EP1130218A1 - Turbine mit Dichtelement für die Fussplatten der Leitschaufeln - Google Patents

Turbine mit Dichtelement für die Fussplatten der Leitschaufeln Download PDF

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Publication number
EP1130218A1
EP1130218A1 EP00104345A EP00104345A EP1130218A1 EP 1130218 A1 EP1130218 A1 EP 1130218A1 EP 00104345 A EP00104345 A EP 00104345A EP 00104345 A EP00104345 A EP 00104345A EP 1130218 A1 EP1130218 A1 EP 1130218A1
Authority
EP
European Patent Office
Prior art keywords
turbine
sealing element
footplate
gas space
foot plates
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.)
Withdrawn
Application number
EP00104345A
Other languages
German (de)
English (en)
French (fr)
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
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP00104345A priority Critical patent/EP1130218A1/de
Priority to CNB01805949XA priority patent/CN1278020C/zh
Priority to DE50101990T priority patent/DE50101990D1/de
Priority to US10/220,490 priority patent/US6705832B2/en
Priority to EP01911696A priority patent/EP1276972B1/de
Priority to JP2001563751A priority patent/JP4660051B2/ja
Priority to PCT/EP2001/002095 priority patent/WO2001065074A1/de
Publication of EP1130218A1 publication Critical patent/EP1130218A1/de
Withdrawn legal-status Critical Current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
    • F01D11/005—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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Definitions

