EP2096261A1 - Aube de turbine pour une turbine à gaz stationnaire - Google Patents

Aube de turbine pour une turbine à gaz stationnaire Download PDF

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Publication number
EP2096261A1
EP2096261A1 EP08003728A EP08003728A EP2096261A1 EP 2096261 A1 EP2096261 A1 EP 2096261A1 EP 08003728 A EP08003728 A EP 08003728A EP 08003728 A EP08003728 A EP 08003728A EP 2096261 A1 EP2096261 A1 EP 2096261A1
Authority
EP
European Patent Office
Prior art keywords
side wall
platform
rib
turbine blade
opening
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Withdrawn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
EP08003728A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Michael Dr. Dankert
Günther Dr. Walz
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 EP08003728A priority Critical patent/EP2096261A1/fr
Priority to CN200980106674.7A priority patent/CN101960096B/zh
Priority to PCT/EP2009/051909 priority patent/WO2009106462A1/fr
Priority to EP09713896A priority patent/EP2245273B1/fr
Priority to JP2010548075A priority patent/JP4971507B2/ja
Priority to AT09713896T priority patent/ATE531899T1/de
Priority to PL09713896T priority patent/PL2245273T3/pl
Priority to ES09713896T priority patent/ES2374520T3/es
Priority to US12/919,265 priority patent/US8602741B2/en
Publication of EP2096261A1 publication Critical patent/EP2096261A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the invention relates to a turbine blade for a stationary gas turbine, comprising at least one platform region, which comprises a platform with a platform surface on which a profiled in cross section airfoil is arranged with a pressure side wall and a suction side wall, wherein the hot gas exposable surfaces of the pressure side wall and the suction side wall each pass over an outer rounding in the platform surface and with at least one arranged in the blade, extending into the platform area cavity, in the at least one the pressure side wall with the suction side wall connecting rib is provided, which along a longitudinal direction of the airfoil dividing dividing the cavity.
  • the aforementioned turbine blades have long been known. As a rule, they have an airfoil traversed by cavities, which cavities are separated from one another by ribs.
  • the ribs extend from the suction sidewall to the pressure sidewall and along the longitudinal direction of the airfoil, ie, from the platform to the blade tip.
  • Molded turbine blades have a transition region between the blade and the platform surface, which thickens the blade side walls, ie the suction side wall and the pressure side wall, in this area by means of a fillet-like rounding. In the transition region thus an accumulation of material is present, which also brings a jump in stiffness of the airfoil with it.
  • the blade is thus platform-stiffer than in its central region or blade tip side. Due to this jump in stiffness, larger temperature gradients can occur during operation, which cause high thermal stresses and thus limit the service life of the turbine blade.
  • At least one of the ribs arranged in the blade leaf has an opening penetrating the rib at the level of the outer rounding in the case of an input turbine blade.
  • the accumulation of material as a whole can be reduced there.
  • These simple constructive means lead to the equalization of the jump in stiffness and to the reduction of the temperature gradient in the then reduced material accumulation.
  • the effects caused by the opening on the cooling air system of the turbine blade as well as on the voltage increase around the opening are to be considered in addition.
  • the so-called creep life due to the reduced, supporting cross-section of the rib and the possibly altered natural frequencies due to the then missing mass Accordingly, it may be useful to provide an oval opening with a suitable orientation.
  • the extension of the rib can be useful up to the platform area and beyond to the foot or mounting area of the turbine blade.
  • an adaptation of a further rounding between the rib and the side wall may be expedient.
  • the proposed measures may also be combined to compensate for the changes that occur through the use of the near-wall opening to achieve an overall extended life of the turbine blade. Overall, can be reduced with the invention, the burden of material accumulation and thus increase the life.
