EP2811118A1 - Segment d'aube directrice d'une turbomachine et turbine - Google Patents

Segment d'aube directrice d'une turbomachine et turbine Download PDF

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Publication number
EP2811118A1
EP2811118A1 EP13170852.1A EP13170852A EP2811118A1 EP 2811118 A1 EP2811118 A1 EP 2811118A1 EP 13170852 A EP13170852 A EP 13170852A EP 2811118 A1 EP2811118 A1 EP 2811118A1
Authority
EP
European Patent Office
Prior art keywords
platform
sealing
vane segment
downstream
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.)
Granted
Application number
EP13170852.1A
Other languages
German (de)
English (en)
Other versions
EP2811118B1 (fr
Inventor
Manfred Feldmann
Norbert Schinko
Janine Sangl
Alexander Buck
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 EP13170852.1A priority Critical patent/EP2811118B1/fr
Priority to ES13170852.1T priority patent/ES2664322T3/es
Priority to US14/295,970 priority patent/US9664057B2/en
Publication of EP2811118A1 publication Critical patent/EP2811118A1/fr
Application granted granted Critical
Publication of EP2811118B1 publication Critical patent/EP2811118B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/57—Seals

Definitions

  • the present invention relates to a stator segment of a turbomachine with an upstream and / or a downstream housing-side suspension and a platform according to the preamble of claim 1. Furthermore, the present invention relates to a turbine, in particular a gas turbine, according to the preamble of claim 10.
  • vanes can be fastened to the housing in different ways.
  • attachment is by means of upstream and downstream housing hanger connected to a vane platform from which the vane extends.
  • sealing elements may be integrated into individual vane segments to seal gaps or gaps that exist between adjacent vane segments. As a result, a seal of the flow channel with respect to the housing cavities is to be achieved.
  • An object of the present invention is to propose a further stator segment of a turbomachine with at least one first sealing section. Furthermore, it is an object of the present invention to propose a turbine with at least one vane segment.
  • the object of the invention is achieved by the vane segment with the features of claim 1. It is further achieved by a turbine having the features of claim 10.
  • a stator segment of a turbomachine which has an upstream, or front, and a downstream, or rear, housing-side suspension and a platform.
  • the Guide vane segment either an upstream or a downstream, housing-side suspension and a platform.
  • the suspensions are arranged on the platform.
  • the upstream chassis-side suspension may be located in the front portion of the platform and the downstream-side suspension in the rear portion of the platform.
  • the platform has a first sealing portion.
  • the platform extends beyond a connection region connecting the rear suspension to the platform with respect to the flow direction in use of the vane segment.
  • the first sealing portion which lies in a portion downstream of the connecting region, according to the invention has a first slot, which is continuous in the circumferential direction.
  • Embodiments of the invention may have one or more of the following features in any combination.
  • the turbomachine is a compressor or a turbine, in particular a gas turbine.
  • vane segment refers to an assembly or segment having one or more vanes and / or optionally optionally provided further sections (or elements, segments, parts) associated with the invention or the guide vanes are connected.
  • a vane segment is a vane cluster.
  • a Leitschaufelcluster may have a plurality of guide vanes, in particular three vanes, at least one, but usually two housing-side suspensions and at least one platform.
  • a vane may have at least one vane profile with a pressure and a suction side and a respective front and rear blade edge.
  • downstream enclosure-side suspension refers to a suspension that is located farther downstream in the direction of flow than an upstream or forward, further upstream suspension.
  • the flow direction can be referred to as the axial direction of the longitudinal axis of the turbomachine. Perpendicular to the axial direction is the radial direction. In a plane perpendicular to the axial direction, the circumferential direction.
  • the first sealing portion is a groove or a recess, hereinafter referred to as a groove.
  • a groove may have a U-profile in cross-section (perpendicular to the longitudinal direction).
  • a groove may have a rectangular, polygonal, semicircular or other cross-sectional shape.
  • the groove can be prepared and / or configured and / or configured for receiving a sealing element, for example a sealing plate, or have a sealing element.
  • the sealing plate can z. B. inserted into the groove, inserted, clamped or connected in a manner with the groove or be.
  • the sealing portion may effect communication between adjacent vane segments.
  • the sealing function of the sealing portion may be completely or at least partially fulfilled after the insertion of the sealing sheet.
  • the sealing function can serve to seal the flow channel in the direction of the cavities or with respect to the cavities of the housing of the turbomachine in the vane region.
  • sealing segments The first, as well as other sealing portions may be referred to as sealing segments.
