EP1861583B1 - Wärmestausegment - Google Patents

Wärmestausegment Download PDF

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Publication number
EP1861583B1
EP1861583B1 EP06725188A EP06725188A EP1861583B1 EP 1861583 B1 EP1861583 B1 EP 1861583B1 EP 06725188 A EP06725188 A EP 06725188A EP 06725188 A EP06725188 A EP 06725188A EP 1861583 B1 EP1861583 B1 EP 1861583B1
Authority
EP
European Patent Office
Prior art keywords
joining
contoured
radially
axially
heat shield
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.)
Not-in-force
Application number
EP06725188A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1861583A1 (de
Inventor
Alexander Khanin
Edouard Sloutski
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to SI200630608T priority Critical patent/SI1861583T1/sl
Publication of EP1861583A1 publication Critical patent/EP1861583A1/de
Application granted granted Critical
Publication of EP1861583B1 publication Critical patent/EP1861583B1/de
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
    • 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
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the invention relates to a heat recovery segment for local separation of a flow channel within a flow rotating machine, in particular gas turbine plant, opposite to a stator radially surrounding the stator housing, with two axially opposite joining contours, which are each engageable with two along the flow channel axially adjacent components.
  • Heat accumulation segments of the type described above are part of axial flow-through turbomachines through which flow for compression or targeted expansion gaseous working media and due to their high process temperatures, the thermally heavily loaded with the hot working fluids system components.
  • the guide vanes arranged axially one after the other in the rows of rotor blades and vanes are acted upon directly by the combustion gases produced in the combustion chamber.
  • so-called heat accumulation segments which are provided on the stator side between two guide vanes arranged axially adjacent to one another, ensure a gas-tight bridge-like seal between the two axially adjacent one another arranged guide blade rows.
  • Correspondingly designed heat accumulation segments can also be used along the rotor unit. These are each to be mounted on the rotor side between two axially adjacent rotor blade rows in order to protect rotor core areas from excessive heat input.
  • FIG. 2 illustrates a partial longitudinal section through a gas turbine stage, in which a flow channel K is bounded radially inwardly by a rotor unit 1 and radially outward by a stator unit 2. Rotationally fixed to the rotor unit 1, blades 3 protrude radially in the flow channel K, which is flowed through axially in the rest of hot gases with the direction of arrow oriented flow direction.
  • the flow channel K is bounded by stator vanes 4 attached to the stator, whose guide vanes 41 protrude radially into the flow channel K from the outside.
  • the guide vanes 4 have for the gas-tight separation of the flow channel K relative to the stator-mounted components on a platform 42 which covers both the axial region immediately around the vane blade 41 as a one-piece component in the form of a balcony-like overhang 42 ', the area between two rows of vanes spans and radially opposite the blade tips.
  • the guide vanes 4 are arranged in the circumferential direction of the gas turbine in each row of guide blades, it is true that within a row of guide vanes in the circumferential direction immediately adjacent arranged vanes 4 along their axial side edges 5 to connect gas-tight with each other. This purpose is served over the entire extent of the side edge 5 extending belt seal 6, which opens on both sides in corresponding grooves along the side edges of two adjacent vanes.
  • the band seal 6 ensures, in particular, that the platform 42 cooling air supplied to the stator can not escape into the flow channel K and is therefore available through appropriate cooling channels within the guide vane for effective cooling of all the vane areas exposed to the hot gases.
  • the guide vane 4 is joined in each case via two collar-like joint contours 8, 9 in engagement with corresponding recesses 10, 11 within the support structure 7 removable joint connection between a stator 4 and a supporting stator supporting structure.
  • the individual guide vanes 4 can be removed or inserted in the circumferential direction from or into the groove-shaped recesses 10, 11.
  • the object of the invention is to effectively counteract the above-described wear phenomena due to mechanical vibrations on the band seals provided between two guide vanes. It should be ensured that the maintenance intervals required to inspect these seals are considerably extended. Consequently, the assembly and disassembly effort, which is required for the inspection and, where appropriate, for the replacement of appropriate sealing materials, should be significantly reduced. In particular, it should not be necessary for the removal of individual guide vanes from the composite of a row of guide vanes to dismantle the entire number of vanes or at least segment regions of the number of vanes.
  • the idea underlying the invention is fundamentally based on a separation of the vane platform 42 and the balcony-like platform section 42 ', which according to image representation in FIG. 2 are integrally formed. It is proposed that between two rows of blades axially extending portion separated by means of a separate, bridge-like heat dam segment, ie between each two axially adjacent vanes extends a heat shield segment and adjacent on both sides as possible gas-tight on the vanes. Corresponding to the number of vanes within a row of vanes, correspondingly many heat accumulation segments are provided in the circumferential direction, which accordingly form a series of heat stacks, along the axial extent of which the blades of a blade row circulate radially inward.
