EP1589192A1 - Aube de turbine avec noyau de refroidissement par impact - Google Patents

Aube de turbine avec noyau de refroidissement par impact Download PDF

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Publication number
EP1589192A1
EP1589192A1 EP04009326A EP04009326A EP1589192A1 EP 1589192 A1 EP1589192 A1 EP 1589192A1 EP 04009326 A EP04009326 A EP 04009326A EP 04009326 A EP04009326 A EP 04009326A EP 1589192 A1 EP1589192 A1 EP 1589192A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine blade
waveform
insert
overlap
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Withdrawn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
EP04009326A
Other languages
German (de)
English (en)
Inventor
Gernot Lang
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 EP04009326A priority Critical patent/EP1589192A1/fr
Priority to ES05731679T priority patent/ES2308476T3/es
Priority to US11/578,920 priority patent/US8137055B2/en
Priority to PCT/EP2005/051487 priority patent/WO2005103452A1/fr
Priority to EP05731679A priority patent/EP1738060B1/fr
Priority to DE502005004644T priority patent/DE502005004644D1/de
Publication of EP1589192A1 publication Critical patent/EP1589192A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated

Definitions

  • the invention relates to a cooled turbine blade, which successively a blade root, a platform area and a hollow airfoil for receiving a sheet-like Impact cooling insert comprises, which at least two in an overlap overlapping, contiguous Has sections. Furthermore, the invention relates to a gas turbine according to claim 6.
  • JP 2001-14 06 02-A discloses a cooled gas turbine blade with sheet-like impingement cooling inserts.
  • An impact-cooling insert arranged in the region of the blade trailing edge of the turbine blade and triangular in cross section is spaced from the inner surface of the outer wall and provided with impingement cooling openings.
  • the cavity enclosed by the impingement cooling insert is supplied with cooling air, which subsequently exits through the impingement cooling openings and impinges on the inner surface of the outer wall, which is flowed around hot outside, in order to cool it.
  • impact cooling inserts from two separate Parts exist successively in the cavity of a turbine blade be inserted.
  • the first part is at the radially inner platform and the second part at the radial outer platform gas-tight fixed to losses in the feed to avoid.
  • the two parts are in one overlapping flat sliding seat abut each other at the Operation of the gas turbine to allow a relative movement.
  • the object of the invention is therefore to specify a turbine blade, which saves cooling medium. It is also a task the invention for this purpose, a correspondingly improved gas turbine specify.
  • the solution of the task aimed at the turbine blade suggests that to seal the overlap area the both sections in the cross section wavy are.
  • the solution is based on the knowledge that by the undulating overlap of the two sections the Enlarged between them formed overlap area and targeted a contact area is created, where the two Sections sealingly abut each other.
  • the waveform has a rising flank between a wave trough and a wave crest and a falling flank between a wave crest and a wave trough.
  • the wave form of the two overlapping sections formed by the wave troughs and the wave crests are approximately parallel, so that contact surfaces are formed between adjacent rising flanks and / or between adjacent falling flanks, which prevent the leakage flow. This leads to a saving of cooling medium.
  • the use of such a turbine blade in a gas turbine during operation leads to an increase in efficiency.
  • there is a mechanical mobility of the two closely juxtaposed sections which are required to compensate for the thermal expansion of the material during cold start or during transient operation of the gas turbine.
  • the frequency deviates and / or the amplitude of the waveform of the first element from the second frequency or amplitude of the waveform of the second element.
  • This will certainly avoid that the waveform of the two sections in the overlap area form a parallel, meandering gap. Consequently, one between two rising or falling edge contact surface generated, the despite the different thermal material expansions or a move against each other because of the contact surface effective sealing force a particularly dense overlap area guaranteed.
  • the overlapping areas are securely sealed.
  • the embodiment in which the Frequency (and / or amplitude) of the waveform of the first element in the order of max. ⁇ 6% of the frequency (and / or amplitude) of the waveform of the second element different.
  • the frequencies and the amplitudes are included to choose so that the thermal expansion of material the elements do not cause mutual mechanical obstruction and thus ensure a secure sealing effect.
  • the parameters of the waveform are based on the material of the Impact cooling insert tuned.
  • the space required for the overlap area can be especially save space when the overlap area in cross section does not have more than five oscillation periods.
  • the Impact cooling insert formed in several parts.
