EP1907670B1 - Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type - Google Patents

Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type Download PDF

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Publication number
EP1907670B1
EP1907670B1 EP06764215A EP06764215A EP1907670B1 EP 1907670 B1 EP1907670 B1 EP 1907670B1 EP 06764215 A EP06764215 A EP 06764215A EP 06764215 A EP06764215 A EP 06764215A EP 1907670 B1 EP1907670 B1 EP 1907670B1
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EP
European Patent Office
Prior art keywords
blade
cavity
platform
airfoil
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.)
Active
Application number
EP06764215A
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German (de)
English (en)
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EP1907670A1 (fr
Inventor
Fathi Ahmad
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
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Siemens AG
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Filing date
Publication date
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Priority to EP06764215A priority Critical patent/EP1907670B1/fr
Priority to PL06764215T priority patent/PL1907670T3/pl
Publication of EP1907670A1 publication Critical patent/EP1907670A1/fr
Application granted granted Critical
Publication of EP1907670B1 publication Critical patent/EP1907670B1/fr
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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
    • 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
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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
    • F05D2260/231—Preventing heat transfer

Definitions

  • the invention relates to a turbine blade for a gas turbine, with a blade root, followed sequentially by a platform region with a transversely extending platform and adjoining a longitudinally curved blade profile, with at least one foot end open and traversed by a coolant cavity extending through extends the blade root and the platform area into the blade profile. Moreover, the invention relates to the use of such a turbine blade.
  • a cooled blade of a gas turbine which has meandering cooling channels inside.
  • delimiting inner walls turbulators are provided in the region of the blade profile, which fan the heat transfer of blade material in the cavity flowing through the coolant. Due to the increased heat transfer, the turbine blade can thus withstand higher operating temperatures.
  • cracks can occur in the area of the hollow-throat-like transition from platform to blade profile, which is also referred to as fillet in English, and / or in the platform. If the resulting cracks exceed a critical crack length, safe operation of the gas turbine equipped with such a turbine blade is not ensured.
  • Another prior art turbine engine is known from the EP 1 267 040 known. Accordingly, a particularly long service life of the turbine blade is a design target with which the disposal period of a gas turbine equipped with it can be further increased.
  • the object of the invention is to provide a turbine blade for a gas turbine where the fatigue life is prolonged. In addition, it is an object of the invention to provide the use of such a turbine blade.
  • the invention is based on the finding that the wear and the crack formation and the subsequent crack growth are thermally induced.
  • the material of the turbine blade is exposed to thermal stresses caused by the external application of hot gas and the internal cooling. It has been found that during operation of the gas turbine in the trough-like transition region between the blade profile and the platform, locally comparatively low hot gas side temperatures occur compared to those in the area of the blade profile. Therefore, the internally cooled turbine blade with turbulators arranged on the inner walls in the area of the platform has hitherto been over-cooled in localized areas. As a result, locally comparatively large temperature differences in the blade material and correspondingly large thermal stresses occurred, which could cause the wear. This effect does not occur in the forefront in particular
  • the invention proposes to substantially reduce these local thermal stresses in the transition region merely by not cooling them as much as the blade profile. To achieve this, it is provided in a generic turbine blade that a section of the surface of the inner wall lying at least in the blade profile and adjacent to the platform region is free of structural elements.
  • the temperature gradient in the blade material is lowered due to the warmer transition region, which prolongs the life of the turbine blade.
  • the proposed measure extends the life, in particular the low cycle fatigue (LCF) for the platform and its transition into the blade profile, ie. H. in the fillet, extended.
  • LCF low cycle fatigue
  • the embodiment in which the surface of the inner wall at the level of the platform portion and the surface of the inner wall of the adjoining portion in the interior of the blade profile are flat. Due to the flow of coolant not swirled in this section, the heat transfer from the blade material into the coolant is reduced compared to the heat transfer in the airfoil profile, so that the temperature difference between a hot gas-charged outer surface of the turbine blade, the hot side, and the coolant-charged inner wall of the turbine blade, the cold side, can be significantly reduced by a permissible increase in the material temperature. The reduction leads to reduced thermal stresses, especially in the area of the transition between the blade profile and the platform, ie in the fillet.
  • the structural elements on the inner wall of the blade profile are generally flat, but - viewed in the radial direction - spaced to form a mean minimum distance from each other, provides an advantageous further development that between the platform surface and - also in the radial direction - the next adjacent structural element determined distance is greater than the average, minimum distance between two adjacent structural elements.
  • the distance is preferably at least 1.1 times the mean minimum distance.
  • the section has a height of 5% of the profile height of the blade profile to the profile peak, calculated from the platform surface.
  • the structural elements are designed as turbulators in the form of ribs, base fields, dimples and / or nipples.
  • the wear-causing local temperature difference between the hot side and the cold side occurs particularly in a middle region of the transitional region between a leading edge of the airfoil and a trailing edge of the airfoil, it is particularly advantageous if the surface of the intermediate region between the leading edge and the trailing edge lying inner wall is free of structural elements.
