, namely as an interface seal between an outlet of a gas combustor and a first vane range of the turbine.
  • a gas turbine power plant (in the following, "gas turbine” only) comprises a compressor, a combustor assembly downstream of the compressor and a turbine downstream of the combustor.
  • the gas turbine includes a rotor comprising a compressor section and a turbine section.
  • downstream and upstream refer to the direction of the main gas flow passing through the gas turbine;
  • axial refers to the direction of the rotor axis;
  • inner refers to the radial position with respect to the rotor axis.
  • the compressor comprises an inlet supplied with air, a plurality of fixed guide vanes and a plurality of rotating blades compressing the passing air.
  • a major part of the compressed air flows into a combustor where the compressed air is mixed with at least one fuel. This mixture is combusted in the combustor leading to a significant temperature rise.
  • the resulting hot gas leaves the combustor and is expanded in the turbine, producing mechanical work on the rotor.
  • the turbine includes fixed vanes carried by the turbine housing and disposed in a plurality of axially spaced circumferential ranges, and rotating blades carried by the rotor and disposed in a plurality of axially spaced circumferential ranges, each blade range being disposed downstream of a respective vane range so that the vanes guide the gas flow in an optimal direction toward the blades.
  • Gas turbines are known in which the combustor is constituted by a plurality of canisters or "can combustors" that are equally spaced around the rotor, each can combustor having an outlet member facing a number of vanes of the first vane range; it is therefore necessary to seal the outlet member against the vanes facing it, so that the outer annular duct where hot combusted gases flow is sealed with respect to an inner space that conveys compressed cooling air at a lower temperature.
  • a honeycomb seal is used, which is solidly bonded to the vane.
  • This solution has operational limits to avoid plastic deformation of the seal and possible delamination.
  • EP 2775102 A2 discloses the features of the preamble of claim 1.
  • An object of the present invention is to provide a seal assembly that ensures optimal sealing in every working condition and is free from the drawbacks of the prior art seals as specified above.
  • Another object of the present invention is to provide a seal assembly that can be retrofitted to existing turbines to replace existing seals.
  • a seal assembly for a gas turbine which is configured to be axially interposed between an outlet member of a combustor and at least one turbine vane and radially interposed between an outer hot gas path and an inner space containing higher-pressure cooling air, the seal assembly comprising:
  • each of the components of the seal assembly is aimed at a specific function and can be specifically dimensioned therefor, so as to ensure maximum performance and durability of the seal assembly in varying operation conditions.
  • Main spring has the only function of providing axial thrust to ensure the contact between the flange of the shield seal member and the vane surface, and is subject to the cooling air temperature rather than the hot gas temperature.
  • Shield seal member has no mechanical stress but is subject to the hot gas temperature.
  • the flexible seal member includes axial slots extending from the plate portion to the outer blade of the flexible seal member.
  • the main spring includes a base leaf configured to rest against the outlet member and at least one spring section including a front leaf and at least a plurality of leaves interposed between the base leaf and the front leaf and integrally connected to one another in an accordion configuration.
  • the seal assembly includes one spring section, as well as an associated flexible seal member and shield seal member, for each vane.
  • Spring sections operate in parallel but independently so as to adapt to individual vanes.
