EP2184442A1 - Raccord de profil d'aube - Google Patents

Raccord de profil d'aube Download PDF

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Publication number
EP2184442A1
EP2184442A1 EP08168866A EP08168866A EP2184442A1 EP 2184442 A1 EP2184442 A1 EP 2184442A1 EP 08168866 A EP08168866 A EP 08168866A EP 08168866 A EP08168866 A EP 08168866A EP 2184442 A1 EP2184442 A1 EP 2184442A1
Authority
EP
European Patent Office
Prior art keywords
platform
arc
airfoil
fillet
compound fillet
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Withdrawn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
EP08168866A
Other languages
German (de)
English (en)
Inventor
Marco Micheli
Peter Erik Boldt
Luis Federico Puerta
Wolfgang Kappis
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP08168866A priority Critical patent/EP2184442A1/fr
Priority to PCT/EP2009/064487 priority patent/WO2010054950A1/fr
Publication of EP2184442A1 publication Critical patent/EP2184442A1/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Withdrawn legal-status Critical Current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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour

Definitions

  • the invention relates generally to turbine blade designs and more specifically to compound fillets for gas turbine blades.
  • a gas turbine engine typically includes at least one rotor assembly in which a plurality of blades, comprising airfoils radially extending from platforms, are circumferentially fitted and distributed around a rotor disk.
  • centrifugal forces generate circumferential rim stress in the rotating blades, which can concentrate at the join between the platform and airfoil.
  • This stress concentration can be minimised by fillets at the platform / airfoil join, which provide a concave easing of the interior corner at the join.
  • Adequate stress relief can however only be achieved with an adequately sized and shaped fillet. For compound fillets this includes adjoining the fillet tangentially to the airfoil and platform to avoid forming notches which concentrate stress.
  • a fillet extending between an airfoil of a turbine blade and a blade platform edge that requires less space compared to fillets of the prior art while maintaining the mechanical integrity of the airfoil / blade platform join.
  • the fillet can be shortened by not forming a tangential join at the platform when the fillet ends at the platform edge. Taking this concept to its limit the second arc can be totally eliminated without affecting the mechanical integrity of the blade but only if the fillet adjoins the platform surface at the platform's edge. If the fillet non-tangentially adjoins the platform surface at a point other than at the platform edge the end of the fillet forms a notch where the stress is theoretically infinite. By ending the fillet at the platform edge this can be avoided.
  • a fillet based on this concept can be formed when space between airfoils and the platform edge of a turbine blade is limited so by at least in part addressing some of the problems known in the art related to the amount of space on the platform i.e. the compound fillet footprint, required by a compound fillet.
  • a compound fillet for a turbine blade airfoil to platform join wherein the turbine blade comprises:
  • the compound fillet is characterized by comprising a first portion configured to consist of the first arc and the second arc wherein the first end of the second arc adjoins non-tangentially the platform surface at the platform edge.
  • the compound fillet comprises a second portion configured to consist of the first arc wherein the second end of the first arc adjoins the platform surface at the platform edge.
  • the compound fillet is configured to consist of the first portions and the second portions.
  • the compound fillet comprises a third portion configured to consist of the first arc and the second arc wherein the second arc second end adjoins tangentially the platform surface.
  • the compound fillet is configured to consist of the first portions and the third portions.
  • the compound fillet consists of the first portions, the second portions and the third portions.
  • FIG. 1 shows a turbine blade 1 with an exemplary compound fillet 10 for a turbine airfoil to platform join 20.
  • the application of the compound fillet 10 is not limited to turbine blades 1 having features as shown and could be applied to other turbine components such as compressor rotor blades and stator vanes or nozzles.
  • the turbine blade 1 comprises a platform 6 that has a platform surface 7 with a platform edge 8 defining the outer extent of the platform surface 7. Radially R extending from the platform surface 7 is an airfoil 3 that has an airfoil surface 5. In this configuration the join between the airfoil surface 5 and the platform surface 7 defines the airfoil to platform join 20.
  • FIG. 2 shows a top view of the turbine blade 1 of FIG. 1 showing the coverage of a compound fillet 10 on the platform surface 7.
  • FIG. 3 is a sectional view at point III in FIG. 2 , showing where a portion of a compound fillet 10 comprising a second arc 16 that tangentially adjoins the platform surface 7 could be located.
  • the compound fillet 10 could at other locations consist of this fillet arrangement.
  • the fillet arrangement of FIG. 3 consists of a first arc 11 with a first radius 12 and has a first end tangentially adjoining the airfoil surface 5 and a second end. As shown in FIG. 3 the fillet arrangement further consists of a second arc 16 with a second radius 17 and has a first end tangentially adjoining the second end of the first arc 11 and a second end that tangentially adjoins the platform surface 7.
  • the first arc 11 primarily provides stress dissipation for the airfoil to platform join 20 while the second arc 16 only provides a smooth interface between the first arc 11 and the platform surface 7 so as to avoid stress build-up at this interface. For this reason and for the reason that increasing the second radius 17 would not provide additional mechanical integrity, the first radius 12 is made larger than the second radius 17. In this way the footprint of the compound fillet 10 on the platform surface 7 is minimised. To further ensure that stress points are not created by the joining of the second arc 16 to the platform surface 7, the join is made tangential.
  • FIG. 4 is a sectional view at point IV in FIG. 2 showing where a portion of a compound fillet 10 comprising a second arc 16 that non-tangentially adjoins the platform surface 7 at the platform edge 8 could be located.
  • the compound fillet 10 could at other locations consist of this fillet arrangement.
  • the fillet arrangement of FIG. 4 consists of a first arc 11 and a second arc 16.
  • the first arc 11 has a first radius 12 and consists of a first end tangentially adjoining the airfoil surface 5 and a second end
  • the second arc 16 has a second radius 17 and consists of a first end tangentially adjoining the second end of the first arc 11 and a second end non- tangentially adjoining platform surface 7.
  • This non-tangentially adjoining of the second arc 16 reduces the amount of platform surface 7 required to form the compound fillet 10 without compromising mechanical integrity as a notch is not formed between the compound fillet 10 and the platform surface 7, as it adjoins the platform surface 7 at the platform edge 8.
  • FIG. 5 is a sectional view at point V in FIG. 2 showing where an portion of a compound fillet 10 consisting only of a first arc 11 that non-tangentially adjoins the platform surface 7 at the platform edge 8 could be located. In some turbine blade 1 arrangements, the compound fillet 10 could at other locations consist of this fillet arrangement.
  • the fillet arrangement of FIG. 5 consists of a first arc 11 and does not comprise the second arc 16 shown in FIG. 3 and FIG. 4 .
  • the first arc has a first end tangentially adjoining the airfoil surface 5 and a second end that adjoins the platform surface 7 non-tangentially at the platform edge 8.
  • This non- tangential adjoining of the second arc 16 reduces the amount of platform surface 7 required to form the compound fillet 10 without compromising mechanical integrity by enabling the full forming of the first arc 11 made possibility by the adjoining occurring at the platform edge 8 so as not to form a notch.
  • the platform surface 7 covered by this portion of a compound fillet 10 is particularly small, further reducing the likelihood for additional reworking of the blade design to overcome fillet layout requirements and providing greater design freedom to size and shape the platform 6.
  • the compound fillet 10 covers at least part of the airfoil to platform join 20 and consists of the exemplary portions as described and illustrated in FIG. 3 and FIG. 4 .
  • the compound fillet 10 covering at least part of the airfoil to platform join 20 consists of the exemplary portions as described and illustrated in FIG. 3 , FIG. 4 and FIG. 5 .