  • the turbine blade several, extending through the turbine blade radially extending and separated by support ribs cavities, in which only lying between the leading edge and the trailing edge of the blade profile, in the central region cavity has the portion of the inner wall whose surface of the inner wall in the blade profile is free of structural elements.
  • the arranged in the central region between the leading edge and trailing edge on the pressure side platform is structurally particularly wide, so far the local temperature minimum occurred in the blade material at this point.
  • the temperature minimum can be increased while reducing the thermal stress, in particular if the surface of the inner wall, which inner wall is formed by the suction-side profile wall of the blade profile, is free of structural elements. As a result, a particularly long service life extension of the expediently cast turbine blade can be brought about.
  • 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 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17 which communicates with an annular hot gas channel 18.
  • There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 is formed of two blade rings.
  • a hot gas 11 produced in the annular combustion chamber 6 follows in the hot gas channel 18 in each case one row of guide blades 13 formed by a rotor blades 15 row 14
  • the vanes 12 are attached to the stator, whereas the blades 15 a row 14 by means of a turbine disk 19 on the rotor are attached.
  • a generator or a working machine (not shown) coupled.
  • a hollow turbine blade 50 according to the invention shows FIG. 2 in perspective view.
  • the preferably cast turbine blade 50 comprises a blade root 52 on which a platform 54 is arranged along a blade axis and a blade profile 56, which is not shown in its entirety but shortened.
  • the blade profile 56 has a pressure-side profile wall 62 and a suction-side profile wall 64, which extend from a front edge 66 of the blade profile 56 to a trailing edge 68.
  • the hot gas 11 flows along the profile walls 62, 64, from the front edge 66 in the direction of the trailing edge 68.
  • a hollow throat-like transition region 48 is formed.
  • the first partial cavity 58a runs parallel to and in the region of the front edge.
  • a second partial cavity 58b follows - seen in the flow direction of the hot gas, behind it.
  • the partial cavities 58 extend in the radial direction, relative to the installation position of the turbine blade 50 in the gas turbine 1, and are separated from one another by support ribs 70.
  • the support ribs 70 connect the pressure-side profile wall 62 with the suction-side profile wall 64.
  • partial cavities 58 in FIG. 2 shown turbine blade 50 no structural elements shown.
  • FIG. 3 shows the inventive designed as a blade or vane turbine blade 50 according to the cross section III-III of FIG. 2 ,
  • the blade root 52 follows in the radial direction, based on the installation position in the gas turbine 1, the platform 54 and the blade profile 56. Both the outside of the blade profile 56 and the blade profile 56 facing surface 61 of the platform 54 are the gas turbine 1 flowing through the hot gas 11th exposed and are referred to as a hot side.
  • the sectional plane of the cross section III-III extends through the second of the three side open partial cavities 58.
  • the foot side supplied coolant K such as cooling air, cools the turbine blade 50, so that they can withstand the temperatures occurring during operation of the gas turbine.
  • the second partial cavity 58b is surrounded by an inner wall 59 which is partially formed by the pressure-side profile wall 62 and the suction-side profile wall 64.
  • On the inner surfaces of the profile walls 62, 64 and the inner walls 59 are provided to increase the heat transfer of heated by the hot gas 11 blade material in the interior flowing coolant K structural elements 72 in the form of turbulators, as ribs, base fields, dimples and / or Nipples can be formed. In the embodiment shown, it is transverse to the coolant flow direction ribs.
  • the turbulators or the structural elements 72 approximately over an entire profile height H from the platform 54 to the blade tip 74 (FIG. FIG. 4 ) on the surfaces of the inner walls 59, as shown on the pressure-side profile wall 62 in a first section.
  • a new path is now taken.
  • the structural elements 72 no longer begin in the region of the platform surface 61, but only from a predetermined height in the blade profile 56.
  • a second section A lying in the blade profile 56 and adjacent to the platform region is the surface
  • the second section A adjoining the platform region is already located in the blade profile 56
  • the surface of the inner wall 59 located in this region is accordingly flat and not profiled by structural elements.
  • Adjacent to the second gate A in the direction of the profile tip 74 is a region C of the surface of the inner wall 59, in which turbulators or structural elements 72 have an average, minimum distance m from each other, which is determined in the radial direction.
  • the radially measured distance D between the lowest structural element 73 adjacent to the platform surface 61 and the platform surface 61 is greater than the average, minimum distance m,
  • the inflowing coolant K flows first laminar in the second section A due to the locally flat surface and meanwhile cools the blade material convectively. Subsequently, the coolant K flowing in region C is swirled due to the structural elements 72, 73, which leads to an improved heat transfer. This ensures that the transition area 48 is local Less cooled than the rest of the blade profile 56 and so the thermal stresses are reduced at this point, which only rarely cause cracks. Crack growth is delayed as compared to a prior art turbine blade. As a result, the life of the turbine blade 50 is prolonged by the proposed measures.
  • FIG. 4 shows a further turbine blade according to the invention 50 in longitudinal section with a blade root 52, a platform 54 and a blade profile 56.
  • the profiled blade root 52 may be formed in the shape of a fir tree or dovetail in cross section.
  • the turbine blade 50 is also hollow and has four radially extending part cavities 58, which are separated from each other by support ribs 70 which connect the pressure side profile wall 62 with the suction side profile wall 64.
  • the surface of the inner wall 59 located in this region is flat and not profiled by structural elements.
  • the second section A for example, has a height of 5% of the profile height H, calculated from the platform surface 61.
  • the lower temperature differences reduce the thermal stresses in the blade material in the transition region, thereby reducing crack initiation and retarding crack growth, significantly increasing the fatigue life of the turbine blade 50.
  • a gas turbine equipped with such a turbine blade 50 can be operated longer; the turbine blades 50 used must less frequently be checked for defects such as cracks. This significantly increases the availability of the gas turbine 1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Blast Furnaces (AREA)