  • the can Baffle insert forming parts from an open top Shovel tip starting in the hollow airfoil successively be inserted. After that lie the sections of the individual parts in each case in an overlapping area together, which is also referred to as a sliding seat.
  • a special easy shifting is ensured because the direction of displacement of the impact cooling insert perpendicular to the propagation of Wave runs.
  • FIG. 1 shows a perspective view of an inventive Turbine blade 1 with a platform area 2 and with one extending along a blade axis 2a Airfoil 2b.
  • the airfoil 2b has at least one Cavity 3, in which a baffle cooling insert 5 is provided. Furthermore, the airfoil 2b has one of a hot gas 7 the gas turbine flowable blade leading edge 9, from the a suction side wall 11 and a pressure side wall 13 extends to a blade trailing edge 15.
  • the turbine blade 1 may include both a vane and a blade be.
  • the inner surfaces 19 of the side walls 11, 13 enclose the cavity 3.
  • To form a gap 22 is the Surface 19 of the baffle insert 5 by means of several ribs or circular spacers 21 spaced.
  • the im Inside of the baffle inserts 5 enclosed coolant channel 23 is traversed by a cooling medium.
  • the bumpers 5 also have impingement cooling openings 25 through which flowing in the coolant channel 23 flowing cooling medium and thereafter perpendicular to the surfaces 19 of the side walls 11, 13 can bounce to cool this.
  • the baffle insert 27 is in the direction of the blade axis 2a seen from two separate parts 29, 31 formed, which each with a portion 30, 32 in an overlap area 33, 35 overlap each other.
  • the overlap area 33, 35 lies outside the middle Blade height.
  • the hot airfoil 2b expands more in the direction of the blade axis 2a than the cool one Impact cooling insert 27, is one along the blade axis 2a directed mobility of the two fixed parts 29, 31 in Overlap area 33, 35 necessary.
  • FIGS. 2 and 3 each show an alternative embodiment of the overlapping area 33, 35 in a detailed view.
  • the baffle insert 5 is under from the inner surface 19 Forming the gap 22 spaced.
  • the suction side wall 11 of the hot gas. 7 flows around.
  • the cooling medium 36 For cooling the suction side wall 11 flows out of the Coolant channel 23, the cooling medium 36 through the impingement cooling holes 25 and bounces cooling on the inner surface 19th
  • the two sections 30, 32 with an identical Waveform formed i. the waveforms of the two Sections 30, 32 of the parts 29, 31 have an identical Frequency f and an identical amplitude A on.
  • the meandering Gap 37 between the two sections 30, 32nd If a leakage reduced by turbulences can flow, compared with a leakage in a flat overlap area According to the state of the art.
  • shifted position of the sections 30, 32 can the rising flanks 39 or the falling flanks 40 of the adjacent sections 30, 32 to form a Contact surface but also close to each other.
  • a shift the two parts 29, 31 perpendicular to it is due the predetermined geometry of the airfoil 2b and the Impact cooling insert 5 not possible.
  • Fig. 3 shows the overlapping region 33 with the two opposite Sections 30, 32, which are a different Have frequency f and a different amplitude A.
  • the thermal Strains of the impingement cooling insert 5 are the rising Flanks 39 and falling edges 40 of the waveform at least a period of the two sections 30, 32 sealingly to each other so that at any time one parallel to the blade axis 2a extending contact surface 43 is present.
  • the contact surface shifts 43 within the overlap region 33, 35 of a Period to an adjacent period. Therefore, it is expedient a minimum of two periods in the overlap area 33, 35 provided to a particularly secure seal the coolant channel 23 with respect to the gap 22 to achieve.
  • baffle cooling openings Be provided 25, in particular in the field of Wave troughs or wave crests of sections 30, 32.
  • the waveform is not necessarily sinusoidal. Same one Effect is also with a waveform consisting of consecutive Semicircles or semi-ellipses achievable. About that In addition, a triangular shape, a sawtooth shape or a Rectangular shape also conceivable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04009326A 2004-04-20 2004-04-20 Aube de turbine avec noyau de refroidissement par impact Withdrawn EP1589192A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP04009326A EP1589192A1 (fr) 2004-04-20 2004-04-20 Aube de turbine avec noyau de refroidissement par impact
ES05731679T ES2308476T3 (es) 2004-04-20 2005-04-01 Pala de turbina con un inserto de refrigeracion por rebote.
US11/578,920 US8137055B2 (en) 2004-04-20 2005-04-01 Turbine blade with an impingement cooling insert
PCT/EP2005/051487 WO2005103452A1 (fr) 2004-04-20 2005-04-01 Aube de turbine comprenant un element d'insertion de refroidissement inertiel
EP05731679A EP1738060B1 (fr) 2004-04-20 2005-04-01 Aube de turbine comprenant un element d'insertion de refroidissement inertiel
DE502005004644T DE502005004644D1 (de) 2004-04-20 2005-04-01 Turbinenschaufel mit einem prallkühleinsatz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04009326A EP1589192A1 (fr) 2004-04-20 2004-04-20 Aube de turbine avec noyau de refroidissement par impact