  • the invention relates to a turbine, in particular a gas turbine.
  • a Hot gas passed through the turbine creating a shaft with blades arranged thereon is driven.
  • This Wave is usually used to generate energy Generator connected.
  • the blades extend radially outward.
  • fixed guide vanes are arranged. When viewed in the longitudinal direction of the turbine, they grip Guide vanes and the rotor blades intermesh tooth-like.
  • the turbine usually has several turbine stages, whereby in a vane ring is arranged at each stage, i.e. several the guide vanes are in the circumferential direction of the turbine arranged side by side.
  • the individual guide vane rings are arranged in succession in the axial direction.
  • the Flow path of the hot gas through the turbine is as follows referred to as gas space.
  • the guide vanes each include a radial in the Airfoil-extending airfoil, which on a base plate is attached, via which the guide vane on a so-called Guide vane carrier is attached.
  • the single ones Base plates of the guide vanes form an essentially closed one Area and limit the gas space to the outside. Around The smallest possible leakage gaps between the individual foot plates can be reached between the individual footplates usually seals provided.
  • Another sealing variant is the grooves and to reset the sealing plate from the hot gas side on the gas chamber side, and in the massive edge area below the sealing element to make an undercut.
  • a third sealing variant after which in the body of the footplate itself Cooling channels are introduced is technically complex to manufacture. In particular, the problem is raised that to form the cooling channels when casting the footplate The core must be cast in, which via spacers is positioned. The core as well as the spacers will be removed after casting by appropriate measures so that the cavities thus formed are used as cooling channels can be. However, there is over that of the spacers created cavity connecting the cooling channels to the outside, making a closed cooling circuit difficult is to be realized.
  • the invention has for its object in a turbine the seal between adjacent vanes for one suitable for simple cooling.
  • the object is achieved by a turbine, in particular by a gas turbine with a gas space and with a number of vanes, each having a base plate and a radially from the footplate into the gas space have extending airfoil, wherein between the Base plates of adjacent guide vanes each have a sealing element is provided with a receiving area in which the Reach in the footplates.
  • the sealing element is in cross section seen H-shaped with two over a cross leg connected longitudinal legs formed, between the Longitudinal legs two receiving areas separated from the cross leg are formed, in each of which the footplates are adjacent Pass in guide vanes. So the sealing element covers with its two longitudinal legs the neighboring footplates partially so that in addition to the sealing property the Foot plates are held by the sealing element.
  • the sealing element is preferably between in Turbine circumferential direction arranged adjacent guide vanes.
  • the foot plates have one each bent radially outwards from the gas space Margin, with between two margins adjacent sealing vanes the sealing element is arranged. This increases the effective sealing height of the seal, without the plate thickness of the base plate being increased.
  • the Both bent side edges of the foot plates are here especially on the cross leg of the H-shaped Sealing element.
  • the page margin essentially has one same material thickness as the rest of the footplate.
  • the sealing element has the front of the footplate facing the gas compartment in the area of the sealing element, one set back from the gas space Contact surface on which the sealing element rests.
  • the sealing element closes flush with the Footplate.
  • the sealing element there is between the sealing element and the foot plates for cooling the sealing element Flow path in the form of a leakage gap for air available. So there is no absolute tightness aimed at thermal load in the area of the sealing element and on the Keep the side edges of the footplate low. Usually the outside space around the gas space becomes in a turbine on a held higher pressure than the gas space, so that over the leakage gap Air enters the gas space from the outside and the Escape of hot gas from the gas space is avoided.
  • a closed through which a coolant can flow Cooling system arranged is from the gas space facing rear area of the footplates, so in Outside, a closed through which a coolant can flow Cooling system arranged.