  • the present invention also relates to a gas turbine comprising an outer casing, a compressor, a plurality of can combustors downstream of the compressor and a turbine downstream of the can combustors, the compressor and turbine comprising fixed vanes carried by the outer casing and rotating blades carried by a rotor, the can combustors being spaced around the rotor and producing hot gas by combusting a mixture of air and at least one fuel, the gas turbine including, for each can combustor, a seal assembly as defined above, the seal assembly being axially interposed between an outlet member of the combustor and at least one turbine vane and radially interposed between an outer hot gas path and an inner space containing higher-pressure cooling air.
  • the difference of pressure between the higher-pressure cooling air and the hot gas path generates a sealing force on the flange of the shield seal member against the vane surface.
  • Figure 1 is a schematic view of a gas turbine 1.
  • Gas turbine 1 comprises a compressor 2, a combustor assembly 3 and a turbine 4.
  • Compressor 2 and turbine 4 have a common axis A and include respective sections of a rotor 5 rotatable about axis A.
  • ambient air 6 enters compressor 2 and is compressed.
  • Compressed air 7 leaves compressor 2 and enters a plenum 8, i.e. a volume defined by an outer casing 9.
  • a plenum 8 i.e. a volume defined by an outer casing 9.
  • compressed air 7 enters combustor assembly 3 that comprises a plurality of can combustors 10 annularly distributed around axis A.
  • combustor assembly 3 that comprises a plurality of can combustors 10 annularly distributed around axis A.
  • turbine 4 includes fixed vanes 14 carried by outer casing 9 and disposed in a plurality of axially spaced circumferential ranges, of which the first two are shown in fig.
  • each blade range is disposed downstream of a respective vane range so that the vanes guide the gas flow in an optimal direction toward the blades.
  • each combustor 10 includes a tubular combustion chamber 16 terminating in an outlet member 17 in the form of a frame of generally rectangular shape or, more precisely, an annulus section facing a plurality of vanes 14 of the first range; in the example shown, each outlet member 17 faces three vanes 14.
  • a seal assembly 18 is housed in a front curved elongated seat 19 provided in an arcuate radially inner side 20 of the outlet member 17. Seal assembly 18 projects towards vanes 14 and is configured to sealingly rest against a correspondingly arcuate plane front surface 21 of vanes 14, thereby sealing the hot gas path 12 from an inner space 22 which communicates with plenum 8 and thus contains compressed air (at a higher pressure than the hot gas path) which can be used as a cooling fluid.
  • Seal assembly 18 ( figures 3 , 5 ) includes a main spring 24 and, for each vane 14, a flexible seal member 25 and a shield seal member 26.
  • Main spring 24 has an arcuate, elongated shape so as to be partially housed inside seat 19 and includes a plain base leaf 27 configured to rest against a bottom shoulder 23 of seat 19 and a plurality of spring sections 28 extending axially from the base leaf 27 and partially projecting axially out of seat 19 towards respective vanes 14.
  • each spring section 28 there are three spring sections 28 extending each for substantially one third of the base leaf 27, being only slightly spaced form one another. Although only one flexible seal member 25 and one shield seal member 26 are shown in figure 5 , each spring section 28 has an associated flexible seal member 25 and a shield seal member 26.
  • Each spring section 28 comprises a plane front leaf 29 parallel to, and axially spaced from, base leaf 27, and two multiple-leaf spring sets 30 arranged in parallel with one another and extending between base leaf 27 and front leaf 29.
  • Spring sets 30 are symmetrical with respect to a median plane of the spring section 28.
