EP1654440B1 - Gasturbine mit einem dichtungselement im bereich des leitschaufelkranzes oder des laufschaufelkranzes des turbinenteils - Google Patents

Gasturbine mit einem dichtungselement im bereich des leitschaufelkranzes oder des laufschaufelkranzes des turbinenteils Download PDF

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Publication number
EP1654440B1
EP1654440B1 EP04740664A EP04740664A EP1654440B1 EP 1654440 B1 EP1654440 B1 EP 1654440B1 EP 04740664 A EP04740664 A EP 04740664A EP 04740664 A EP04740664 A EP 04740664A EP 1654440 B1 EP1654440 B1 EP 1654440B1
Authority
EP
European Patent Office
Prior art keywords
sealing element
guide
ring
turbine
gas turbine
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.)
Expired - Lifetime
Application number
EP04740664A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1654440A1 (de
Inventor
Peter Tiemann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to PL04740664T priority Critical patent/PL1654440T3/pl
Priority to EP04740664A priority patent/EP1654440B1/de
Publication of EP1654440A1 publication Critical patent/EP1654440A1/de
Application granted granted Critical
Publication of EP1654440B1 publication Critical patent/EP1654440B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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

Definitions

  • the invention relates to an axial gas turbine, arranged in the hot gas duct axially successive vane rings and blade rings. These blade rings are subjected to cooling air from different pressure levels. For sealing between the individual pressure levels, a sealing element is provided.
  • An axial gas turbine comprises a compressor, a combustion chamber and a turbine part.
  • combustion air is highly compressed, which is burned in the combustion chamber with fuel.
  • the resulting hot gas is passed through a hot gas duct in the turbine part.
  • turbine part In the turbine part alternately successive vane rings and blade rings. In each of these blade rings guide vanes are arranged adjacent in the circumferential direction.
  • the temperatures in such a gas turbine can reach values which exceed the melting points of the materials used or intolerably reduce the heat resistance of the materials. For this reason, the components in the hot gas channel are often cooled with a cooling medium. Usually this air is diverted from the compressor as cooling air. The cooling requirement decreases along the flow direction in the hot gas duct. For this reason, a cooling air with a lower pressure level than cooling air for front turbine stages is sufficient for cooling rear turbine stages. In order to keep the cooling air consumption as low as possible, since this reduces the efficiency of the gas turbine, the axially different turbine stages, ie the different blade rings, are acted upon by cooling air from different pressure levels. In the direction of flow further forward blade rings are supplied with compressed air higher pressure than blade rings, which are further downstream in the flow direction.
  • the U.S. Patent 5,833,244 shows a gas turbine seal assembly.
  • the sealing of two adjacent blade rings is achieved here by a labyrinth seal system.
  • Individual sealing elements are arranged in grooves of rotor discs. These sealing segments have transversely to the flow direction and in the axial direction one behind the other arranged tooth-like elevations, which are arranged opposite a vane tip.
  • a circumferential circumferential labyrinth seal system is provided, which is particularly suitable for the seal in large gas turbines.
  • the object of the invention is to provide a sealing system for sealing located between two blade rings of a gas turbine pressure levels, which has a particularly good sealing effect and at the same time is easy to install and inexpensive.
  • this object is achieved by a directed along a turbine axis axial gas turbine comprising a compressor, a combustion chamber and a turbine part, wherein in the turbine part axially successive vane rings and blade rings are arranged in a hot gas duct, wherein in operation a hot gas flows through the hot gas duct and wherein the Leitschaufelkränze and guide rings are cooled with cooling air at different pressure levels, the pressure level decreases in the flow direction of the hot gas between a vane ring and a vane support (79) or between a guide ring and a vane support (79) a sealing element is arranged, which seals the various pressure levels against each other and extends in one piece at least a quarter of a perpendicular to the turbine axis as a center extending circle.
  • the invention pursues the way of extending a sealing element for sealing in the axial direction over a greater circumferential distance.
  • the sealing effect is considerably improved because circumferentially extending sealing boundaries are reduced.