  • Such a heat dissipation segment which basically serves for the local separation of a flow channel within a flow-rotating machine, in particular a gas turbine plant, with respect to a stator housing radially surrounding the flow channel, with two axially opposite joining contours, each in engagement with two axially adjacent components along the flow channel, in particular two Guide vanes, can be brought, according to the solution is designed such that a first of the two joining contours has a radially oriented recess with a contour surface, to the radially a Fastening pin with an outer contour from the side of a force adjacent to the first joining contour adjacent component is available kraftbeaufschlagt. Furthermore, the first joining contour has a collar portion with a radially upper and lower collar surface, which is available in a counter contoured receiving contour within the axially adjacent component by a joining force acting between the fastening pin and the contour surface.
  • the fastening pin preferably has a cylindrical outer contour which comes into operative connection with the contour surface of the recess.
  • it is a so-called cylindrical mounting pin, which is flush pressed against a correspondingly contoured contoured cylindrical contour surface and ensures a secure fit of the heat shield segment on the adjacent component.
  • the heat recovery segment according to the invention is releasably fixedly connected to a guide vane arranged axially adjacent only over a single joining region.
  • the second joining region of the heat recovery segment which is axially opposite this joining region is loosely pressed against a radially oriented joining surface on a stator-supporting structure. If it is necessary to remove the heat release segment, it may be loose Press connection with the heat shield segment in contact standing guide vane are separated by mere axial removal.
  • the heat spreader segment can be easily separated from the other vane by loosening the joint by removing the respective vane in the circumferential direction from the stator supporting structure carrying the vane, whereby the joint connection to the heat spreader is automatically released. Since the heat recovery segment according to the invention is distinguished by design features with regard to the joint construction, the heat recovery segment according to the invention will be described below with reference to a preferred exemplary embodiment.
  • FIG. 1 shows a partial longitudinal sectional view through the stator-side suspension of a stator blade 4 and a heat shield segment 12 formed separately to the guide blade 4 as in the embodiment described above FIG. 2 , to the description of which reference is made to the introduction to the description, also in the FIG. 1a shown guide vane 4 and the axially adjacent thereto heat accumulation segment 12 the flow channel K relative to the stator arranged components 2 to separate gas-tight.
  • the band seals 6 and 14 of the separately executed guide vane and heat shield segment 12 only half the length, whereby the wear due to the vibration occurring unchanged due to material abrasion occur significantly less in appearance. This makes it possible to extend the maintenance and possibly replacement intervals for the band seal significantly.
  • the heat dissipation segment 12 formed in accordance with the invention has two axially opposite joining contours 17, 18, of which the joining contour 18 is merely subjected to a force via a radially oriented joining surface 19 to a Surface region 20 of the stator-side support structure 7 is pressed.
  • a groove-shaped recess is provided within the radially oriented joining surface 19, within which a sealing means 21 is introduced.
  • the second joining region 18 adjoins an axially adjacent guide vane 4 'via a further axial joining face 22, which can be mounted or dismounted by appropriate axial mounting or dismounting by means of exclusive axial approach or removal to the heat spreader segment 12.
  • the joining region 18, axially opposite, the first joining region 17 is provided, which, according to the illustration in FIG. 1 b is shown enlarged. The further comments thus refer to both FIGS. 1a and 1b ,
  • the joining region 17 of the heat spreader segment 12 has a collar section 23, which provides a radially upper and radially lower collar surface 24, 25.
  • the collar portion 23 protrudes axially into a corresponding counter-contoured receiving contour 26 within the axially adjacent guide vane 4.
  • the joining between the collar portion 23 and the receiving contour 26, which is more precisely provided in the foot region of the guide vane 4, takes place precisely, so that the joint at least in Radial direction has no clearance or tolerance. This is necessary in particular for a gas-tight and force-loaded pressing of the axially opposite joining contour 18 against the support structure 7 in the surface region 20.
  • the joining contour 17 has a radially oriented recess 27, which has a cylindrically shaped contour surface 28.
  • the radially oriented recess 27 is formed as a half-mold, wherein the cylindrically shaped contour surface 28 axially facing the collar portion 23 is attached.
  • the joining region 17 is also covered radially on the outside by an overhanging region 29 of the guide blade 4, with which the guide blade 4 is fastened in a stator-side support structure 7.
  • an opening 30 is provided which passes through the overhanging region 29 completely radially and in which a cylindrically shaped mounting pin 31, a spring element 32 and a helically shaped support member 33 are provided.
  • the fastening pin 31 has a cylindrical outer contour 34, which comes into engagement with the contour surface 28 of the first joining contour 17 by radially lowering the fastening pin 31.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Thermotherapy And Cooling Therapy Devices (AREA)
  • Central Heating Systems (AREA)
  • Materials For Medical Uses (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
EP06725188A 2005-03-24 2006-03-21 Wärmestausegment Not-in-force EP1861583B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SI200630608T SI1861583T1 (sl) 2005-03-24 2006-03-21 Segment toplotne zapore