  • each spring set 30 extends for substantially one longitudinal half of the spring section 28 and is formed by a plurality of leaves 31 integrally connected in series to one another at their ends in an "accordion” or “bellows” fashion. More specifically, each leaf 31 is spaced from the adjacent ones in an axial direction (i.e. parallel to axis A), and is slightly inclined so as to diverge axially from the preceding so as to form a zigzag pattern.
  • the end leaves 31 of each spring set 30 are joined to base leaf 27 and front leaf 29, respectively, at lateral ends of the spring section 28.
  • Main spring 24 finally includes a plurality of positioning pins 32 that project axially from base leaf 27 and are configured to engage corresponding bores (not shown) in outlet member 17.
  • Flexible seal members 25 ( figures 3-5 ) comprise, each, a substantially rectangular plate portion 34 elongated in circumferential direction and curved so as follow the radially outer contour of main spring 24.
  • An outer blade 35 is bent back axially from one circumferential side of plate 34 and extends parallel thereto. More specifically, outer blade 35 is formed by two radially offset portions, namely a spring portion 36 that is joined to plate 34 at end bend 37, and a seal portion 38 that is joined to spring portion 36 at an intermediate step 39 so as to be parallel to plate 34 and spaced therefrom more than spring portion 36.
  • Flexible seal member 25 includes an end flange 44 extending perpendicularly inward, i.e. on the opposite side of outer blade 35, from an end side of plate 34 opposite to end bend 37.
  • Flexible seal member 25 is finally provided with a plurality of axial slots 45 that are preferably equally spaced along its width. Slots 45 are provided in the form of axial cuts extending along most of plate 34 (except for a portion thereof adjacent end flange 44), end bend 37, spring portion 36, intermediate step 39 and part of seal portion 38.
  • plate 34 rests on the outer contour of a respective spring section 28 of main spring 24, and end flange 44 rests axially against front leaf 29 of spring section 28 ( figure 3 ).
  • Shield seal member 26 ( figures 3-5 ) includes a substantially rectangular plate 46 elongated in circumferential direction, which rests against plate 34 of flexible seal member 25, is tightly inserted between plate 34 and spring portion 36, and forms a gap 40 with seal portion 38 of outer blade 35 of flexible seal member 25.
  • Shield member 26 also includes an end flange 47 extending perpendicularly inward from an end side of plate 46 in axial contact against end flange 44 of flexible seal member 26.
  • flange 47 has a sealing lip 48 configured to rest against front surface 21 of vanes 14.
  • seal assembly 18 is partially housed within seat 19, with seal portion 38 of the flexible seal member 25 in radial elastic contact against the radially outer side of seat 19 due to the elastic deformation of spring portion 36, and sealing lip 48 against vane surface 21.
  • the distance D between surface 21 and shoulder 23 ( figure 3 ) is such that spring sections 28 are axially pre-compressed during assembly, so as to exert an axial load against flanges 44, 47 and ensure that the latter contacts surface 21 with sealing lip 48 under an elastic load.
  • This load is not the main force ensuring sealing; in fact, in use there is a pressure difference between the inner space including compressed cooling air and the hot gas path, which pressure difference presses flange 47 against surface 21.
  • Such pressure difference also ensures that cooling air flows in a controlled manner through slots 45, which form cooling channels connecting the inner space 22 to gap 40 which axially communicates with hot gas path 12, thereby cooling main spring 24, flexible seal member 25 and shield seal member 26.
  • seal assembly 18 is constituted by a plurality of elements, each of which is used in optimal mechanical and temperature conditions so as to ensure perfect sealing in variable operational conditions and over a long life span. Moreover, relatively large displacements can be accommodated.
  • Main spring 24 is configured to maintain the contact of seal assembly 18 with front surface 21 of vanes 14, and is subject to cooling air pressure and temperature.
