EP1413714B1 - Leitschaufel für eine Turbine - Google Patents

Leitschaufel für eine Turbine Download PDF

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Publication number
EP1413714B1
EP1413714B1 EP20030007140 EP03007140A EP1413714B1 EP 1413714 B1 EP1413714 B1 EP 1413714B1 EP 20030007140 EP20030007140 EP 20030007140 EP 03007140 A EP03007140 A EP 03007140A EP 1413714 B1 EP1413714 B1 EP 1413714B1
Authority
EP
European Patent Office
Prior art keywords
guide vane
insert
platform
recess
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 - Fee Related
Application number
EP20030007140
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1413714A3 (de
EP1413714A2 (de
Inventor
Jürgen Dellmann
Martin-Ferdinand Urban
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 US10/670,805 priority Critical patent/US6951444B2/en
Priority to JP2003360500A priority patent/JP4447282B2/ja
Publication of EP1413714A2 publication Critical patent/EP1413714A2/de
Publication of EP1413714A3 publication Critical patent/EP1413714A3/de
Application granted granted Critical
Publication of EP1413714B1 publication Critical patent/EP1413714B1/de
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Definitions

  • the present invention relates to a guide vane for a turbine according to the preamble of claim 1 and to a turbine according to the preamble of claim 9.
  • Cooled vanes for turbines are well known.
  • the vanes have a hollow profile body, at the end of each extending to a transverse platform.
  • An insert serving as an impingement cooling plate is arranged in the cavity of the profile body at a distance from the inside of the outer wall and has a plurality of impingement cooling openings.
  • the cooling medium flows through the impact cooling holes, bounces against the inside of the outer wall and cools them.
  • a vane is for example from the EP 911 486 A2 known.
  • compressor air As a cooling medium usually compressor air is used. Although the compressor air is already cleaned before entering the compressor by means of an air filter, it still has fine particles in the order of ⁇ 10 microns. These fine particles consisting of dust, particles and sticky compounds such as e.g. Sulfur compounds can often settle inside the baffle plate. Furthermore, agglomerates and corrosion products from these particles can deposit on the impingement cooling openings of the insert, thereby reducing the cross section of the impingement cooling opening. This results in flow losses, so that sets a significantly reduced cooling effect. This can lead to thermal stresses in the outer wall, which can lead to cracking and, in the case of coated guide vanes, to the spalling of the coating.
  • Object of the present invention is therefore to provide a guide vane, are avoided in the mechanical damage during turbine operation.
  • the solution is based on the knowledge that the particles located in the cooling medium are deposited on the inner surface of the insert, preferably where the regions with a strongly decreasing flow velocity and the locations with smaller flow velocities of the cooling medium are.
  • the corresponding areas of the guide vane outer wall are characterized significantly lower cooled zones, which then have the mechanical damage.
  • the zones with the lower flow velocities are displaced from the profiled body region, which is to be intensively cooled, into a region which is cooled less locally, namely that of the platform breakthrough.
  • the exposed to the hot gas profile body is sufficiently cooled over its entire length.
  • the bottom of the insert for producing a predetermined pressure gradient in the bottom region has at least one outlet opening for the cooling medium.
  • the recess is particularly easy to produce in the casting of the guide vane, when the recess is formed as a platform breakthrough.
  • the platform breakthrough is then closed again from the outside by means of a cover plate.
  • the outlet opening has a larger bore diameter than an impingement cooling opening, it can be ensured that the lower pressure gradient lies in the region of the outlet opening.
  • the outlet opening expediently has a bore diameter in the range between 1 mm and 3 mm.
  • the vane is used in a turbine.
  • the Fig. 1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successively follow an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of coaxially arranged burners 7, a turbine. 8 and the exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17, which communicates with an annular hot gas duct 18.
  • There four successive turbine stages 10 form the turbine 8. Each turbine stage 10 is formed of two blade rings. In the direction of flow of a working medium 11, follows in the hot gas duct 18 of a row of vanes 13 formed by a blade 15 series 14.
  • the vanes 12 are attached to the stator 13, whereas the blades 15 of a row 14 are mounted by means of a turbine disk 19 on the rotor 3. Coupled to the rotor 3 is a generator or work machine (not shown).
  • air 16 is sucked and compressed by the compressor 4 through the intake housing.
  • the compressed air provided at the turbine-side end of the compressor 5 is led to the burners 7 where it is mixed with a fuel.
  • the mixture is then burned to form the working medium 11 in the combustion chamber 17.
  • the working medium 11 flows along the hot gas channel 18 past the guide vanes 12 and the blades 15.
  • the working fluid 11 relaxes impulsively, so that the blades 15 drive the rotor 3 and this the driven machine coupled to it.
  • the exposed to the hot working fluid 11 components are subject during the operation of the gas turbine 1 enormous thermal loads.
  • the guide vanes 12 and rotor blades 15 of the first turbine stage 10, viewed in the flow direction of the working medium 11, are subjected to the greatest thermal stress in addition to the heat shield bricks which line the annular combustion chamber 6. In order to withstand the prevailing temperatures, they are cooled by means of a cooling medium K.
  • Fig.1 shows a section through the partially illustrated vane 12 of the turbine 8.
  • the guide vane 12 has a profile body 22, at whose head end a platform 23 is arranged. The foot-side end of the vane 23 with the molded thereon second platform is not shown. Between the two platforms of the profile body portion 37 is arranged.
  • the profile body 22 extends in the flow direction of the working medium 11 seen from a circular leading edge 25 toward a pointed trailing edge 26.
  • the guide vane 12 has a slot 41 extending from the foot end to Kopf tenuem end, arranged in the round turbulators 27 are.
  • a cavity 21 is provided in the interior of the profile body 22, which is enclosed by the outer wall 40 of the profile body 22.
  • the cavity 21 extends through the head-side platform 23, so that the platform 23 has a recess 24, which is designed as a kidney-shaped platform opening 39.
  • the cavity 21 is closed gas-tight at the platform opening 39 by means of a cover cover 32.
  • the edge of the platform breakthrough 39 and the end cover 32 are welded together.
  • An insert 20 located in the cavity 21 serves as an impingement cooling plate. It is accordingly spaced from the inside 28 of the outer wall 40. Furthermore, the insert 20 has impact cooling openings 29 on its side facing the leading edge 25. These are designed as holes with a diameter of 0.7 mm.
  • the head-side platform 23 facing the end of the insert 20 projects into the platform breakthrough 39 inside. At the front side of the insert 20, this is closed with a bottom 35 in the form of a sheet.
  • the insert 20 is extended by the length V in the recess 24; the bottom 35 of the insert 20 is displaced into the platform opening 39.
  • an outlet opening 31 in the form of a bore. It is, based on the cross section of the impingement cooling opening 29, by a factor of 2 to factor 5 larger and has a diameter in the range of 1 mm to 4 mm. Alternatively, a plurality of outlet openings 31 could be provided, which together have an equivalent cross-section.
  • the working fluid 11 flows from the leading edge 25 around the outer wall 40 of the profile body 22 around to the trailing edge 26.
  • the leading edge 25 is particularly exposed to thermal stresses.
  • the guide vane 12 is supplied by the foot-side end as a cooling medium K cooling air and forwarded into the interior of the insert 20. From here, the cooling air flows at a higher speed through the impingement cooling openings 29 of the insert 20 and bounces against the inner side 28 of the outer wall 40. The outer walls 40 extending between the leading edge 25 and the trailing edge 26 are impingement-cooled in the region of the insert 20. Subsequently, the cooling air flows approximately parallel to the flow direction of the working medium 11 in the direction of the trailing edge 26. By the turbulators 27, the cooling medium K is swirled, which enhances the convective cooling effect of the cooling medium K. Thereafter, the cooling medium K exits through the slot 41.
  • the amount of relatively slowly flowing through the outlet opening 31 cooling air is determined by the downstream immediately behind the bottom 35 prevailing cooling air pressure as back pressure. Therefore, the platform breakthrough 39 is closed for pressure separation of the cooling air flow areas through the end cover 32.
  • the cooling air can flow through the outflow cross sections S1, S2 and S3 and finally escape through the cooling air openings 27 into the hot gas channel 18.
  • the recess 24 is in a relatively protected area, based on the hot working medium 11. Thus, this area is exposed to lower temperatures than the profile body 22, so that due to the lower flow velocity of the cooling air and lower cooling effect continues there is sufficient.
  • the transition region 36 from the leading edge 25 to the platform 23 out prevail substantially higher flow velocities for the cooling air than in the profile body portion 37 of the guide vane 12. Thus, in the transition region 36 also ensures sufficient cooling.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20030007140 2002-10-22 2003-03-28 Leitschaufel für eine Turbine Expired - Fee Related EP1413714B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US10/670,805 US6951444B2 (en) 2002-10-22 2003-09-25 Turbine and a turbine vane for a turbine
JP2003360500A JP4447282B2 (ja) 2002-10-22 2003-10-21 タービンおよびその静翼

