EP2826962B1 - Turbomachine avec segments d'étanchéité et segments d'aube directrice - Google Patents

Turbomachine avec segments d'étanchéité et segments d'aube directrice Download PDF

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Publication number
EP2826962B1
EP2826962B1 EP13176503.4A EP13176503A EP2826962B1 EP 2826962 B1 EP2826962 B1 EP 2826962B1 EP 13176503 A EP13176503 A EP 13176503A EP 2826962 B1 EP2826962 B1 EP 2826962B1
Authority
EP
European Patent Office
Prior art keywords
sealing
segments
segment
row
vane
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
EP13176503.4A
Other languages
German (de)
English (en)
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EP2826962A1 (fr
Inventor
Walter Gieg
Petra Kufner
Rudolf Stanka
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP13176503.4A priority Critical patent/EP2826962B1/fr
Priority to ES13176503.4T priority patent/ES2581511T3/es
Priority to US14/329,570 priority patent/US9982566B2/en
Publication of EP2826962A1 publication Critical patent/EP2826962A1/fr
Application granted granted Critical
Publication of EP2826962B1 publication Critical patent/EP2826962B1/fr
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2240/11—Shroud seal segments

Definitions

  • the invention relates to a turbomachine according to the preamble of patent claim 1.
  • a sealing segment ring For sealing a radial gap between blade tips of a blade row and a blade section surrounding a turbine section of a turbomachine such as a gas turbine usually a sealing segment ring is provided, which extends on the housing side between a front blade row and a rear blade row.
  • the sealing segment ring consists of a plurality of identical sealing segments, each having a plurality of slots for positive engagement with an equal number of protrusions of the front guide blade row for circumferential securing at its front edge portion.
  • the vane rows consist of a plurality of identical vane segments, wherein in this type of circumferential securing the number of sealing segments is equal to the number of front vane segments or the front vane segments are an integer multiple of the sealing segments. With 15 vane segments, there are usually 15, 5 or 3 sealing segments. In the US 2005002779 A1 Such a circumferential securing in the region of a rear edge portion of the sealing segments and a rear vane row is shown.
  • the object of the invention is to provide a turbomachine with a circumferential securing a sealing segment ring with an alternative sealing segment number for sealing a radial gap between a housing portion and a blade row.
  • a turbomachine according to the invention has a sealing segment ring between a front row of vanes and a rear row of vanes for sealing a radial gap between a housing portion and a row of blades revolving between the rows of vanes.
  • the sealing segment ring has a plurality of identical sealing segments and at least one of the rows of stator blades has a plurality of identical vane segments.
  • the sealing segments each have a plurality of circumferentially adjacent receptacles for cooperation with securing elements of this guide blade row, wherein the receptacles and securing elements are distributed uniformly over the circumference and the receptacles are a multiple of the securing elements, and each vane segment of this vane row has a securing element.
  • the invention enables circumferential securing and the formation of a sealing segment ring whose sealing segment number is not an integral subset of a number of vane segments. With 15 vane segments, for example, 10 sealing segments can be realized thanks to the invention. The number of sealing segments can thus be determined optimally according to structure-mechanical, manufacturing-technical and / or cost-related aspects. Because the receptacles are a multiple of the securing elements, not all receptacles are in the mounted state in engagement with the securing elements and can thus serve to equalize different thermal expansion behavior of the sealing segments and the vane segments.
  • each sealing segment is merely connected to a vane segment of this vane row by means of a receiving-securing element engagement.
  • a receiving-securing element engagement By only one positive connection per sealing segment and vane segment jamming of the components is prevented during assembly.
  • each sealing segment has a same plurality of receptacles and these and the securing elements are arranged at identical positions of the sealing segments or the guide blade segments.
  • the production of the sealing segments and of the guide blade segments is simplified by the respective same arrangement of the receptacles and securing elements.
  • the securing element of the respective vane segment and the receptacles of the respective sealing segment are arranged symmetrically to the respective segment longitudinal axis.
  • 1.5 times as many vane segments of the vane row as sealing segments and per sealing segment three times as many receptacles as securing elements per vane segment are provided.
  • every second receptacle is in engagement with a securing element or the receptacles are alternately occupied by a respective securing element.
  • the recordings are in alternating engagement with a securing element. The double intervention here must be taken into account when designing tolerances and thermal expansion forces.
  • An inventive sealing segment for a turbomachine according to the invention has a plurality of circumferentially uniformly spaced apart receptacles for cooperation with a corresponding securing element.
  • An inventive vane segment for a turbomachine according to the invention has only one securing element for cooperating with a corresponding receiving a sealing segment.
  • a turbomachine 1 viewed in the direction of a hot gas flowing through a hot gas channel 2, has a front stator-side guide blade row 4 and a rear stator-side stator blade row 6, between which a rotor-side blade row 8 rotates about a rotor axis (not shown).
  • the blade row 8 is encompassed by a housing portion 10 of the turbomachine 1, wherein a sealing segment ring 12 is arranged for sealing a radial gap between the blade row 8 and the housing portion 10 between the guide blade rows 4, 6.
  • the turbomachine is in particular a gas turbine and preferably an aircraft engine.
  • the blade rows 4, 6, 8 and the sealing segment ring 12 are preferably located in the low-pressure turbine of the turbomachine 1.
  • the front vane row 4 has a plurality of identical vane segments 14, each having a plurality of airfoils and by means of a front holding portion 16 and a rear holding portion 18 positively engage in housing grooves 20 and the like of the turbomachine 1.