  • the inventive measure to provide in the rib at the level of the outer rounding a rib penetrating wall-near opening is easy to implement and can also be retrofitted in operationally loaded turbine blades, provided that the accessibility of the rib is ensured by the blade root.
  • the opening in the manufacture of new parts can be achieved in a simple manner when the blade and the platform are cast in one piece and the casting core used for the production of the cavities in the casting device for the later in the rib existing near wall opening through one in the core existing hole is realized.
  • the hole can also be used to stabilize the casting core and other so-called cross-over holes, which neither near the wall nor at the level of the outer rounding in a rib, which is arranged between the suction side wall and the pressure side wall, are provided, can be omitted.
  • An opening penetrating the rib is not only close to the wall when it is arranged eccentrically between the suction side wall and the pressure side wall, but also when it touches or intersects the side wall plane spanned by the inside of the suction side wall and / or pressure side wall.
  • the opening is round or oval. These openings are particularly easy to produce, especially when the turbine blade is cast substantially in one piece. A casting core must then have only a corresponding hole at the appropriate location.
  • the life of a corresponding to the preamble of claim 1 turbine blade can also be extended by the fact that the platform-side fin end extends longer or shorter on the inside of the pressure side wall than on the inside of the suction side wall.
  • the turbine blade according to the second embodiment can have a platform surface which is part of an imaginary platform plane which extends through the cavity, wherein the platform-side end of the rib lies on the pressure side on the one hand the platform plane and on the suction side on the other hand the platform plane.
  • FIG. 1 shows a perspective view of a turbine blade 10 for a stationary gas turbine.
  • the turbine blade 10 according to FIG. 1 is designed as a blade. However, the invention can also be applied in guide vanes of a stationary gas turbine.
  • the cast, one-piece turbine blade 10 comprises along a longitudinal direction 12 a blade root 14, to which a platform region 16 adjoins.
  • the platform region 16 essentially comprises a platform 18 with a platform surface 20.
  • the platform surface 20 is essentially planar and thus part of an imaginary platform plane 22.
  • An airfoil profiled in cross-section is arranged on the platform surface 20.
  • the airfoil 24 is formed by a pressure side wall 26 and a suction side wall 28, which extend from a common leading edge 30 to a common trailing edge 32 and thereby merge into each other at both the leading edge 30 and the trailing edge 32.
  • the surfaces of the suction side wall 28, the pressure side wall 26 and the platform surface 20 are flowed around by a hot gas of the gas turbine. Both the pressure side wall 26 and the suction side wall 28 merge into the platform 18 via a hollow groove-like circumferential rounding 34.
  • the rounding 34 or the transition region is also known as fillet.
  • Each rib 36 extends, at least within the airfoil 24, along its longitudinal direction 12. In FIG. 1 only a stub of the airfoil 24 is shown. The complete blade up to the blade tip is indicated only by a dashed line.
  • FIG. 2 shows the detail Z of the turbine blade 10 according to FIG. 1 in a perspective view, wherein for reasons of clarity insignificant elements in the direction of the leading edge 30 and trailing edge 32 are hidden.
  • FIG. 2 shows in detail the already too FIG. 1 features described: the platform surface 20, the pressure sidewall 26, the suction sidewall 28, the platform 18, the rib 36, and the fillet 34.
  • a rib 36 penetrating wall-near opening 40 is provided.
  • the near-wall opening 40 is executed in the embodiment shown around.
  • An oval opening 40 is possible.