  • the coolant is particular Steam.
  • a coolant is also used Liquid, such as water, or another gas, such as air or Hydrogen, used.
  • Such a closed cooling system enables an effective, targeted and homogeneous Cooling of the base plates and the entire guide vanes.
  • Coolant can flow directly over the base plates, so that between the coolant and the footplate direct heat exchange takes place.
  • an inflow channel for the coolant between an outer Baffle and a baffle formed, the baffle arranged between the outer baffle and the footplate is and has flow openings to the base plate, and a backflow channel between the baffle plate and the footplate is formed for the cooling medium. So that is easier Way realized a closed cooling system which has a high cooling effect. In operation it will Coolant supplied via the inflow channel and in particular nozzle-like flow openings in the Baffle plate directed to the footplate at high speed, so that between the coolant and the footplate intensive heat exchange takes place. Then the warmed up Coolant discharged in the return flow channel.
  • the baffle plate on the footplate is over one Support element supported so that the baffle plate in a defined Distance from the footplate is kept.
  • the baffle is preferred for easy attachment on the bent side edge of the footplate and the baffle especially attached to the baffle.
  • the further sealing element preferably connects the foot plates on their rear sides facing away from the gas space like a clamp together.
  • the main advantage here is that bracket-like design of the further sealing element see which spans the two footplates.
  • the further The sealing element is in particular in several directions designed to be elastic so that it is subject to thermal expansion follows the footplates without leaving a gap. The seal through the further sealing element is therefore of thermal Extensions largely unaffected.
  • a turbine system 1 comprises a turbine system 2, in particular one Gas turbine system of a turbo set for a power plant Power generation, a combustion chamber 4 and a turbine 6, the in the longitudinal or axial direction 8 of the turbine system 2 after the Combustion chamber 4 is arranged.
  • the turbine 6 is in one Partial area shown cut open, so that a look in the gas space 12 of the turbine 6 is made possible. As gas space 12 becomes the flow path of a hot gas HG through the turbine 6 designated.
  • the combustion chamber 4 is connected to a gas supply 14 a fuel gas BG is supplied, which burns in the combustion chamber 4 and forms the mentioned hot gas HG.
  • the hot gas HG flows through the turbine 6 and leaves it as Kaltgas KG via a gas discharge 16.
  • the hot gas HG is in the turbine 6 via guide vanes 18 and rotor blades 20 guided.
  • a shaft 22 is driven on which the Run blades 20 are arranged.
  • the shaft 22 is with a Generator 24 connected to generate electrical energy.
  • the blades 20 extend radially from the shaft 22 outward.
  • the guide vanes 18 have a base plate 21 and an attached blade 23.
  • the guide vanes 20 are each on a so-called Guide vane carrier 26 attached to the outside of the turbine 6 and extend radially into the gas space 12. In the longitudinal direction 8 seen, the guide vanes 18 and the rotor blades engage 20 interdigitated.
  • Several of the blades 20 and the guide vanes 18 are each one Wreath summarized, with each vane ring one Represents turbine stage. 1 is the second turbine stage 28 and the third turbine stage 30 exemplified.
  • the base plates 21 of the individual guide vanes 18 both delimit in the axial direction 8 and in the circumferential direction 32 of the Turbine 6 to each other and limit the gas space 12 to the outside.
  • the adjacent foot plates 21 are sealed from one another, to minimize leakage gaps 34 between them to keep.
  • foot plates 21 arranged side by side 2 have a thickened edge region 36.
  • a common sealing plate 42 is inserted in the end faces 38 of the edge areas 36 of adjacent foot plates 21 opposite grooves 40 in which a common sealing plate 42 is inserted.
  • This Sealing principle according to which the foot plates 21 in a sealing element Taking up the shape of a sealing plate 42 inevitably requires the reinforced edge region 36. As a rule, this has Edge area 36 is higher by a factor of 3 to a factor of 5 Thickness D1 as the thickness D2 of the remaining foot plate 21 on.
  • the conventional sealing principle vice versa, so that now the foot plates 21 in one Reach in sealing element 44.