  • the sealing portion is a receiving device or receiving device for a sealing plate or a plug-in sealing device.
  • connection region connecting the rear suspension to the platform designates the hub, joint, connecting portion or transition region between the downstream rearward housing-side suspension and the platform.
  • the lug may be made together with the suspension and the platform as a part or section, in particular made as a casting.
  • the casting may be referred to as an integral casting that collectively fulfills the function of the suspension, the platform, and the connection area (or transition area).
  • connection region has an increased accumulation of material, for example due to structurally necessary rounding and / or material reinforcements in the connection region.
  • the upstream suspension has a second sealing portion and the downstream suspension has a third sealing portion.
  • the first and / or the second and / or the third sealing section is designed for inserting sealing sheets or has sealing sheets.
  • the three sealing sections can be arranged in such a way and have sealing sheets such that a sealing of the housing cavities with respect to the throughflow region of the turbomachine is achieved.
  • the platform and the first seal portion extend downstream of the connection region beyond a vane profile trailing edge in the flow direction.
  • the vane segment may include one or more vanes.
  • the extent of the platform and the first sealing portion may refer to one or more vanes.
  • the vane segment has a plurality of guide vanes, it is contemplated according to the invention that the extent does not concern all the vanes, but is provided only with one or less than all vanes.
  • the first sealing portion of the platform extends completely or partially beyond the connecting portion of the rear suspension to the platform. Although only partially extending, the platform has a first sealing portion, but this does not extend beyond the connecting portion of the rear suspension.
  • the portion of the platform has a second slot downstream of the connection area.
  • the second slot may be continuous in the radial direction, for example, to the outside.
  • a radially inwardly outwardly continuous second slot is an outgoing from the first slot and in communication with this, outward (ie open in cavities of the housing) continuous or open slot.
  • the portion of the platform downstream of the connection region has a second slot that is continuous inward in the radial direction alone.
  • a radially inwardly continuous second slot is in this embodiment, from the first slot to the inside (up to the flow area of the turbomachine open) continuous slot.
  • the portion of the platform downstream of the connection region has a second slot that is radially outwardly and inwardly continuous.
  • the stiffness of the vane segment, in particular in the connection region between the rear suspension and the platform, can be advantageously reduced.
  • the second slot may have a square, rectangular, trapezoidal, oval or other cross section in a plane perpendicular to its longitudinal axis.
  • the longitudinal axis may be arranged in the circumferential direction straight or obliquely (diagonally) with respect to the circumferential and flow direction.
  • the portion of the platform that lies downstream of the connection region has a third slot that is continuous in the circumferential direction.
  • the second slot is disposed at one end (with respect to the circumferential direction) of the aforementioned portion, the third slot at the other end.
  • the portion of the platform downstream of the connecting region has a sectionally tapered wall thickness, ie a narrowing wall thickness.
  • the wall thickness can taper in the radial direction and / or in the circumferential direction.
  • the vane segment has at least two vanes.
  • a vane segment having at least two vanes may be referred to as a vane cluster.
  • the vane cluster may in particular have three guide vanes.
  • the vane segment is manufactured as a casting, in particular as an integral casting, in particular in one piece.
  • a casting may be referred to as having multiple functional parts or sections.
  • An integral vane segment may include one or more vanes, further comprising front and / or rear chassis side hangers, and a platform.
  • a vane segment, which is produced as a casting, is reworked, for example ground, in particular at the abutment surfaces to adjacent further vane segments. Furthermore, provided sealing sections cast guide vane segment can be reworked.
  • the sealing portions are produced or reworked by means of erosion in some embodiments according to the invention.
  • Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.
  • connection points or joints of guide blade segments in particular of guide blade clusters, can be sealed with the aid of sealing sheets.
  • sealing sections, sealing grooves or sealing slots can be introduced into the abutting surfaces in the hub and housing region of the gas turbines, in which the sealing plates are inserted during assembly of the turbomachine.
  • the sealing of the gas or flow channel in the direction of the housing cavities in the vane region can take place.