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10249211 2002-10-22
DE10249211 2002-10-22

Publications (3)

Publication Number Publication Date
EP1413714A2 EP1413714A2 (de) 2004-04-28
EP1413714A3 EP1413714A3 (de) 2004-12-22
EP1413714B1 true EP1413714B1 (de) 2013-05-29

Family

ID=32049546

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20030007140 Expired - Fee Related EP1413714B1 (de) 2002-10-22 2003-03-28 Leitschaufel für eine Turbine

Country Status (2)

Country Link
EP (1) EP1413714B1 (zh)
CN (1) CN100402801C (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20180094095A (ko) * 2016-02-22 2018-08-22 미츠비시 히타치 파워 시스템즈 가부시키가이샤 인서트 조립품, 날개, 가스 터빈, 및, 날개의 제조 방법

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10260356B2 (en) * 2016-06-02 2019-04-16 General Electric Company Nozzle cooling system for a gas turbine engine
CN114687807A (zh) * 2020-12-28 2022-07-01 中国航发商用航空发动机有限责任公司 涡轮叶片冷却封严机构及航空发动机
US20230184139A1 (en) * 2021-12-15 2023-06-15 Raytheon Technologies Corporation High pressure turbine dirt blocker

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4962640A (en) * 1989-02-06 1990-10-16 Westinghouse Electric Corp. Apparatus and method for cooling a gas turbine vane
JPH05156901A (ja) * 1991-12-02 1993-06-22 Hitachi Ltd ガスタービン冷却静翼
US5511937A (en) * 1994-09-30 1996-04-30 Westinghouse Electric Corporation Gas turbine airfoil with a cooling air regulating seal
JP3495579B2 (ja) * 1997-10-28 2004-02-09 三菱重工業株式会社 ガスタービン静翼
EP1191189A1 (de) * 2000-09-26 2002-03-27 Siemens Aktiengesellschaft Gasturbinenschaufel

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20180094095A (ko) * 2016-02-22 2018-08-22 미츠비시 히타치 파워 시스템즈 가부시키가이샤 인서트 조립품, 날개, 가스 터빈, 및, 날개의 제조 방법

Also Published As

Publication number Publication date
CN100402801C (zh) 2008-07-16
EP1413714A3 (de) 2004-12-22
CN1497130A (zh) 2004-05-19
EP1413714A2 (de) 2004-04-28

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