  • Spring sections 28 are pre-compressed and operate in parallel but independently so as to adapt to individual vanes 14.
  • Flexible seal member 25 is aimed at ensuring sealing against the outlet member 17, adapting to thermal deformations. Slots 45 guarantee flexibility and cooling air flow; cooling air leakage may be estimated and tuned.
  • Shield seal member 26 which is the only element of seal assembly 18 that is subject to the hot gas path temperature, is free form mechanical stress and has a very simple design that provides for the main component of sealing pressure.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Ensemble joint d'étanchéité d'une turbine à gaz, configuré pour être interposé axialement entre un élément sortie (17) d'une chambre de combustion (10) et au moins une aube de turbine (14) et être interposé radialement entre un chemin de gaz chauds extérieur (12) et un espace intérieur (22) qui contient un air de refroidissement à haute pression, l'ensemble joint d'étanchéité comprenant :
    - au moins un ressort principal (24) qui exerce une charge élastique axiale, et qui est configuré pour être logé, en partie au moins, dans un siège (19) de l'élément sortie (17) ;
    - au moins un élément joint d'étanchéité souple (25) qui présente une partie plaque (34) disposée sur un côté extérieur du ressort principal (24) ; et
    - au moins un élément joint d'étanchéité de protection (26) qui présente une partie plaque (46) et une bride (47) configurée pour entrer en contact axialement avec une surface d'aube (21) sous la charge élastique axiale du ressort principal (24),
    caractérisé en ce que l'élément joint d'étanchéité souple (25) présente une lame extérieure (35) configurée pour coopérer de manière étanche radialement avec une surface extérieure radialement du siège (19), et en ce que la partie plaque (46) de l'élément joint d'étanchéité de protection (26), est disposée sur un côté extérieur de la partie plaque (34) de l'élément joint d'étanchéité souple (25).
  2. Ensemble joint d'étanchéité selon la revendication 1, dans lequel la lame extérieure (35) et la partie plaque (34) de l'élément joint d'étanchéité souple (25) sont connectées d'une pièce par un coude d'extrémité (37), la partie plaque (46) de l'élément joint d'étanchéité de protection (26), étant logée entre la partie plaque (34) et la lame extérieure (35) de l'élément joint d'étanchéité souple (25).
  3. Ensemble joint d'étanchéité selon la revendication 1 ou 2, dans lequel l'élément joint d'étanchéité souple (25) comprend des fentes axiales (45) qui s'étendent à partir de la partie plaque (34) vers la lame extérieure (35) de l'élément joint d'étanchéité souple (25).
  4. Ensemble joint d'étanchéité selon la revendication 2 ou 3, dans lequel la lame extérieure (35) comprend une partie ressort (36) adjacente au coude d'extrémité (37), et une partie joint d'étanchéité (38) connectée à la partie ressort (36) par un palier intermédiaire (39), la partie plaque (46) de l'élément joint d'étanchéité de protection (26) étant insérée étroitement entre la partie plaque (34) et la partie ressort (36) de l'élément joint d'étanchéité souple (25), pour former un intervalle (40) avec la partie plaque (34) de l'élément joint d'étanchéité de protection (26).
  5. Ensemble joint d'étanchéité selon la revendication 4, caractérisé en ce que l'élément joint d'étanchéité souple (25) comprend une bride d'extrémité (44) interposée entre le ressort principal (24) et la bride (47) de l'élément joint d'étanchéité de protection (26).
  6. Ensemble joint d'étanchéité selon l'une quelconque des revendications précédentes, dans lequel le ressort principal (24) comprend une lame de base (27) configurée pour reposer contre l'élément sortie (17) et au moins une section ressort (28) comprenant une lame avant (29) et au moins une pluralité de lames (31) interposées entre la lame de base (27) et la lame avant (29) et connectées les unes aux autres selon une configuration en accordéon.