  • the opening 40 is arranged with respect to an inner side 42 of the pressure side wall 26 such that the sidewall plane 44 spanned by it is cut by the opening 40. This results in the region of the rounding 34, a material reduction, which is shown hatched by the reference numeral 46 is shown.
  • the platform-side rib end extends on the inside 42 of the pressure side wall 26 less far than the arranged on the inside 43 of the suction side wall 28 fin end.
  • the platform surface 20 is part of an imaginary platform plane 22 which extends through the cavity.
  • the platform-side end of the rib 36 on the pressure side on the one hand ie above (blade tip side) of the platform level 22 and suction side on the other hand, ie below (blade foot side) of the platform level 22.
  • An inverted arrangement of the rib ends is also possible, in which the platform side terminates the pressure-side end of the rib below and the suction-side end of the rib above the platform plane.
  • the manner of the course of the platform-side rib end of the pressure side 26 to the suction side 28 may be formed arbitrarily.
  • the course can for example be rectilinear or, as in the FIG. 3 shown embodiment, convex / concave.
  • a further rounding which is present in the transition from rib 36 to the inner wall 42, 43 of the pressure side wall 26 and / or suction side wall 28, adapted.
  • the adjustment leads to different radii for the further rounding at different positions along the longitudinal extension 12 of the airfoil 24.
  • the radius of the further rounding can be greater at the level of the outer rounding than the radius of the further rounding at the mean height of the airfoil 24.
  • the opening 40 or recess is provided on the pressure side wall.
  • the opening 40 or the recess according to the invention can be arranged on the suction side, since higher hot gas and material temperatures occur in the corresponding regions.
  • the inside 43 of the suction side wall 28 caused recess at the level of the outer fillet 34 may extend along the inside 42, 43 also beyond the region of the rib 36 out, so that the recess is disposed on the inside also in the portion of the transition region where no rib 36, the side walls 26, 28 is supported.
  • the recess deepens each associated spanned sidewall plane of the side walls 26, 28 in a hollow throat, whereby a mass reduction can also be achieved in the portion of the outer rounding 34, in which no rib 36 is arranged.
  • This recess can also be in accordance with FIG. 3 trained turbine blade can be used.
  • stress reductions can thus be achieved, which causes cracking and possibly crack growth to occur further delayed in this section of the transition region.
  • the invention relates to a turbine blade 10 for a stationary gas turbine, which has a hollow airfoil 24 in which at least one inside the inside of the pressure side wall 26 and the suction side wall 28 supporting rib 36 is present, in order to extend the life of the turbine blade 10 in height the outer fillet 34 between the side wall 26, 28 and platform surface 20, a rib 36 penetrating wall near opening 40 is provided.
  • a rib 36 penetrating wall near opening 40 is provided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
EP08003728A 2008-02-28 2008-02-28 Aube de turbine pour une turbine à gaz stationnaire Withdrawn EP2096261A1 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP08003728A EP2096261A1 (fr) 2008-02-28 2008-02-28 Aube de turbine pour une turbine à gaz stationnaire
CN200980106674.7A CN101960096B (zh) 2008-02-28 2009-02-18 用于固定式燃气轮机的涡轮叶片
PCT/EP2009/051909 WO2009106462A1 (fr) 2008-02-28 2009-02-18 Aube de turbine destinée à une turbine à gaz fixe
EP09713896A EP2245273B1 (fr) 2008-02-28 2009-02-18 Aube de turbine destinée à une turbine à gaz fixe
JP2010548075A JP4971507B2 (ja) 2008-02-28 2009-02-18 定置型ガスタービン用のタービン翼
AT09713896T ATE531899T1 (de) 2008-02-28 2009-02-18 Turbinenschaufel für eine stationäre gasturbine
PL09713896T PL2245273T3 (pl) 2008-02-28 2009-02-18 Łopatka turbiny, do stacjonarnej turbiny gazowej
ES09713896T ES2374520T3 (es) 2008-02-28 2009-02-18 �?labe de turbina para una turbina de gas fija.
US12/919,265 US8602741B2 (en) 2008-02-28 2009-02-18 Turbine vane for a stationary gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08003728A EP2096261A1 (fr) 2008-02-28 2008-02-28 Aube de turbine pour une turbine à gaz stationnaire