  • housing-side suspension with the platform of the guide blade segment may result from structurally related reinforcements, for example, by applying material to abutting edges, which lead to rounding, an increase of material result. This can become one Increase in stiffness in this area, which may have a negative effect on the tolerable thermomechanical load cycles in the area of the pressure-side blade trailing edge and may result in unintentional early failure of the component according to the prior art.
  • a reduction of the rigidity in the embodiment of the guide blade segment can be accompanied or achieved with a reduction of the sealing sheet length.
  • the gap seal may decrease or decrease, which may result in an increase in leakage losses.
  • the first slot according to the invention which has the first sealing section of the guide blade segment according to the invention
  • a reduction of the rigidity of the guide blade segment, in particular in the connection region of the rear, housing-side suspension with the platform can be advantageously achieved.
  • a reduction in the rigidity-and thus indirectly an increase in the load cycles sustained in the operation of the turbomachine-can advantageously be achieved by a vane segment according to the invention (because of the integration of sealing sections as narrow webs at the joint of the outside of the rear platform).
  • the extension or continuation of the sealing sheets or their trailing edges beyond the guide blade trailing edges can advantageously improve the sealing of the housing cavities in the region of the rear platform (reduction of the thermal entry into the rear housing suspension or the possibility of using less cooling air).
  • Fig. 1 shows a perspective view of a section of a guide vane segment 100 according to the invention.
  • the vane segment 100 comprises an upstream housing-side suspension 1, a downstream housing-side suspension 3, a platform 5, and three guide vanes 200.
  • Each vane 200 has a pressure side 7, a rear suction side 9 (obscured), a vane leading edge 11, and a vane trailing edge 13.
  • connection region 15 connects the rear suspension 3 to the platform 5, which merge into one another in the connection region 15.
  • Fig. 1 a first sealing portion 17 which extends into a portion 18 downstream of the connecting portion 15 inside.
  • the first sealing section 17 is designed or manufactured in the section 18 as the first slot 19.
  • the first slot 19 is continuous in the circumferential direction z.
  • the blade assembly 100 has a second sealing portion 17a in the upstream suspension 1 and a third sealing portion 17b in the downstream suspension 3.
  • sealing plates can be inserted.
  • these sealing plates By means of these sealing plates, the joints or joints to other sealing portions in adjacent vane segments (in Fig. 1 not shown) bridged and sealed with it.
  • these sealing sheets can also fulfill a thermal sealing function, or thermal insulation, in the form of a heat shield.
  • the sealing plates can thus fulfill an integral function with regard to the flow-related and the temperature-related sealing function between the flow channel and the housing.
  • the sealing plate which is inserted into the first sealing portion 17, may extend into the portion 19 of the platform 5.
  • This sealing plate can extend in the circumferential direction of the first slot 19 either only over part of the entire slot depth (eg corresponding to the depth of the first sealing section 17 in the circumferential direction), over the entire slot depth, or over the entire slot depth.
  • the rigidity of the section 18 is influenced accordingly. For example, the rigidity is smaller with a small depth of the sealing plate in the circumferential direction.
  • Fig. 2 shows another perspective view of the in Fig. 1 shown guide vane segment 100 according to the invention.
  • the first slot 19 is continuous in the section 18 in the circumferential direction z.
  • Fig. 3a shows a detail of a perspective view of another guide vane segment 100 according to the invention with a second slot 20, which in both the radial direction y and in the circumferential direction z is open or continuous.
  • Fig. 3b shows another perspective view of the in Fig. 3a shown further guide vane segment 100 according to the invention.
  • Fig. 4a shows a detail of a perspective view of yet another guide vane segment 100 according to the invention.
  • the first slot 19 extends in the flow stream x shortened in the section 18, compared with its extension in Fig. 1 and Fig. 2 , As a result of this reduction, the wall thickness 21 is made narrower in the radial direction y with respect to the wall thickness 23 with the slot 19. Thus, the rigidity of the portion 18 can be advantageously reduced.
  • Fig. 4b shows another perspective view of the in Fig. 4a shown further guide vane segment 100 according to the invention.
  • vane segment 200 vane x The direction of flow; axially y radial direction z circumferentially 1 upstream, front housing-side suspension 3 downstream, rear-side suspension 5 platform 7 Pressure side of the vane 9 Suction side of the vane 11 vane leading edge 13 vane trailing 15 Connection area; connects the rear suspension with the platform 17 first sealing section 17a, 17b second / third sealing section 18 Section of the platform downstream of the connection area 19 first slot 20 second slot 21 Wall thickness in the radial direction without sealing section 23 Wall thickness in the radial direction with sealing section