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08168866A 2008-11-11 2008-11-11 Raccord de profil d'aube Withdrawn EP2184442A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP08168866A EP2184442A1 (fr) 2008-11-11 2008-11-11 Raccord de profil d'aube
PCT/EP2009/064487 WO2010054950A1 (fr) 2008-11-11 2009-11-03 Congé de raccordement à profil aérodynamique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08168866A EP2184442A1 (fr) 2008-11-11 2008-11-11 Raccord de profil d'aube

Publications (1)

Publication Number Publication Date
EP2184442A1 true EP2184442A1 (fr) 2010-05-12

Family

ID=40527607

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08168866A Withdrawn EP2184442A1 (fr) 2008-11-11 2008-11-11 Raccord de profil d'aube

Country Status (2)

Country Link
EP (1) EP2184442A1 (fr)
WO (1) WO2010054950A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014113043A1 (fr) * 2013-01-18 2014-07-24 United Technologies Corporation Flanc de raccordement composite pour aube directrice
US8801367B2 (en) 2011-09-23 2014-08-12 United Technologies Corporation Hollow fan blade channel configuration to reduce stress
US8807924B2 (en) 2011-09-23 2014-08-19 United Technologies Corporation Fan blade channel termination
EP2811116A1 (fr) 2013-06-05 2014-12-10 Alstom Technology Ltd Aube pour turbine à gaz, aube de rotor et stator
US9221120B2 (en) 2012-01-04 2015-12-29 United Technologies Corporation Aluminum fan blade construction with welded cover
US10215027B2 (en) 2012-01-04 2019-02-26 United Technologies Corporation Aluminum fan blade construction with welded cover
JP2020090953A (ja) * 2018-12-07 2020-06-11 三菱日立パワーシステムズ株式会社 軸流式ターボ機械及びその翼