  • the rear vane row 6 has a plurality of identical vane segments 22, which cooperate in a form-fitting manner via front holder sections 24 and rear holding sections, not shown, with housing grooves 26 and the like of the turbomachine 1.
  • the sealing segment ring 12 has a plurality of identical sealing segments 28, each having a multi-angled base body 30, on whose the hot gas channel 2 facing inner surface sealing honeycomb 32 for running in opposite sealing webs 34, 36 of the blade row 8 are arranged.
  • the sealing segment ring 12 and the sealing webs 34, 36 form the so-called Outer Air Seal (OAS).
  • OAS Outer Air Seal
  • each base body 30 With its front edge portion 38 and its rear edge portion 40, each base body 30 is in axial overlap with platform overhangs 42, 44 of the vane segments 14, 22.
  • Die Platform overhangs 40, 42 are guided over the respective edge section 38, 40 or the edge sections 38, 40 are guided under the respective platform overhang 42, 44.
  • the edge sections 38, 40 are thus arranged radially outside the platform overhangs 40, 42.
  • the front guide blade segments 14 each have a securing element, which in the embodiment shown here is a securing web 46, with which the sealing segments 28 cooperate positively.
  • the securing webs 46 each extend at a distance from the platform along a rear side 48 of the rear holder section 18 of the respective guide blade segment 14 radially outward.
  • the sealing segments 28 each have a plurality of receptacles, which are formed in the embodiment shown here as slots 50.
  • the slots 50 are opened upstream and respectively pass through the front edge portion 38 of the base body 30.
  • Each vane segment 14a, 14b, 14c, 14d has a single securing leg 46a, 46b, 46c, 46d positioned circumferentially centrally on the back 48 of the rear retaining sections 18 in the embodiment shown here.
  • the position of the securing bar 46a, 46b is not limited to a center position.
  • the securing webs 46a, 46b, 46c, 46d are located at identical positions of the vane segments 14a, 14b, 14c, 14d. A circumferential distance to both side edges 52, 54 of the holding portion 18 is thus equal.
  • the respective single securing web 46a, 46b, 46c, 46d per vane segment 14a, 14b, 14c, 14d lies on a longitudinal axis of the respective vane segment 14a, 14b, 14c, 14d which extends approximately in the flow direction of the hot gas and is therefore symmetrical in the circumferential direction to the longitudinal axis oriented. Viewed over the circumference of the guide blade row 4, the securing webs 46a, 46b, 46c, 46d are uniformly spaced from one another.
  • the sealing segments 28a, 28b, 28c each have three slots 50a, 56a, 58a and 50b, 56b, 58b and 50c, respectively FIG. 2 for distinguishing dividing lines 60, 62, 64, 66 between adjacent sealing segments 28a, 28b, 28c and adjacent vane segments 14a, 14b, 14c, 14d are shown as dots. Due to the detail in FIG. 2 Of the three slots of the sealing segment 28c, only the slot 50c is visible.
  • the slots 50a, 56a, 58a and 50b, 56b, 58b and 50c are at identical positions of the sealing segments 28a, 28b, 28c.
  • the number of slots 50a, 56a, 58a or 50b, 56b, 58b and 50c per sealing segment 28a, 28b, 28c (here three slots 50, 56, 58 per sealing segment 28) is thus an integer multiple of the number of securing webs 46a, 46b, 46c, 46d per vane segment 14a, 14b, 14c, 14d (here one securing ridge 46 per vane segment 14).
  • the slots 50a, 56a, 58a and 50b, 56b, 58b and 50c are circumferentially symmetrical to the longitudinal axis of the sealing segments 28a, 28b, 28c extending approximately in the direction of flow of the hot gas.
  • a slot 56a, 56b lies directly on the longitudinal axis and is located at the same circumferential distance from side edges 68, 70 of the respective sealing segment 28a, 28b, 28c.
  • the two other slots 50a, 58a and 50b, 58b and 50c is located on both sides of the respective central slot 56a, 56b.
  • lateral slots 50a, 58a and 50b, 58b and 50c are located at an equal circumferential distance from the central slot 56a, 56b and thus at an equal circumferential distance to the respective adjacent side edge 68, 70.
  • the lateral slots 50a, 58a or 50b, 58b and 50c are also at an equal circumferential distance from the respective side edge 70, 68.
  • the slots 50a, 56a, 58a and 50b, 56b, 58b and 50c are equally spaced from each other.
  • the circumferential distance of the lateral slots 50a, 58a or 50b, 58b and 50c to the central slot 56a, 56b is twice as large in the embodiment shown here as the circumferential distance to the respective adjacent side edge 68, 70th
  • the sealing segments 28a, 28b, 28c have a greater extent in the circumferential direction than the vane segments 14a, 14b, 14c, 14d, so that the parting lines 60, 62 between the sealing segments 28a, 28b, 28c are circumferentially offset from the parting lines 64, 66 of the vane segments 14a , 14b, 14c, 14d are arranged.
  • a sealing segment 28a, 28b, 28c has 1.5 times the circumferential extent as a Leitschaufelsegment14a, 14b, 14c, 14d.
  • each second slot 50a, 58a, 56b, 50c of the sealing segment ring 12 is in engagement with a securing web 46a, 46b, 46c, 46d.
  • every second slot 56a, 50b, 58b is free.
  • the securing web 46a engages in the slot 50a, the securing web 46b in the slot 58a, the securing web 46c in the slot 56b and the securing web 46d in the slot 50c.
  • the slots 56a, 50b and 58b are not occupied.
  • each vane segment 14a, 14b, 14c, 14d has only one securing web 46a, 46b, 46c, 46d, each vane segment 14a, 14b, 14c, 14d forms only a form-locking connection with a sealing segment 28a, 28b, 28c or only one circumferential securing device for a sealing segment 28a, 28b, 28c.
  • sealing segments 28a with multiple vane segments 14a, 14b are in positive engagement at the same time.
  • the securing webs 46a, 46b of the guide blade segments 14a, 14b engage in a form-fitting manner in the slots 50a, 58a of the sealing segment 28a.
  • a turbomachine having a sealing segment ring between a front row of vanes and a rear row of vanes for sealing a radial gap between a housing portion and a row of blades revolving between the rows of vanes, the sealing segment ring having a plurality of like sealing segments and at least one of the plurality of vanes having a plurality of like vane segments, wherein the sealing segments each have a plurality of circumferentially adjacent receptacles for interacting with securing elements of this guide vane row, wherein the receptacles and securing elements are distributed uniformly over the circumference and the receptacles are a multiple of the securing elements, a sealing segment and a vane segment.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (4)