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13170852.1A 2013-06-06 2013-06-06 Segment d'aube directrice d'une turbomachine et turbine Not-in-force EP2811118B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13170852.1A EP2811118B1 (fr) 2013-06-06 2013-06-06 Segment d'aube directrice d'une turbomachine et turbine
ES13170852.1T ES2664322T3 (es) 2013-06-06 2013-06-06 Segmento de álabes directores de una turbomáquina y una turbina
US14/295,970 US9664057B2 (en) 2013-06-06 2014-06-04 Stator vane segment of a fluid flow machine and turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13170852.1A EP2811118B1 (fr) 2013-06-06 2013-06-06 Segment d'aube directrice d'une turbomachine et turbine

Publications (2)

Publication Number Publication Date
EP2811118A1 true EP2811118A1 (fr) 2014-12-10
EP2811118B1 EP2811118B1 (fr) 2018-03-14

Family

ID=48625786

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13170852.1A Not-in-force EP2811118B1 (fr) 2013-06-06 2013-06-06 Segment d'aube directrice d'une turbomachine et turbine

Country Status (3)

Country Link
US (1) US9664057B2 (fr)
EP (1) EP2811118B1 (fr)
ES (1) ES2664322T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3176388A1 (fr) * 2015-12-04 2017-06-07 MTU Aero Engines GmbH Segment d'aube directrice à sécurité radiale

Families Citing this family (5)

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Publication number Priority date Publication date Assignee Title
US20180355754A1 (en) * 2017-02-24 2018-12-13 General Electric Company Spline for a turbine engine
KR101986021B1 (ko) * 2017-10-23 2019-06-04 두산중공업 주식회사 씰링어셈블리 및 이를 포함하는 가스터빈
US10655489B2 (en) * 2018-01-04 2020-05-19 General Electric Company Systems and methods for assembling flow path components
US11885241B1 (en) 2022-07-28 2024-01-30 General Electric Company Turbine nozzle assembly with stress relief structure for mounting rail
US11814991B1 (en) * 2022-07-28 2023-11-14 General Electric Company Turbine nozzle assembly with stress relief structure for mounting rail

Citations (3)

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Publication number Priority date Publication date Assignee Title
US5154577A (en) * 1991-01-17 1992-10-13 General Electric Company Flexible three-piece seal assembly
EP1074695A2 (fr) * 1999-08-02 2001-02-07 United Technologies Corporation Méthode pour réaliser un passage de refroidissement dans une aube de turbine
US20100284800A1 (en) * 2009-05-11 2010-11-11 General Electric Company Turbine nozzle with sidewall cooling plenum

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US6241467B1 (en) * 1999-08-02 2001-06-05 United Technologies Corporation Stator vane for a rotary machine
ATE487025T1 (de) * 2007-06-28 2010-11-15 Alstom Technology Ltd Leitschaufel für eine gasturbine
EP2300686B1 (fr) * 2008-05-26 2013-08-07 Alstom Technology Ltd Turbine à gaz pourvue d'une aube directrice
US8371800B2 (en) * 2010-03-03 2013-02-12 General Electric Company Cooling gas turbine components with seal slot channels
US20120128472A1 (en) * 2010-11-23 2012-05-24 General Electric Company Turbomachine nozzle segment having an integrated diaphragm
US8376705B1 (en) * 2011-09-09 2013-02-19 Siemens Energy, Inc. Turbine endwall with grooved recess cavity
FR2990719B1 (fr) * 2012-05-16 2016-07-22 Snecma Distributeur de turbomachine, et procede de fabrication
US20130315708A1 (en) * 2012-05-25 2013-11-28 Jacob Romeo Rendon Nozzle with Extended Tab

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5154577A (en) * 1991-01-17 1992-10-13 General Electric Company Flexible three-piece seal assembly
EP1074695A2 (fr) * 1999-08-02 2001-02-07 United Technologies Corporation Méthode pour réaliser un passage de refroidissement dans une aube de turbine
US20100284800A1 (en) * 2009-05-11 2010-11-11 General Electric Company Turbine nozzle with sidewall cooling plenum

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3176388A1 (fr) * 2015-12-04 2017-06-07 MTU Aero Engines GmbH Segment d'aube directrice à sécurité radiale
DE102015224378A1 (de) * 2015-12-04 2017-06-08 MTU Aero Engines AG Leitschaufelsegment mit Radialsicherung
US10370989B2 (en) 2015-12-04 2019-08-06 MTU Aero Engines AG Guide vane segment with radical securing elements

Also Published As

Publication number Publication date
ES2664322T3 (es) 2018-04-19
EP2811118B1 (fr) 2018-03-14
US20140363284A1 (en) 2014-12-11
US9664057B2 (en) 2017-05-30

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