  7. Ensemble joint d'étanchéité selon la revendication 6, quand elle dépend de la revendication 5, caractérisé en ce que ladite lame avant (29) entre en contact avec la bride d'extrémité (44) de l'élément joint d'étanchéité souple (25).
  8. Ensemble joint d'étanchéité selon la revendication 6 ou 7, caractérisé en ce que la ou les sections ressorts (28) comprennent deux ensembles (30) de ressorts à lames (31) interposés entre la lame de base (27) et la lame avant (29), et connectés les uns aux autres dans une configuration en accordéon, les deux ensembles (30) de ressorts à lames (31) étant symétriques par rapport à un plan médian de ladite section ressort (28).
  9. Ensemble joint d'étanchéité selon l'une quelconque des revendications précédentes, caractérisé en ce que ladite bride de l'élément joint d'étanchéité de protection comprend une lèvre (48) configurée pour entrer en contact avec une surface d'une aube respective (14).
  10. Ensemble joint d'étanchéité selon l'une quelconque des revendications 6 à 9, caractérisé en ce qu'il comprend une pluralité de sections ressorts (28) espacées le long de la lame de base, et une pluralité correspondante d'éléments joints d'étanchéité souples (25), et d'éléments joints d'étanchéité de protection (26) associés, chacun, à une section ressort respective (28).
  11. Turbine à gaz comprenant une enveloppe extérieure (9), un compresseur (2), une pluralité de chambres de combustion tubulaires (10) en aval du compresseur (2), et une turbine (4) en aval des chambres de combustion tubulaires (10), le compresseur (2) et la turbine (4) comprenant des aubes fixes (14) portées par l'enveloppe extérieure (9) et des pales tournantes (15) portées par un rotor (5), les chambres de combustion tubulaires (10) étant espacées autour du rotor (5) et configurées pour produire des gaz chauds en brûlant un mélange d'air et d'un combustible au moins, la turbine à gaz (1) comprenant, pour chaque chambre de combustion tubulaire (10), un ensemble joint d'étanchéité (18) selon l'une quelconque des revendications précédentes, l'ensemble joint d'étanchéité (18) étant interposé axialement entre un élément sortie (17) de la chambre de combustion (10) et au moins une aube de turbine (14) et interposé radialement entre un chemin des gaz chauds extérieur (12) et un espace intérieur qui contient un air de refroidissement à haute pression.
  12. Turbine à gaz selon la revendication 11, dans laquelle le ou les ressorts principaux (24) sont logés en partie au moins dans un siège (19) de l'élément sortie (17) et exercent une charge élastique axiale pour maintenir la bride (47) de l'élément joint d'étanchéité de protection (26) en contact axial avec une surface d'aube (21).
  13. Turbine à gaz selon la revendication 11 ou 12, dans laquelle lesdites fentes (45) définissent une pluralité de canaux de refroidissement qui permettent un écoulement contrôlé d'air de refroidissement à partir de l'espace intérieur (22) vers le chemin des gaz chauds (12).
  14. Turbine à gaz selon la revendication 13, caractérisée en ce que lesdits canaux de refroidissement connectent l'espace d'air de refroidissement intérieur à l'intervalle (40) formé entre la partie joint d'étanchéité (38) de l'élément joint d'étanchéité souple (25) et la partie plaque (46) de l'élément joint d'étanchéité de protection (26).
  15. Turbine à gaz selon l'une quelconque des revendications 11 à 14, caractérisée en ce que l'élément sortie (17) de chaque chambre de combustion tubulaire (10) fait face à une pluralité d'aubes (14), ledit ensemble joint d'étanchéité comprenant une pluralité de sections ressorts (28) espacées le long de la lame de base (27) et, pour chaque section ressort (28), un élément joint d'étanchéité souple (25) et un élément joint d'étanchéité de protection (26) entrent en contact avec l'aube respective (14).
EP19425005.6A 2019-01-28 2019-01-28 Joint d'étanchéité pour une turbine à gaz Active EP3686398B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19425005.6A EP3686398B1 (fr) 2019-01-28 2019-01-28 Joint d'étanchéité pour une turbine à gaz
CN202010074161.0A CN111502773B (zh) 2019-01-28 2020-01-22 密封组件