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005013796A DE102005013796A1 (de) 2005-03-24 2005-03-24 Wärmestausegment
PCT/EP2006/060900 WO2006100233A1 (de) 2005-03-24 2006-03-21 Wärmestausegment

Publications (2)

Publication Number Publication Date
EP1861583A1 EP1861583A1 (de) 2007-12-05
EP1861583B1 true EP1861583B1 (de) 2009-12-30

Family

ID=36581787

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06725188A Not-in-force EP1861583B1 (de) 2005-03-24 2006-03-21 Wärmestausegment

Country Status (10)

Country Link
US (1) US7665958B2 (sl)
EP (1) EP1861583B1 (sl)
KR (1) KR101259205B1 (sl)
AT (1) ATE453779T1 (sl)
AU (1) AU2006226419B2 (sl)
BR (1) BRPI0609310A8 (sl)
DE (2) DE102005013796A1 (sl)
MX (1) MX2007011766A (sl)
SI (1) SI1861583T1 (sl)
WO (1) WO2006100233A1 (sl)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7377742B2 (en) * 2005-10-14 2008-05-27 General Electric Company Turbine shroud assembly and method for assembling a gas turbine engine
EP2886802B1 (fr) * 2013-12-20 2019-04-10 Safran Aero Boosters SA Joint de virole interne de dernier étage de compresseur de turbomachine axiale
FR3045716B1 (fr) * 2015-12-18 2018-01-26 Safran Aircraft Engines Ensemble d'anneau de turbine avec maintien elastique a froid
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
FR3070429B1 (fr) * 2017-08-30 2022-04-22 Safran Aircraft Engines Secteur d'un distributeur annulaire d'une turbine de turbomachine