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3067518B1 (fr) * 2015-03-11 2022-12-21 Rolls-Royce Corporation Aube statorique ou rotorique pour un moteur à turbine à gaz, moteur à turbine à gaz et procédé de fabrication d'une aube statorique directrice pour un moteur à turbine à gaz
EP3553277B1 (fr) * 2017-02-07 2023-06-28 IHI Corporation Aube de machine à flux axial
DE102019117298A1 (de) * 2019-06-27 2020-12-31 Man Energy Solutions Se Turbolader-Turbinenrotor und Turbolader

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU556238A1 (ru) * 1975-09-23 1977-04-30 Предприятие П/Я А-3513 Рабочее колесо радиально-осевой гидромашины
DE19941134C1 (de) * 1999-08-30 2000-12-28 Mtu Muenchen Gmbh Schaufelkranz für eine Gasturbine
US20020194733A1 (en) * 2001-06-22 2002-12-26 Surace Raymond C. Method for repairing cracks in a turbine blade root trailing edge
US6942460B2 (en) * 2002-01-04 2005-09-13 Mitsubishi Heavy Industries, Ltd. Vane wheel for radial turbine
EP1731712A1 (fr) * 2005-06-06 2006-12-13 General Electric Company Aube de turbine comprenant un contour de raccordement variable et composé

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6524070B1 (en) * 2000-08-21 2003-02-25 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
DE102004043036A1 (de) * 2004-09-06 2006-03-09 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidentnahme
GB2436597A (en) * 2006-03-27 2007-10-03 Alstom Technology Ltd Turbine blade and diaphragm

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU556238A1 (ru) * 1975-09-23 1977-04-30 Предприятие П/Я А-3513 Рабочее колесо радиально-осевой гидромашины
DE19941134C1 (de) * 1999-08-30 2000-12-28 Mtu Muenchen Gmbh Schaufelkranz für eine Gasturbine
US20020194733A1 (en) * 2001-06-22 2002-12-26 Surace Raymond C. Method for repairing cracks in a turbine blade root trailing edge
US6942460B2 (en) * 2002-01-04 2005-09-13 Mitsubishi Heavy Industries, Ltd. Vane wheel for radial turbine
EP1731712A1 (fr) * 2005-06-06 2006-12-13 General Electric Company Aube de turbine comprenant un contour de raccordement variable et composé

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8801367B2 (en) 2011-09-23 2014-08-12 United Technologies Corporation Hollow fan blade channel configuration to reduce stress
US8807924B2 (en) 2011-09-23 2014-08-19 United Technologies Corporation Fan blade channel termination
US10215027B2 (en) 2012-01-04 2019-02-26 United Technologies Corporation Aluminum fan blade construction with welded cover
US9221120B2 (en) 2012-01-04 2015-12-29 United Technologies Corporation Aluminum fan blade construction with welded cover
WO2014113043A1 (fr) * 2013-01-18 2014-07-24 United Technologies Corporation Flanc de raccordement composite pour aube directrice
CN104234754A (zh) * 2013-06-05 2014-12-24 阿尔斯通技术有限公司 用于燃气涡轮的翼型件、叶片和导叶
KR20140143091A (ko) * 2013-06-05 2014-12-15 알스톰 테크놀러지 리미티드 가스 터빈용 에어포일, 블레이드 및 베인
EP2811115A1 (fr) 2013-06-05 2014-12-10 Alstom Technology Ltd Profil d'aube pour turbine à gaz, pale et aube de guidage
CN104234754B (zh) * 2013-06-05 2016-04-13 阿尔斯通技术有限公司 用于燃气涡轮的翼型件、叶片和导叶
US9581027B2 (en) 2013-06-05 2017-02-28 General Electric Technology Gmbh Airfoil for gas turbine, blade and vane
EP2811116A1 (fr) 2013-06-05 2014-12-10 Alstom Technology Ltd Aube pour turbine à gaz, aube de rotor et stator
JP2020090953A (ja) * 2018-12-07 2020-06-11 三菱日立パワーシステムズ株式会社 軸流式ターボ機械及びその翼
CN111287800A (zh) * 2018-12-07 2020-06-16 三菱日立电力系统株式会社 轴流式涡轮机械以及其叶片
US11242755B2 (en) * 2018-12-07 2022-02-08 Mitsubishi Power, Ltd. Axial flow turbomachine and blade thereof
DE102019219106B4 (de) 2018-12-07 2024-10-17 Mitsubishi Heavy Industries, Ltd. Axialströmungsturbomaschine und schaufel

Also Published As

Publication number Publication date
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