Claims (12)

  1. Aube ( 50 ) de turbine pour une turbine à gaz,
    comprenant une emplanture ( 52 ) d'aube à laquelle se raccordent successivement une partie de plate-forme ayant une plate-forme ( 504 ) s'étendant transversalement et à celle-ci un profil ( 56 ) d'aube courbé,
    comprenant une surface ( 61 ) de plate-forme prévue sur la plate-forme, pouvant être alimentée en gaz chaud et de laquelle le profil ( 56 ) courbe s'étend jusqu'à une pointe d'aube ayant une hauteur ( H ) de profil,
    comprenant au moins une cavité ( 58 ) qui est ouverte du côté de l'emplanture, dans laquelle peut passer un fluide ( 60 ) de refroidissement et qui s'étend dans l'emplanture ( 52 ) d'aube et dans la partie de plate-forme jusque dans le profil ( 56 ) d'aube et qui est subdivisée au moins en une première sous-cavité voisine du bord avant et en une deuxième sous-cavité voisine de la première sous-cavité, les sous-cavités étant entourées en partie de parois ( 59 ) intérieures à la surface desquelles sont prévus des éléments ( 72, 73 ) de structure influant sur le fluide ( 60 ) de refroidissement,
    dans laquelle une première partie ( A ), qui se trouve au moins dans le profil ( 56 ) d'aube et qui est voisine de la partie de plate-forme, de la surface de la paroi ( 59 ) intérieure de la première sous-cavité a au moins un élément de structure,
    caractérisée
    en ce qu'une deuxième partie ( A ), qui se trouve au moins dans le profil ( 56 ) d'aube et qui est voisine de la partie de plate-forme, de la surface de la paroi ( 59 ) intérieure de la deuxième sous-cavité est sans élément ( 72, 73 ) de structure.
  2. Aube ( 50 ) de turbine suivant la revendication 1,
    dans laquelle la surface de la paroi ( 59 ) intérieure de la deuxième sous-cavité est plate au niveau de la partie de la plate-forme et la surface de la paroi ( 59 ) intérieure de la deuxième partie ( A ) qui en est voisine est plate dans le profil ( 56 ) d'aube.
  3. Aube ( 50 ) de turbine suivant la revendication 1 ou 2,
    dans laquelle, dans la deuxième sous-cavité, la surface ( 60 ) de la plate-forme et, vu dans la direction radiale, l'élément ( 73 ) de structure le plus voisin sont à une distance ( D ) qui est plus grande qu'un intervalle ( m ) minimum moyen entre deux éléments ( 72, 73 ) de structure immédiatement voisins prévus dans le profil ( 56 ) d'aube.
  4. Aube ( 50 ) de turbine suivant la revendication 3,
    dans laquelle la distance ( D ) représente au moins 1,1 fois l'intervalle ( m ) minimum moyen entre deux éléments ( 72, 73 ) de structure prévus dans le profil ( 56 ) d'aube.
  5. Aube ( 50 ) de turbine suivant l'une des revendications 1 à 4,
    dans laquelle la deuxième partie ( A ) a une hauteur représentant 5 % de la hauteur ( H ) du profil, calculée à partir de la surface ( 61 ) de la plate-forme.
  6. Aube ( 50 ) de turbine suivant l'une des revendications 1 à 5,
    dans laquelle une partie ( B ), qui a les éléments ( 72, 73 ) de structure, de la paroi ( 59 ) intérieure se trouvant dans le profil ( 56 ) d'aube de la deuxième sous-cavité ne commence qu'à partir d'une hauteur de 10 % de la hauteur ( H ) du profilé, calculée à partir de la surface ( 61 ) de la plate-forme dans la direction de la pointe ( 74 ) du profil.