Family Cites Families (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB721453A (en) * 1951-10-19 1955-01-05 Vickers Electrical Co Ltd Improvements relating to gas turbines
US3362160A (en) * 1966-09-16 1968-01-09 Gen Electric Gas turbine engine inspection apparatus
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal
US3558237A (en) * 1969-06-25 1971-01-26 Gen Motors Corp Variable turbine nozzles
BE756582A (fr) * 1969-10-02 1971-03-01 Gen Electric Ecran circulaire et support d'ecran avec dispositif de reglage de la temperature pour turbomachine
US3825364A (en) * 1972-06-09 1974-07-23 Gen Electric Porous abradable turbine shroud
GB1400131A (en) * 1973-07-03 1975-07-16 Bekaert Sa Nv Packaging coils of wire netting
US3864056A (en) * 1973-07-27 1975-02-04 Westinghouse Electric Corp Cooled turbine blade ring assembly
US3892497A (en) * 1974-05-14 1975-07-01 Westinghouse Electric Corp Axial flow turbine stationary blade and blade ring locking arrangement
FR2416345A1 (fr) * 1978-01-31 1979-08-31 Snecma Dispositif de refroidissement par impact des segments d'etancheite de turbine d'un turboreacteur
FR2574473B1 (fr) * 1984-11-22 1987-03-20 Snecma Anneau de turbine pour une turbomachine a gaz
US5071313A (en) * 1990-01-16 1991-12-10 General Electric Company Rotor blade shroud segment
GB2245316B (en) * 1990-06-21 1993-12-15 Rolls Royce Plc Improvements in shroud assemblies for turbine rotors
US5169287A (en) * 1991-05-20 1992-12-08 General Electric Company Shroud cooling assembly for gas turbine engine
US5165847A (en) * 1991-05-20 1992-11-24 General Electric Company Tapered enlargement metering inlet channel for a shroud cooling assembly of gas turbine engines
US5593277A (en) * 1995-06-06 1997-01-14 General Electric Company Smart turbine shroud
GB2310255B (en) * 1996-02-13 1999-06-16 Rolls Royce Plc A turbomachine
DE19619438B4 (de) * 1996-05-14 2005-04-21 Alstom Wärmestausegment für eine Turbomaschine
EP0844369B1 (en) * 1996-11-23 2002-01-30 ROLLS-ROYCE plc A bladed rotor and surround assembly
FR2766517B1 (fr) * 1997-07-24 1999-09-03 Snecma Dispositif de ventilation d'un anneau de turbomachine
US5993150A (en) * 1998-01-16 1999-11-30 General Electric Company Dual cooled shroud
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FR2780443B1 (fr) * 1998-06-25 2000-08-04 Snecma Anneau de stator de turbine haute pression d'une turbomachine
US6183192B1 (en) * 1999-03-22 2001-02-06 General Electric Company Durable turbine nozzle
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FR2800797B1 (fr) * 1999-11-10 2001-12-07 Snecma Assemblage d'un anneau bordant une turbine a la structure de turbine
FR2803871B1 (fr) * 2000-01-13 2002-06-07 Snecma Moteurs Agencement de reglage de diametre d'un stator de turbine a gaz
US6386127B1 (en) * 2000-02-07 2002-05-14 Case Corporation Disc opener assembly for a seed planter
US6514041B1 (en) * 2001-09-12 2003-02-04 Alstom (Switzerland) Ltd Carrier for guide vane and heat shield segment
US6726448B2 (en) * 2002-05-15 2004-04-27 General Electric Company Ceramic turbine shroud
US6902371B2 (en) * 2002-07-26 2005-06-07 General Electric Company Internal low pressure turbine case cooling
US7367776B2 (en) * 2005-01-26 2008-05-06 General Electric Company Turbine engine stator including shape memory alloy and clearance control method
US7438520B2 (en) * 2005-08-06 2008-10-21 General Electric Company Thermally compliant turbine shroud mounting assembly
FR2899274B1 (fr) * 2006-03-30 2012-08-17 Snecma Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine d'une turbomachine
FR2914350B1 (fr) * 2007-03-30 2011-06-24 Snecma Enveloppe externe etanche pour une roue de turbine de turbomachine

Also Published As

Publication number Publication date
US7665958B2 (en) 2010-02-23
BRPI0609310A8 (pt) 2017-01-24
MX2007011766A (es) 2007-11-22
US20080050225A1 (en) 2008-02-28
AU2006226419B2 (en) 2009-07-23
WO2006100233A1 (de) 2006-09-28
KR101259205B1 (ko) 2013-04-29
DE102005013796A1 (de) 2006-09-28
SI1861583T1 (sl) 2010-05-31
DE502006005785D1 (de) 2010-02-11
BRPI0609310A2 (pt) 2010-03-09
KR20070116152A (ko) 2007-12-06
EP1861583A1 (de) 2007-12-05
AU2006226419A1 (en) 2006-09-28
ATE453779T1 (de) 2010-01-15

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