EP1163426A1 - Aube de turbomachine - Google Patents

Aube de turbomachine

Info

Publication number
EP1163426A1
EP1163426A1 EP00908907A EP00908907A EP1163426A1 EP 1163426 A1 EP1163426 A1 EP 1163426A1 EP 00908907 A EP00908907 A EP 00908907A EP 00908907 A EP00908907 A EP 00908907A EP 1163426 A1 EP1163426 A1 EP 1163426A1
Authority
EP
European Patent Office
Prior art keywords
blade
edge
airfoil
hole
turbomachine
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.)
Granted
Application number
EP00908907A
Other languages
German (de)
English (en)
Other versions
EP1163426B1 (fr
Inventor
Bent Phillipsen
Boris Mamaev
Evgeny Ryabov
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems 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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Publication of EP1163426A1 publication Critical patent/EP1163426A1/fr
Application granted granted Critical
Publication of EP1163426B1 publication Critical patent/EP1163426B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the invention relates to a turbomachine blade provided with a damper wire hole according to the preamble of claim 1.
  • damper wires or other damping elements are often used, which are received in corresponding holes in the blades.
  • increased stresses occur especially at the edges of the holes.
  • the contact area that the damper wire has with the damper wire hole during operation of the turbomachine is defined by the distance between the boundary planes of the reinforcements. This distance or the length of the contact area is chosen so that both sufficient static and dynamic strength is guaranteed.
  • the invention tries to avoid all these disadvantages. It is the object of the invention to improve the efficiency of a turbomachine blade which has a reinforced hole for receiving a damping element
  • the two acute angles .alpha. And .beta. are preferably formed in a range from 5 ° to 30 °. It has been shown that with such a configuration, particularly minor disturbances in the flow occur in the area of the damping elements
  • FIG. 3 shows a section through the rotor blade, along the line III-III in FIG. 1 Only the elements essential for understanding the invention are shown. For example, the other components of the exhaust gas turbine, including its turbine wheel, are not shown
  • the turbine machine blade shown in FIG. 1, designed as a rotor blade 1, consists of a blade root 2, a platform 3 and an airfoil 4.
  • the platforms of adjacent turbine blades of the turbine wheel lie directly against one another and thus form the inner boundary of the flow channel, which is directed outwards from one Blade cover, also not shown, is completed.
  • the blade 4 has an entry edge 5, a discharge edge 6, a suction side 7 and a pressure side 8 and has a blade tip 9
  • the airfoil 4 there is a through hole 10 from the suction side 7 to the pressure side 8 for receiving a steam wire, not shown, which reduces the blade vibration occurring during operation.
  • the airfoil is also formed with an edge region 11 reinforced towards the hole 10, the edge region 11 both on the suction side 7 and on the pressure side 11 has an end surface 12, 13 which is raised in relation to the airfoil 4.
  • the end surfaces 12, 13 are at an acute angle ex of approximately 10 ° open to the leading edge 5 of the airfoil 4 and with one to the airfoil tip 9 open, acute angle ⁇ of approximately 20 ° (FIG. 2, FIG. 3)
  • both end faces 12, 13 of the reinforced edge region 11 converge in the direction of the discharge edge 6 of the airfoil 4 and in the direction of the blade root 2 in such a way that the reinforcement of the outlet-side and the blade foot-side part of the edge region 11 is significantly less than the reinforcement the part of the edge region 11 on the entrance side and the blade tip side
  • This formation of the airfoil 4 in the region of the hole 10 results in improved flow control during operation of the turbocharger or the exhaust gas turbine.
  • the working medium flowing along the airfoil 4 in a main flow direction 14 experiences, as a result of the end faces 12, 13 arranged at an acute angle to one another as described above, a significantly lower disturbance than is the case with the solutions of the prior art. Due to the improved flow guidance in the area of the turbine wheel, a higher efficiency of the turbocharger and thus ultimately also of the internal combustion engine connected to it can be achieved.
  • angles ⁇ and ⁇ between the end faces 12, 13 of the reinforced edge region 11 are each advantageously in a range from 5 ° to 30 °.
  • end surfaces 12, 13 can also have only one of the two acute angles ⁇ , ⁇ (not shown), which simplifies production but represents a certain loss in efficiency.
  • such a reinforcement of the edge region of the hole receiving the damper wire can be used for all types of damping elements, such as, for example, also in the case of binding wires, bolts, etc. and also in the case of so-called zigzag bonds.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