  • the reduction of components facilitates installation.
  • the reduction in components also causes a more cost-effective design.
  • the sealing element extends around half of the circle.
  • the sealing elements are preferably arranged so that in each case a sealing element extends along one of the two housing halves.
  • the sealing element is designed as an annular plate with extending in the radial direction surface having an outer edge and an inner edge.
  • an annular metal sheet is particularly easy to manufacture.
  • the inner edge engages in each corresponding platform grooves, which is provided in the hot gas duct side facing away from a respective platform of vanes of the vane ring or a radially outwardly of the blade ring lying guide ring.
  • the outer edge is disposed in a carrier groove extending in a vane carrier.
  • Vanes have an airfoil that is bordered by a platform. This platform serves to shield the hot gas from the vane carrier. Attached to the platform is a fixture that secures the vane to the vane support. In the axial direction adjacent to a vane ring, a blade ring, the rotor side also leads through platforms on the blades, the hot gas.
  • the surface of the hot gas passage adjacent the vane support is shielded from the hot gas by guide rings facing the rotating blade tips of the blades.
  • the inner edge of the annular sealing plate can be performed.
  • the outer edge is guided in a carrier groove extending in the guide vane carrier.
  • the sealing element with a pressing on its surface screw, the sealing element against the opposite comparativelynuten sidewall and Victoriaernuten sidewall presses, tense.
  • a secure, independent of the operating condition sealing is achieved.
  • Vanes typically have an entanglement with which they are hooked into the vane carrier. Such a hooking then defines an axial fixed point by an axial contact surface between hooking and Leitschaufelani.
  • the sealing element is arranged in the region of the axial fixed points. This position of the sealing element is particularly advantageous in the above-described active approach of the sealing element, since thermal displacements in the region of the axial fixed point are small.
  • the sealing element is preferably arranged away from the region of the axial fixed points. Due to the large temperature differences at standstill and operating state, considerable thermally induced shifts of the blade platforms or guide rings relative to the guide blade carrier result here. By loosely inserting the sealing element in the platform or Leitschaufelaninuten a passive approach is achieved here just by these thermal shifts.
  • the sealing element is pressed during thermal displacement against the groove walls so that no secure seal is achieved.
  • a further projection extending in the circumferential direction is arranged as an axial contact surface for the sealing element.
  • FIG. 1 shows a gas turbine 1.
  • the gas turbine 1 has along a turbine axis 10 directed successively a compressor 3, a combustion chamber 5 and a turbine part 7.
  • the compressor 3 and the turbine part 7 are arranged on a common shaft 9 extending along the turbine axis 10.
  • In the turbine part 7 extends a conically expanding hot gas channel 12.
  • In this hot gas duct 12 protrude guide vanes 11 and blades 13 into it.
  • a plurality of vanes 11 are disposed adjacent to each other in a vane ring 14 in the circumferential direction.
  • a plurality of blades 13 are arranged in a blade ring 16 circumferentially adjacent to each other. Leitschaufelkränze 14 and blade rings 16 alternate in the hot gas duct 12 alternately.
  • ambient air is sucked in by the compressor 3 and compressed to compressor air 15.
  • the compressor air 15 is fed to the combustion chamber 5 and burned there with the addition of fuel to a hot gas 17.
  • the hot gas 17 flows through the hot gas channel 12 and thus past the guide vanes 11 and the rotor blades 13.
  • the shaft 9 is set in rotation, since the blades 13 absorb kinetic energy from the hot gas 17 and transmitted to the shaft 9, with which they are firmly connected.
  • the energy thus obtained from the hot gas 17 may, for. B. are transmitted to a generator for power generation.
  • FIG. 2 shows a cross section through the hot gas channel 12.
  • a portion of the blade ring 16 and a portion of the vane ring 14 are shown.
  • a formed as an annular plate seal member 35 extends between the vane ring 14 and the blade ring 16 in the circumferential direction over half of a circle 41 which is perpendicular to the turbine axis 10.
  • a similar sealing element 35 runs along the second half of the circle 41, so that both sealing elements 35 form a closed circle.
  • the parting line 42 corresponds to a joint not shown in detail for the half-way division of the hot gas duct 12 enclosing the gas turbine housing.