Publications (1)

Publication Number Publication Date
EP1589192A1 true EP1589192A1 (fr) 2005-10-26

Family

ID=34924665

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04009326A Withdrawn EP1589192A1 (fr) 2004-04-20 2004-04-20 Aube de turbine avec noyau de refroidissement par impact
EP05731679A Expired - Fee Related EP1738060B1 (fr) 2004-04-20 2005-04-01 Aube de turbine comprenant un element d'insertion de refroidissement inertiel

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05731679A Expired - Fee Related EP1738060B1 (fr) 2004-04-20 2005-04-01 Aube de turbine comprenant un element d'insertion de refroidissement inertiel

Country Status (5)

Country Link
US (1) US8137055B2 (fr)
EP (2) EP1589192A1 (fr)
DE (1) DE502005004644D1 (fr)
ES (1) ES2308476T3 (fr)
WO (1) WO2005103452A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008081486A1 (fr) * 2007-01-04 2008-07-10 Ansaldo Energia S.P.A. Élément d'espacement pour insert d'aube de turbine à gaz
CN100420542C (zh) * 2006-06-22 2008-09-24 上海电气电站设备有限公司 镶入式焊接隔板的装配工艺
EP3293356A1 (fr) * 2016-09-06 2018-03-14 Rolls-Royce Deutschland Ltd & Co KG Aube rotorique pour turbomachine comprenant une tôle de refroidissement par impact mobile et procédé d'assemblage correspondant

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8206109B2 (en) * 2009-03-30 2012-06-26 General Electric Company Turbine blade assemblies with thermal insulation
US8777569B1 (en) * 2011-03-16 2014-07-15 Florida Turbine Technologies, Inc. Turbine vane with impingement cooling insert
US9719372B2 (en) 2012-05-01 2017-08-01 General Electric Company Gas turbomachine including a counter-flow cooling system and method
US10100659B2 (en) 2014-12-16 2018-10-16 Rolls-Royce North American Technologies Inc. Hanger system for a turbine engine component
US9879554B2 (en) 2015-01-09 2018-01-30 Solar Turbines Incorporated Crimped insert for improved turbine vane internal cooling
DE102016207162A1 (de) 2016-04-27 2017-11-02 Siemens Aktiengesellschaft Kühlfluidverteiler für eine Schaufel aus mehreren Teileinsätzen
PL232314B1 (pl) 2016-05-06 2019-06-28 Gen Electric Maszyna przepływowa zawierająca system regulacji luzu
US10309246B2 (en) 2016-06-07 2019-06-04 General Electric Company Passive clearance control system for gas turbomachine
US10392944B2 (en) 2016-07-12 2019-08-27 General Electric Company Turbomachine component having impingement heat transfer feature, related turbomachine and storage medium
US10605093B2 (en) 2016-07-12 2020-03-31 General Electric Company Heat transfer device and related turbine airfoil
US10767487B2 (en) * 2016-11-17 2020-09-08 Raytheon Technologies Corporation Airfoil with panel having flow guide
JP6655589B2 (ja) * 2017-11-29 2020-02-26 三菱重工業株式会社 計測システム、加工システム、計測方法及びプログラム
CN111764967B (zh) * 2020-07-06 2022-10-14 中国航发湖南动力机械研究所 涡轮叶片尾缘冷却结构