  1. Turbomachine (1) comprenant une couronne de segments d'étanchéité (12) placée entre une rangée avant d'aubes directrices (4) et une rangée arrière d'aubes directrices (6) pour rendre étanche un espace radial ménagé entre une partie de boîtier (10) et une rangée d'aubes directrices (8) circulant entre les aubes directrices (4, 6), la couronne de segments d'étanchéité (12) comportant une pluralité de segments d'étanchéité (28) identiques et au moins une rangée d'aubes directrices (4) comportant une pluralité de segments d'aube directrice (14) identiques, les segments d'étanchéité (28) comportant chacun une pluralité de logements (50, 56, 58) adjacents dans la direction circonférentielle et destinés à coopérer avec des éléments de fixation (46) de cette rangée d'aubes directrices (4), et les logements (50, 56, 58) et éléments de fixation (46) étant répartis uniformément sur la circonférence, caractérisée en ce que les logements (50, 56, 58) sont un multiple des éléments de fixation (46), et en ce que chaque segment d'aube directrice (14) de cette rangée d'aubes directrices (4) ne comporte qu'un seul élément de fixation (46).
  2. Turbomachine selon la revendication 1, dans laquelle chaque segment d'étanchéité (28) comporte une même pluralité de logements (50, 56, 58) et les logements (50, 56, 58) et les éléments de fixation (46) sont disposés aux mêmes positions des segments d'étanchéité (28) ou des segments d'aube directrice (14) de cette rangée d'aubes directrices (4).
  3. Turbomachine selon la revendication 1 ou 2, dans laquelle l'élément de fixation (46) du segment d'aube directrice (14) respectif et les logements (50, 56, 58) du segment d'étanchéité (28) respectif sont disposés symétriquement par rapport à l'axe longitudinal du segment respectif.
  4. Turbomachine selon l'une des revendications précédentes, dans laquelle le nombre de segments d'aube directrice (14) de cette rangée d'aubes directrices (4) est égal à 1,5 fois le nombre de segments d'étanchéité (28) et le nombre de logements (50, 56, 58) par segment d'étanchéité (28) est égal à trois fois le nombre d'éléments de fixation (46) par segment d'aube directrice (14).
EP13176503.4A 2013-07-15 2013-07-15 Turbomachine avec segments d'étanchéité et segments d'aube directrice Active EP2826962B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13176503.4A EP2826962B1 (fr) 2013-07-15 2013-07-15 Turbomachine avec segments d'étanchéité et segments d'aube directrice
ES13176503.4T ES2581511T3 (es) 2013-07-15 2013-07-15 Turbomáquina, segmento de sellado y segmento de álabe de guía
US14/329,570 US9982566B2 (en) 2013-07-15 2014-07-11 Turbomachine, sealing segment, and guide vane segment