  • the sealing element 44 is in the Cross section seen H-shaped and has two Longitudinal leg 46 on each other via a cross leg 48 are connected.
  • the sealing element 44 is therefore according to Art a "double T-beam" is formed. Between the two Longitudinal legs 46 are two separate from the transverse leg 48 Receiving areas 50 are formed, into which the foot plates 21 extend.
  • Sealing element 44 is T-shaped, ie with only one Longitudinal leg 46. With such a sealing element 44 the recording rooms formed are open.
  • the front sides 52 of the foot plates oriented towards the gas space 12 21 each in the area of the sealing element 44 a contact surface 54 set back from the gas space 12 one of the longitudinal legs 56 of the sealing element 44 rests.
  • the base plate 21 is in the area of the sealing element 44 stepped.
  • the end regions of the foot plates 21, that connect to the stage are approximately perpendicular from Gas space 12 bent outwards and each form a bent or radially extending side edge 56.
  • the Side edges 56 of the adjacent foot plates 21 nestle directly on the cross leg 48. This is an increase the sealing height H reached without the foot plate 21 in Sealing area is reinforced.
  • a leakage flow path 58 Between the Sealing element 44 and at least one of the foot plates 21 is a formed as a leakage flow path 58, so that outside space 60 facing away from gas space 12, for example Air flows into the gas space 12 via the flow path 58 can and thus the sealing area, ie the sealing element 44 as well as the side edges 56 cools.
  • a closed one in particular Cooling system 62 is provided, which is preferred as the coolant Steam is used and this is shown in detail in FIG. 3 is.
  • This closed cooling system 62 has one Inflow channel 64 and a return flow channel 66.
  • the inflow channel 64 is between an outer baffle 68 and one Baffle plate 70 formed between the baffle 68 and the foot plate 21 is arranged.
  • the baffle 70 has Flow openings 72 formed in the manner of nozzles are, so that the coolant supplied via the inflow channel 64 along the arrows shown in the return flow channel 66 passes.
  • the baffle plate 70 via support elements 76, for example in the form of welding spots or welding webs, supported against the base plate 21 and kept spaced.
  • the baffle 70 is on the side edge 56 of the foot plate 21 directly attached, in particular welded on, and the baffle 68 is attached to the baffle 70.
  • FIG. 3 shown sealing arrangement in particular for two in the circumferential direction 32 adjacent guide vanes 18 are provided.
  • the shown inflow channels 64 and backflow channels 66 extend accordingly in the axial direction 8 of the turbine 6 H-shaped sealing element 44 thus become the base plates 21 a vane ring sealed to each other. From assembly technology This seal is for in the axial direction 8 adjacent base plates 21 successive turbine stages 28.30 less suitable, although in principle possible.
  • a further sealing element 80 is provided, which the base plates 21 connects to one another at the rear sides 74 like a clamp.
  • the further sealing element 80 is in grooves 82 introduced and attached, which is essentially radial stretch into the foot plates 21 from the rear 74.
  • the further sealing element 80 is, as shown in FIG. 4, for example U-shaped with two connected via an arc 84 Leg 86 designed.
  • the other is Sealing element 80 with a corrugated structure according to Art a bellows.
  • the elongated U-shaped design or the design with the corrugated Structure causes the further sealing element 80 to be elastic is and an all-round mobility of the foot plates 21 due thermal expansion.
  • 4 are further interlocking elements 88 shown on the rear sides 74 are arranged, and with which the guide vanes 18 be hooked into the guide vane carrier 26 (see FIG. 1).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00104345A 2000-03-02 2000-03-02 Turbine mit Dichtelement für die Fussplatten der Leitschaufeln Withdrawn EP1130218A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP00104345A EP1130218A1 (de) 2000-03-02 2000-03-02 Turbine mit Dichtelement für die Fussplatten der Leitschaufeln
CNB01805949XA CN1278020C (zh) 2000-03-02 2001-02-23 涡轮机
DE50101990T DE50101990D1 (en) 2000-03-02 2001-02-23 Turbine
US10/220,490 US6705832B2 (en) 2000-03-02 2001-02-23 Turbine
EP01911696A EP1276972B1 (de) 2000-03-02 2001-02-23 Turbine
JP2001563751A JP4660051B2 (ja) 2000-03-02 2001-02-23 タービン
PCT/EP2001/002095 WO2001065074A1 (de) 2000-03-02 2001-02-23 Turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00104345A EP1130218A1 (de) 2000-03-02 2000-03-02 Turbine mit Dichtelement für die Fussplatten der Leitschaufeln