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19425005.6A EP3686398B1 (fr) 2019-01-28 2019-01-28 Joint d'étanchéité pour une turbine à gaz

Publications (2)

Publication Number Publication Date
EP3686398A1 EP3686398A1 (fr) 2020-07-29
EP3686398B1 true EP3686398B1 (fr) 2023-05-03

Family

ID=65635617

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19425005.6A Active EP3686398B1 (fr) 2019-01-28 2019-01-28 Joint d'étanchéité pour une turbine à gaz

Country Status (2)

Country Link
EP (1) EP3686398B1 (fr)
CN (1) CN111502773B (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114458449B (zh) * 2022-01-29 2023-08-11 中国航发湖南动力机械研究所 一种带导气功能的安装边连接结构
CN115218223B (zh) * 2022-07-20 2024-06-25 中国航发湖南动力机械研究所 陶瓷基火焰筒出口密封结构、涡轮发动机

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6418727B1 (en) * 2000-03-22 2002-07-16 Allison Advanced Development Company Combustor seal assembly
US6834507B2 (en) * 2002-08-15 2004-12-28 Power Systems Mfg., Llc Convoluted seal with enhanced wear capability
US8033786B2 (en) * 2007-12-12 2011-10-11 Pratt & Whitney Canada Corp. Axial loading element for turbine vane
US20100186415A1 (en) * 2009-01-23 2010-07-29 General Electric Company Turbulated aft-end liner assembly and related cooling method
US9488110B2 (en) * 2013-03-08 2016-11-08 General Electric Company Device and method for preventing leakage of air between multiple turbine components
US9404376B2 (en) * 2013-10-28 2016-08-02 General Electric Company Sealing component for reducing secondary airflow in a turbine system
US9366444B2 (en) * 2013-11-12 2016-06-14 Siemens Energy, Inc. Flexible component providing sealing connection
JP6372210B2 (ja) * 2014-07-14 2018-08-15 株式会社Ihi セラミックス基複合材料よりなるタービン静翼
US10047624B2 (en) * 2015-06-29 2018-08-14 Rolls-Royce North American Technologies Inc. Turbine shroud segment with flange-facing perimeter seal

Also Published As

Publication number Publication date
EP3686398A1 (fr) 2020-07-29
CN111502773B (zh) 2024-08-06
CN111502773A (zh) 2020-08-07

Similar Documents

Publication Publication Date Title
US9879555B2 (en) Turbine combustion system transition seals
CN107013257B (zh) 涡轮的带槽的弧形片密封件
US7037071B2 (en) Device for maintaining joints with sealing leaves
EP2532837B1 (fr) Ensemble d'étanchéité pour turbine à gaz
EP2871326A1 (fr) Composant flexible fournissant une connexion étanche et ensemble d'étanchéité
EP0903519B1 (fr) Dispositif de joint flexible en tissue
US6418727B1 (en) Combustor seal assembly
US9506374B2 (en) Component of a turbine with leaf seals and method for sealing against leakage between a vane and a carrier element
EP2247830B1 (fr) Joint souple pour turbine et turbine associée
US20130149125A1 (en) Turbine and method for manufacturing turbine
JP2011508151A (ja) タービンノズルセグメントおよびタービンノズルアセンブリ
JP2011508152A (ja) タービンノズルセグメント
US9234433B2 (en) Flap seal spring and sealing apparatus
EP3686398B1 (fr) Joint d'étanchéité pour une turbine à gaz
US8888445B2 (en) Turbomachine seal assembly
RU2350771C2 (ru) Обеспечение герметичности для отбора воздуха в кабину самолета при помощи сегментного соединения
US9057274B2 (en) Housing system for an axial turbomachine
EP3945246B1 (fr) Turbine à gaz pour centrales électriques doté d'un dispositif d'étanchéité en nid d'abeilles
CN115680897B (zh) 具有浮动密封组件的涡轮发动机
WO2020013837A1 (fr) Appareil d'étanchéité permettant de sceller un jeu radial entre des éléments fixes et rotatifs d'une turbine à gaz et procédé d'actionnement correspondant
EP3960991A1 (fr) Joint de chambre de combustion et procedé accosié

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

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

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: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20210128

RBV Designated contracting states (corrected)

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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20221028

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602019028342

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1564750

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230515

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20230503

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1564750

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230904

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230803

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230903

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230804

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

RAP4 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: ANSALDO ENERGIA S.P.A.

Owner name: ANSALDO ENERGIA SWITZERLAND AG

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602019028342

Country of ref document: DE

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: 20240206

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20240430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240128

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20240128

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240128

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: 20240128

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240131

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: 20240128

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240131

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240131

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240131

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20240131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240128

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240128

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20250120

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20250131

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20190128

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20190128

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20230503