  7. Aube ( 50 ) de turbine suivant l'une des revendications 1 à 6,
    dans laquelle les éléments ( 72, 73 ) de structure sont constitués sous la forme d'éléments donnant de la turbulence, en forme de nervures, de champs d'embout, de bossages et/ou de mamelons.
  8. Aube ( 50 ) de turbine suivant l'une des revendications 1 à 7,
    dans laquelle les sous-cavités sont séparées les unes des autres par des nervures ( 70 ) d'appui,
    et dans laquelle la deuxième sous-cavité se trouve entre le bord ( 66 ) avant et le bord ( 68 ) arrière du profil ( 56 ) d'aube dans la partie médiane.
  9. Aube ( 50 ) de turbine suivant la revendication 8,
    dans laquelle le profil ( 56 ) d'aube a une paroi ( 64 ) de profil du côté d'extrados, qui délimite en partie la cavité ( 58 ) et sur la face intérieure tournée vers la cavité ( 58 ) de laquelle se trouve la deuxième partie ( A ) de la surface des parois ( 59 ) intérieures.
  10. Aube ( 50 ) de turbine suivant la revendication 9,
    dans laquelle le profil ( 56 ) d'aube a une paroi ( 62 ) de profil du côté d'extrados, qui délimite en partie la cavité ( 58 ) et sur la face intérieure tournée vers la cavité ( 58 ) de laquelle se trouve la première partie ( A ) de la surface des parois ( 59 ) intérieures.
  11. Aube ( 50 ) coulée de turbine suivant l'une des revendications 1 à 10.
  12. Utilisation d'une aube ( 50 ) de turbine suivant l'une des revendications 1 à 11 dans une turbine ( 1 ) à gaz, de préférence fixe.
EP06764215A 2005-07-27 2006-07-19 Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type Active EP1907670B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP06764215A EP1907670B1 (fr) 2005-07-27 2006-07-19 Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type
PL06764215T PL1907670T3 (pl) 2005-07-27 2006-07-19 Chłodzona łopatka dla turbiny gazowej i zastosowanie takiej łopatki turbiny

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05016328 2005-07-27
EP06764215A EP1907670B1 (fr) 2005-07-27 2006-07-19 Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type
PCT/EP2006/064414 WO2007012592A1 (fr) 2005-07-27 2006-07-19 Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type

Publications (2)

Publication Number Publication Date
EP1907670A1 EP1907670A1 (fr) 2008-04-09
EP1907670B1 true EP1907670B1 (fr) 2008-11-05

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ID=35448370

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EP06764215A Active EP1907670B1 (fr) 2005-07-27 2006-07-19 Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type

Country Status (9)

Country Link
US (1) US8545169B2 (fr)
EP (1) EP1907670B1 (fr)
JP (1) JP4689720B2 (fr)
CN (1) CN101627182B (fr)
AT (1) ATE413514T1 (fr)
DE (1) DE502006002030D1 (fr)
ES (1) ES2314928T3 (fr)
PL (1) PL1907670T3 (fr)
WO (1) WO2007012592A1 (fr)

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Publication number Publication date
CN101627182A (zh) 2010-01-13
JP4689720B2 (ja) 2011-05-25
US20090035128A1 (en) 2009-02-05
ES2314928T3 (es) 2009-03-16
PL1907670T3 (pl) 2009-04-30
ATE413514T1 (de) 2008-11-15
JP2009517574A (ja) 2009-04-30
DE502006002030D1 (de) 2008-12-18
CN101627182B (zh) 2013-02-27
WO2007012592A1 (fr) 2007-02-01
EP1907670A1 (fr) 2008-04-09
US8545169B2 (en) 2013-10-01

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