  • the sealing element 35 is flat, with a plan view of the surface F is shown.
  • the surface F is bounded by an outer edge 37 and an inner edge 39 of the sealing element 35.
  • FIG. 3 shows a section of a longitudinal section through the hot gas channel 12. It is a guide blade 11 is shown, which is enclosed in the axial direction on both sides by a respective guide ring 51. A sealing element 35 is appropriate FIG. 2 educated. The exact arrangement is based on FIG. 4 described.
  • the vane 11 is supplied to cooling air 53 from a first pressure level.
  • the guide ring 51 is supplied with cooling air 55 from a second pressure level.
  • the pressure level of the cooling air 53 is higher than that of the cooling air 55, since there is a higher cooling requirement for the guide vane 11 located further forward in the direction of flow of the hot gas 17 than for the guide ring 51 located farther downstream.
  • FIG. 4 shows enlarged a section of FIG. 3 with the sealing element 35.
  • a groove 85 extending in the circumferential direction is introduced on the side facing away from the hot gas.
  • the guide blade 11 on the side facing away from the hot gas channel 12 is opposite a guide vane carrier 79.
  • In Leitschaufelani 79 is in the radial direction of the platform groove 85 opposite a Leitschaufelaninut 83 also extending in the circumferential direction.
  • the sealing element 35 is a corresponding FIG. 2 trained annular metal strip whose inner edge 39 engages in the platform groove 85.
  • the outer edge 37 of the sealing element 35 is located in the Leitschaufelitatinut 83.
  • the axial position of the sealing element 35 is selected in the region of an entanglement 71 of the guide blade 11.
  • This entanglement 71 is used to mount the guide vane 11. Furthermore, with this entanglement 71 by an axial contact surface fixed an axial fixed point 73, as well as a radial fixed point 75 by means of a radial approach surface.
  • thermal expansions of the platform 87 of the guide blade 11 relative to the guide blade carrier 79 are relatively small, so that a good sealing effect is achieved by the active attachment of the sealing element 35, independently of the operating state of the gas turbine.
  • the guide ring 51 is also arranged by a hooking 77 in the guide vane carrier 79. In prior art configurations, i.
  • FIG. 5 shows a further section of a longitudinal section through the hot gas channel 12. It is in turn a guide blade 11 is shown, which is enclosed on both sides of guide rings 51 in the axial direction. Here, however, the sealing element 35 is far away from the axial fixed point 73 arranged. In addition, no device for pressing the sealing element 35 is provided on the groove walls. This will be explained in more detail by FIG. 6 described.
  • FIG. 6 shows a section with the sealing element 35 FIG. 5 ,
  • the sealing element 35 is again arranged with its inner edge 39 in a platform groove 85 and with its outer edge 37 in a Leitschaufelaninut 83.
  • an additional shoulder 91 is formed as an axial contact surface so that it lies approximately in the region of the radial center of the sealing element 35.
  • the platform groove 85 is arranged in the guide ring 51 in the example shown here.
  • the guide ring 51 is movable relative to the vane support 79 to avoid thermal stresses. In operation, temperature differences result in a displacement of the guide ring 51 relative to the guide blade carrier 79. In this way, the sealing element 35 is bent and pressed against the projection 91 in the guide blade carrier 79.
  • This form of passive approach of the sealing element 35 leads to a good sealing effect, at the same time a very low expenditure on equipment is required.
  • the sealing element 35 When mounting the gas turbine 1 or even during a service operation, the sealing element 35 is simply inserted into the Leitschaufelitatinut 83 and the guide vanes 11 or the guide rings 51 mounted, depending on which of the components has the corresponding platform groove 85. Subsequently, either the guide vanes 11 or the guide rings 51 are then mounted in each case, which adjoin the previously installed components.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04740664A 2003-08-11 2004-07-05 Gasturbine mit einem dichtungselement im bereich des leitschaufelkranzes oder des laufschaufelkranzes des turbinenteils Expired - Lifetime EP1654440B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PL04740664T PL1654440T3 (pl) 2003-08-11 2004-07-05 Turbina gazowa z elementem uszczelniającym w obszarze wieńca łopatek kierowniczych lub wieńca łopatek wirujących części turbinowej
EP04740664A EP1654440B1 (de) 2003-08-11 2004-07-05 Gasturbine mit einem dichtungselement im bereich des leitschaufelkranzes oder des laufschaufelkranzes des turbinenteils