Publications (1)

Publication Number Publication Date
EP1130218A1 true EP1130218A1 (de) 2001-09-05

Family

ID=8168007

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00104345A Withdrawn EP1130218A1 (de) 2000-03-02 2000-03-02 Turbine mit Dichtelement für die Fussplatten der Leitschaufeln
EP01911696A Expired - Lifetime EP1276972B1 (de) 2000-03-02 2001-02-23 Turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP01911696A Expired - Lifetime EP1276972B1 (de) 2000-03-02 2001-02-23 Turbine

Country Status (6)

Country Link
US (1) US6705832B2 (ja)
EP (2) EP1130218A1 (ja)
JP (1) JP4660051B2 (ja)
CN (1) CN1278020C (ja)
DE (1) DE50101990D1 (ja)
WO (1) WO2001065074A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2003035105A (ja) * 2001-07-19 2003-02-07 Mitsubishi Heavy Ind Ltd ガスタービン分割壁

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Publication number Priority date Publication date Assignee Title
US20050034399A1 (en) * 2002-01-15 2005-02-17 Rolls-Royce Plc Double wall combustor tile arrangement
CN100528080C (zh) * 2004-05-07 2009-08-19 贝克顿·迪金森公司 旋转致动的医疗穿刺装置
ES2378375T3 (es) * 2005-02-07 2012-04-11 Siemens Aktiengesellschaft Pantalla térmica
EP1731714A1 (de) * 2005-06-08 2006-12-13 Siemens Aktiengesellschaft Spaltsperrvorrichtung und Verwendung einer solchen
US7670108B2 (en) * 2006-11-21 2010-03-02 Siemens Energy, Inc. Air seal unit adapted to be positioned adjacent blade structure in a gas turbine
US20090110546A1 (en) * 2007-10-29 2009-04-30 United Technologies Corp. Feather Seals and Gas Turbine Engine Systems Involving Such Seals
EP2265801B1 (en) * 2008-03-18 2017-12-13 GKN Aerospace Sweden AB A gas turbine housing component
JP4815536B2 (ja) * 2010-01-12 2011-11-16 川崎重工業株式会社 ガスタービンエンジンのシール構造
US8359865B2 (en) * 2010-02-04 2013-01-29 United Technologies Corporation Combustor liner segment seal member
US8359866B2 (en) * 2010-02-04 2013-01-29 United Technologies Corporation Combustor liner segment seal member
JP5546420B2 (ja) 2010-10-29 2014-07-09 三菱重工業株式会社 タービン
US9534783B2 (en) * 2011-07-21 2017-01-03 United Technologies Corporation Insert adjacent to a heat shield element for a gas turbine engine combustor
FR2978197B1 (fr) * 2011-07-22 2015-12-25 Snecma Distributeur de turbine de turbomachine et turbine comportant un tel distributeur
US20130134678A1 (en) * 2011-11-29 2013-05-30 General Electric Company Shim seal assemblies and assembly methods for stationary components of rotary machines
EP3092372B1 (en) 2014-01-08 2019-06-19 United Technologies Corporation Clamping seal for jet engine mid-turbine frame
EP3099921B1 (en) * 2014-01-28 2019-01-16 United Technologies Corporation Impingement structure for jet engine mid-turbine frame
EP3099903B1 (en) * 2014-01-28 2020-04-22 United Technologies Corporation Seal for jet engine mid-turbine frame
US9869201B2 (en) * 2015-05-29 2018-01-16 General Electric Company Impingement cooled spline seal
CN105704982B (zh) * 2015-12-18 2017-12-22 上海联影医疗科技有限公司 一种用于医学成像装置的冷却系统
US10378772B2 (en) * 2017-01-19 2019-08-13 General Electric Company Combustor heat shield sealing
US10954809B2 (en) * 2017-06-26 2021-03-23 Rolls-Royce High Temperature Composites Inc. Ceramic matrix full hoop blade track
US10697315B2 (en) * 2018-03-27 2020-06-30 Rolls-Royce North American Technologies Inc. Full hoop blade track with keystoning segments
US11319827B2 (en) * 2019-04-01 2022-05-03 Raytheon Technologies Corporation Intersegment seal for blade outer air seal
CN113623020B (zh) * 2021-08-02 2022-07-08 无锡友鹏航空装备科技有限公司 一种密封性高的涡轮导向装置

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EP0357984A1 (en) * 1988-08-31 1990-03-14 Westinghouse Electric Corporation Gas turbine with film cooling of turbine vane shrouds
US5470198A (en) * 1993-03-11 1995-11-28 Rolls-Royce Plc Sealing structures for gas turbine engines
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EP0921273A1 (en) * 1997-06-11 1999-06-09 Mitsubishi Heavy Industries, Ltd. Rotor for gas turbines
EP0943847A2 (en) * 1998-03-18 1999-09-22 ROLLS-ROYCE plc A seal

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Publication number Priority date Publication date Assignee Title
EP0298897A2 (en) * 1987-07-08 1989-01-11 United Technologies Corporation Stiffening ring for a stator assembly of an axial flow rotary machine
EP0357984A1 (en) * 1988-08-31 1990-03-14 Westinghouse Electric Corporation Gas turbine with film cooling of turbine vane shrouds
US5470198A (en) * 1993-03-11 1995-11-28 Rolls-Royce Plc Sealing structures for gas turbine engines
WO1998053228A1 (en) * 1997-05-21 1998-11-26 Allison Advanced Development Company Interstage vane seal apparatus
EP0921273A1 (en) * 1997-06-11 1999-06-09 Mitsubishi Heavy Industries, Ltd. Rotor for gas turbines
EP0943847A2 (en) * 1998-03-18 1999-09-22 ROLLS-ROYCE plc A seal

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2003035105A (ja) * 2001-07-19 2003-02-07 Mitsubishi Heavy Ind Ltd ガスタービン分割壁

Also Published As

Publication number Publication date
US20030021676A1 (en) 2003-01-30
WO2001065074A1 (de) 2001-09-07
EP1276972A1 (de) 2003-01-22
DE50101990D1 (en) 2004-05-19
JP2003525382A (ja) 2003-08-26
CN1408049A (zh) 2003-04-02
US6705832B2 (en) 2004-03-16
JP4660051B2 (ja) 2011-03-30
EP1276972B1 (de) 2004-04-14
CN1278020C (zh) 2006-10-04

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