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13176503.4A EP2826962B1 (fr) 2013-07-15 2013-07-15 Turbomachine avec segments d'étanchéité et segments d'aube directrice

Publications (2)

Publication Number Publication Date
EP2826962A1 EP2826962A1 (fr) 2015-01-21
EP2826962B1 true EP2826962B1 (fr) 2016-06-22

Family

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Application Number Title Priority Date Filing Date
EP13176503.4A Active EP2826962B1 (fr) 2013-07-15 2013-07-15 Turbomachine avec segments d'étanchéité et segments d'aube directrice

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US (1) US9982566B2 (fr)
EP (1) EP2826962B1 (fr)
ES (1) ES2581511T3 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2628679T3 (es) * 2013-12-04 2017-08-03 MTU Aero Engines AG Elemento de estanqueidad, dispositivo de estanqueidad y turbomáquina
DE102015224160A1 (de) * 2015-12-03 2017-06-08 MTU Aero Engines AG Einlaufbelag für eine äußere Luftdichtung einer Strömungsmaschine
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
DE102018210600A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Mantelringanordnung für eine strömungsmaschine

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3365173A (en) * 1966-02-28 1968-01-23 Gen Electric Stator structure
GB2310255B (en) * 1996-02-13 1999-06-16 Rolls Royce Plc A turbomachine
GB0218060D0 (en) * 2002-08-03 2002-09-11 Alstom Switzerland Ltd Sealing arrangements
GB2395756B (en) * 2002-11-27 2006-02-08 Rolls Royce Plc Cooled turbine assembly
JP4269829B2 (ja) * 2003-07-04 2009-05-27 株式会社Ｉｈｉ シュラウドセグメント
US7186078B2 (en) 2003-07-04 2007-03-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
DE10359730A1 (de) * 2003-12-19 2005-07-14 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
WO2008128876A1 (fr) * 2007-04-19 2008-10-30 Alstom Technology Ltd Écran thermique de stator
DE102007031711A1 (de) * 2007-07-06 2009-01-08 Rolls-Royce Deutschland Ltd & Co Kg Gehäusedeckbandsegment-Aufhängung
JP5384983B2 (ja) * 2009-03-27 2014-01-08 本田技研工業株式会社 タービンシュラウド
US20110243725A1 (en) * 2010-03-31 2011-10-06 General Electric Company Turbine shroud mounting apparatus with anti-rotation feature

Also Published As

Publication number Publication date
US20150016969A1 (en) 2015-01-15
EP2826962A1 (fr) 2015-01-21
US9982566B2 (en) 2018-05-29
ES2581511T3 (es) 2016-09-06

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