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2888241A (en) * 1954-06-09 1959-05-26 Stalker Corp Fabricated cooled turbine blades
GB833770A (en) * 1956-11-01 1960-04-27 Havilland Engine Co Ltd Hollow turbine or compressor blades
GB1261765A (en) * 1966-12-01 1972-01-26 Gen Electric Improvements in axial flow turbomachinery vanes
US3707750A (en) * 1968-11-14 1973-01-02 Mtu Muenchen Gmbh Method for manufacturing a turbine blade
US4056332A (en) * 1975-05-16 1977-11-01 Bbc Brown Boveri & Company Limited Cooled turbine blade
US4403917A (en) * 1980-01-10 1983-09-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbine distributor vane
US6439847B2 (en) * 2000-01-31 2002-08-27 Alstom (Switzerland) Ltd. Air-cooled turbine blade
GB2386926A (en) * 2002-03-27 2003-10-01 Alstom Two part impingement tube for a turbine blade or vane

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2873944A (en) * 1952-09-10 1959-02-17 Gen Motors Corp Turbine blade cooling
GB753224A (en) * 1953-04-13 1956-07-18 Rolls Royce Improvements in or relating to blading for turbines or compressors
US4257734A (en) * 1978-03-22 1981-03-24 Rolls-Royce Limited Guide vanes for gas turbine engines
JP2001140602A (ja) 1999-11-12 2001-05-22 Mitsubishi Heavy Ind Ltd ガスタービン静翼
US7104756B2 (en) * 2004-08-11 2006-09-12 United Technologies Corporation Temperature tolerant vane assembly

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2888241A (en) * 1954-06-09 1959-05-26 Stalker Corp Fabricated cooled turbine blades
GB833770A (en) * 1956-11-01 1960-04-27 Havilland Engine Co Ltd Hollow turbine or compressor blades
GB1261765A (en) * 1966-12-01 1972-01-26 Gen Electric Improvements in axial flow turbomachinery vanes
US3707750A (en) * 1968-11-14 1973-01-02 Mtu Muenchen Gmbh Method for manufacturing a turbine blade
US4056332A (en) * 1975-05-16 1977-11-01 Bbc Brown Boveri & Company Limited Cooled turbine blade
US4403917A (en) * 1980-01-10 1983-09-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbine distributor vane
US6439847B2 (en) * 2000-01-31 2002-08-27 Alstom (Switzerland) Ltd. Air-cooled turbine blade
GB2386926A (en) * 2002-03-27 2003-10-01 Alstom Two part impingement tube for a turbine blade or vane

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN100420542C (zh) * 2006-06-22 2008-09-24 上海电气电站设备有限公司 镶入式焊接隔板的装配工艺
WO2008081486A1 (fr) * 2007-01-04 2008-07-10 Ansaldo Energia S.P.A. Élément d'espacement pour insert d'aube de turbine à gaz
JP2010515850A (ja) * 2007-01-04 2010-05-13 アンサルド エネルジア エス．ピー．エー． ガスタービンブレード・インサート用スペーサ
EP3293356A1 (fr) * 2016-09-06 2018-03-14 Rolls-Royce Deutschland Ltd & Co KG Aube rotorique pour turbomachine comprenant une tôle de refroidissement par impact mobile et procédé d'assemblage correspondant
US10781699B2 (en) 2016-09-06 2020-09-22 Rolls-Royce Deutschland Ltd & Co Kg Rotor blade for a turbomachine and method for the assembly of a rotor blade for a turbomachine

Also Published As

Publication number Publication date
EP1738060A1 (fr) 2007-01-03
WO2005103452A1 (fr) 2005-11-03
US20080260537A1 (en) 2008-10-23
EP1738060B1 (fr) 2008-07-09
DE502005004644D1 (de) 2008-08-21
ES2308476T3 (es) 2008-12-01
US8137055B2 (en) 2012-03-20

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