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03018240 2003-08-11
PCT/EP2004/007333 WO2005019602A1 (de) 2003-08-11 2004-07-05 Gasturbine mit einem dichtungselement zwischen leitschaufelkranz und laufschaufelkranz des turbinenteils
EP04740664A EP1654440B1 (de) 2003-08-11 2004-07-05 Gasturbine mit einem dichtungselement im bereich des leitschaufelkranzes oder des laufschaufelkranzes des turbinenteils

Publications (2)

Publication Number Publication Date
EP1654440A1 EP1654440A1 (de) 2006-05-10
EP1654440B1 true EP1654440B1 (de) 2009-01-07

Family

ID=34203213

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04740664A Expired - Lifetime EP1654440B1 (de) 2003-08-11 2004-07-05 Gasturbine mit einem dichtungselement im bereich des leitschaufelkranzes oder des laufschaufelkranzes des turbinenteils

Country Status (7)

Country Link
US (1) US7303371B2 (pl)
EP (1) EP1654440B1 (pl)
CN (1) CN100395431C (pl)
DE (1) DE502004008830D1 (pl)
ES (1) ES2316994T3 (pl)
PL (1) PL1654440T3 (pl)
WO (1) WO2005019602A1 (pl)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2923525B1 (fr) * 2007-11-13 2009-12-18 Snecma Etancheite d'un anneau de rotor dans un etage de turbine
US8821114B2 (en) 2010-06-04 2014-09-02 Siemens Energy, Inc. Gas turbine engine sealing structure
WO2014130147A1 (en) 2013-02-23 2014-08-28 Jun Shi Edge seal for gas turbine engine ceramic matrix composite component
EP2971590B1 (en) * 2013-03-14 2017-05-03 United Technologies Corporation Assembly for sealing a gap between components of a turbine engine
US9963989B2 (en) * 2013-06-12 2018-05-08 United Technologies Corporation Gas turbine engine vane-to-transition duct seal
US10240473B2 (en) * 2013-08-30 2019-03-26 United Technologies Corporation Bifurcated sliding seal
US10107123B2 (en) 2013-08-30 2018-10-23 United Technologies Corporation Sliding seal
EP2960439A1 (en) * 2014-06-26 2015-12-30 Siemens Aktiengesellschaft Turbomachine with an outer sealing and use of the turbomachine
US10161257B2 (en) * 2015-10-20 2018-12-25 General Electric Company Turbine slotted arcuate leaf seal
US12012858B1 (en) 2023-04-28 2024-06-18 Rtx Corporation Failsafe blade outer airseal retention
CN117345433B (zh) * 2023-12-06 2024-02-06 成都中科翼能科技有限公司 一种燃气轮机排气机匣的封严装配组件

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1605310A (en) * 1975-05-30 1989-02-01 Rolls Royce Nozzle guide vane structure
US4425078A (en) * 1980-07-18 1984-01-10 United Technologies Corporation Axial flexible radially stiff retaining ring for sealing in a gas turbine engine
US4379560A (en) * 1981-08-13 1983-04-12 Fern Engineering Turbine seal
GB2307520B (en) * 1995-11-14 1999-07-07 Rolls Royce Plc A gas turbine engine
US5609469A (en) * 1995-11-22 1997-03-11 United Technologies Corporation Rotor assembly shroud
US5785499A (en) 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US6164656A (en) * 1999-01-29 2000-12-26 General Electric Company Turbine nozzle interface seal and methods
US6273683B1 (en) 1999-02-05 2001-08-14 Siemens Westinghouse Power Corporation Turbine blade platform seal
US6702549B2 (en) * 2000-03-02 2004-03-09 Siemens Aktiengesellschaft Turbine installation
GB0108398D0 (en) * 2001-04-04 2001-05-23 Siemens Ag Seal element for sealing a gap and combustion turbine having a seal element
US7094025B2 (en) * 2003-11-20 2006-08-22 General Electric Company Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction
US7040857B2 (en) * 2004-04-14 2006-05-09 General Electric Company Flexible seal assembly between gas turbine components and methods of installation

Also Published As

Publication number Publication date
ES2316994T3 (es) 2009-04-16
PL1654440T3 (pl) 2009-06-30
CN1833094A (zh) 2006-09-13
EP1654440A1 (de) 2006-05-10
CN100395431C (zh) 2008-06-18
WO2005019602A1 (de) 2005-03-03
US7303371B2 (en) 2007-12-04
US20060245915A1 (en) 2006-11-02
DE502004008830D1 (de) 2009-02-26

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