Publications (1)

Publication Number Publication Date
EP2096261A1 true EP2096261A1 (fr) 2009-09-02

Family

ID=40242678

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08003728A Withdrawn EP2096261A1 (fr) 2008-02-28 2008-02-28 Aube de turbine pour une turbine à gaz stationnaire
EP09713896A Not-in-force EP2245273B1 (fr) 2008-02-28 2009-02-18 Aube de turbine destinée à une turbine à gaz fixe

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09713896A Not-in-force EP2245273B1 (fr) 2008-02-28 2009-02-18 Aube de turbine destinée à une turbine à gaz fixe

Country Status (8)

Country Link
US (1) US8602741B2 (fr)
EP (2) EP2096261A1 (fr)
JP (1) JP4971507B2 (fr)
CN (1) CN101960096B (fr)
AT (1) ATE531899T1 (fr)
ES (1) ES2374520T3 (fr)
PL (1) PL2245273T3 (fr)
WO (1) WO2009106462A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014116475A1 (fr) 2013-01-23 2014-07-31 United Technologies Corporation Composant de moteur à turbine à gaz ayant une extrémité de nervure profilée

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101543141B1 (ko) * 2011-04-22 2015-08-07 미츠비시 히타치 파워 시스템즈 가부시키가이샤 날개 부재 및 회전 기계
EP2863010A1 (fr) * 2013-10-21 2015-04-22 Siemens Aktiengesellschaft Aube de turbine
US10519781B2 (en) 2017-01-12 2019-12-31 United Technologies Corporation Airfoil turn caps in gas turbine engines
US10465528B2 (en) 2017-02-07 2019-11-05 United Technologies Corporation Airfoil turn caps in gas turbine engines
US10480329B2 (en) 2017-04-25 2019-11-19 United Technologies Corporation Airfoil turn caps in gas turbine engines
US10267163B2 (en) * 2017-05-02 2019-04-23 United Technologies Corporation Airfoil turn caps in gas turbine engines
DE102017218886A1 (de) * 2017-10-23 2019-04-25 MTU Aero Engines AG Schaufel und Rotor für eine Strömungsmaschine sowie Strömungsmaschine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2314125A (en) * 1988-08-24 1997-12-17 United Technologies Corp Cooled blades for a gas turbine engine
US5716192A (en) * 1996-09-13 1998-02-10 United Technologies Corporation Cooling duct turn geometry for bowed airfoil
EP1420142A1 (fr) * 1997-08-07 2004-05-19 United Technologies Corporation Aube refroidie pour turbine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3370829A (en) * 1965-12-20 1968-02-27 Avco Corp Gas turbine blade construction
US6290463B1 (en) * 1999-09-30 2001-09-18 General Electric Company Slotted impingement cooling of airfoil leading edge
GB2395232B (en) * 2002-11-12 2006-01-25 Rolls Royce Plc Turbine components
US7195448B2 (en) 2004-05-27 2007-03-27 United Technologies Corporation Cooled rotor blade
US20050265839A1 (en) * 2004-05-27 2005-12-01 United Technologies Corporation Cooled rotor blade
US7220103B2 (en) 2004-10-18 2007-05-22 United Technologies Corporation Impingement cooling of large fillet of an airfoil
CA2548184A1 (fr) * 2005-05-26 2006-11-26 S. C. Johnson Home Storage, Inc. Dispositif et methode de retenue dynamique d'un element de manoeuvre d'un mecanisme de fermeture allonge
US7713027B2 (en) * 2006-08-28 2010-05-11 United Technologies Corporation Turbine blade with split impingement rib

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2314125A (en) * 1988-08-24 1997-12-17 United Technologies Corp Cooled blades for a gas turbine engine
US5716192A (en) * 1996-09-13 1998-02-10 United Technologies Corporation Cooling duct turn geometry for bowed airfoil
EP1420142A1 (fr) * 1997-08-07 2004-05-19 United Technologies Corporation Aube refroidie pour turbine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014116475A1 (fr) 2013-01-23 2014-07-31 United Technologies Corporation Composant de moteur à turbine à gaz ayant une extrémité de nervure profilée
EP2948636A4 (fr) * 2013-01-23 2016-11-23 United Technologies Corp Composant de moteur à turbine à gaz ayant une extrémité de nervure profilée
US10472970B2 (en) 2013-01-23 2019-11-12 United Technologies Corporation Gas turbine engine component having contoured rib end

Also Published As

Publication number Publication date
ATE531899T1 (de) 2011-11-15
PL2245273T3 (pl) 2012-03-30
JP2011513623A (ja) 2011-04-28
US8602741B2 (en) 2013-12-10
ES2374520T3 (es) 2012-02-17
WO2009106462A1 (fr) 2009-09-03
EP2245273B1 (fr) 2011-11-02
CN101960096B (zh) 2014-06-25
CN101960096A (zh) 2011-01-26
JP4971507B2 (ja) 2012-07-11
US20110033305A1 (en) 2011-02-10
EP2245273A1 (fr) 2010-11-03

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