L'invention vise à améliorer le rendement d'une aube de turbomachine présentant un orifice renforcé pour le logement d'un élément d'amortissement. A cet effet, les surfaces d'extrémité saillantes (12, 13) de la zone marginale (11), de la pale (4), renforcée vers l'orifice (10) forment l'une par rapport à l'autre un angle aigu α ouvert en direction de l'arête d'entrée (5) de la pale (4) et/ou un angle aigu β ouvert en direction de l'extrémité (9) de l'aube.
EP00908907A 1999-03-24 2000-03-23 Aube de turbomachine Expired - Lifetime EP1163426B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19913265 1999-03-24
DE19913265A DE19913265A1 (de) 1999-03-24 1999-03-24 Turbomaschinenschaufel
PCT/CH2000/000171 WO2000057030A1 (fr) 1999-03-24 2000-03-23 Aube de turbomachine

Publications (2)

Publication Number Publication Date
EP1163426A1 true EP1163426A1 (fr) 2001-12-19
EP1163426B1 EP1163426B1 (fr) 2003-06-18

Family

ID=7902195

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00908907A Expired - Lifetime EP1163426B1 (fr) 1999-03-24 2000-03-23 Aube de turbomachine

Country Status (8)

Country Link
US (1) US6520741B1 (fr)
EP (1) EP1163426B1 (fr)
JP (1) JP4531268B2 (fr)
KR (1) KR100718859B1 (fr)
CN (1) CN1171005C (fr)
DE (2) DE19913265A1 (fr)
TW (1) TW440654B (fr)
WO (1) WO2000057030A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2928174B1 (fr) * 2008-02-28 2011-05-06 Snecma Aube avec plateforme non axisymetrique : creux et bosse sur extrados.
KR101324249B1 (ko) * 2011-12-06 2013-11-01 삼성테크윈 주식회사 스퀼러 팁이 형성된 블레이드를 구비한 터빈 임펠러
US20140215998A1 (en) * 2012-10-26 2014-08-07 Honeywell International Inc. Gas turbine engines with improved compressor blades
US10316670B2 (en) * 2013-12-05 2019-06-11 United Technologies Corporation Hollow blade having internal damper
DE102014223231B4 (de) 2014-11-13 2017-09-07 MTU Aero Engines AG Turbomaschinenschaufelanordnung
GB201511416D0 (en) * 2015-06-30 2015-08-12 Napier Turbochargers Ltd Turbomachinery rotor blade
JP7264881B2 (ja) * 2017-09-20 2023-04-25 スルザー ターボ サービシーズ フェンロー ベスローテン フェンノートシャップ 翼ユニットの組立体
CN107514292A (zh) * 2017-09-30 2017-12-26 南京赛达机械制造有限公司 一种抗扭断汽轮机叶片
CN114396315A (zh) * 2021-12-27 2022-04-26 哈尔滨工程大学 一种带有混合式冷却-密封结构的锯齿冠涡轮叶片

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE393333C (de) * 1924-04-01 Karl Imfeld Dipl Ing Schaufelung fuer Turbinen
FR1252766A (fr) * 1959-12-18 1961-02-03 Alsthom Cgee Entretoises pour aubes de turbines
JPS5035602B1 (fr) * 1970-09-14 1975-11-18
JPS50158705A (fr) * 1974-06-17 1975-12-22
JPS5395406A (en) * 1977-02-02 1978-08-21 Hitachi Ltd Connection structure for vane
FR2381905A1 (fr) * 1977-02-24 1978-09-22 Snecma Perfectionnement aux ailettes mobiles de turbine
CH622313A5 (fr) * 1977-09-14 1981-03-31 Bbc Brown Boveri & Cie
JPS6045285B2 (ja) * 1978-02-01 1985-10-08 株式会社日立製作所 動翼連結装置
JPS5832904A (ja) * 1981-08-20 1983-02-26 Toshiba Corp 蒸気タ−ビン翼
JPS5919902U (ja) * 1982-07-29 1984-02-07 株式会社東芝 蒸気タ−ビン羽根
JPS6278404A (ja) * 1985-09-30 1987-04-10 Toshiba Corp 蒸気タ−ビン翼の補強構造
DE4229769A1 (de) * 1992-09-05 1994-03-10 Asea Brown Boveri Dämpfungselement für Turbinenschaufeln
US5267834A (en) 1992-12-30 1993-12-07 General Electric Company Bucket for the last stage of a steam turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO0057030A1 *

Also Published As

Publication number Publication date
JP4531268B2 (ja) 2010-08-25
KR100718859B1 (ko) 2007-05-16
EP1163426B1 (fr) 2003-06-18
WO2000057030A1 (fr) 2000-09-28
CN1171005C (zh) 2004-10-13
DE50002590D1 (de) 2003-07-24
KR20020004969A (ko) 2002-01-16
DE19913265A1 (de) 2000-09-28
TW440654B (en) 2001-06-16
CN1359445A (zh) 2002-07-17
JP2002540335A (ja) 2002-11-26
US6520741B1 (en) 2003-02-18

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