EP1925780A1 - Aube d' une turbine à écoulement axial - Google Patents

Aube d' une turbine à écoulement axial Download PDF

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Publication number
EP1925780A1
EP1925780A1 EP06024322A EP06024322A EP1925780A1 EP 1925780 A1 EP1925780 A1 EP 1925780A1 EP 06024322 A EP06024322 A EP 06024322A EP 06024322 A EP06024322 A EP 06024322A EP 1925780 A1 EP1925780 A1 EP 1925780A1
Authority
EP
European Patent Office
Prior art keywords
blade
rips
core
suction side
pressure side
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.)
Ceased
Application number
EP06024322A
Other languages
German (de)
English (en)
Inventor
Andrey Shukin
Sergey Shukin
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 EP06024322A priority Critical patent/EP1925780A1/fr
Publication of EP1925780A1 publication Critical patent/EP1925780A1/fr
Ceased 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other

Definitions

  • the invention relates to a blade for an axial-flow turbine, in particular a blade for an axial-flow steam turbine.
  • Blades in particular rotor blades and stator vanes, in axial-flow turbines, in particular in steam turbines, are subjected to mechanical and thermal loads during operation of the turbines.
  • the thermal and mechanical loads are caused by hot gas flow, for example super heated steam in case of a steam turbine, heating up the blades and applying gas forces to the blades.
  • hot gas flow for example super heated steam in case of a steam turbine
  • the rotational speed of the rotor additionally strains the blades due to centrifugal forces.
  • an excessive length of operation time affects the life endurance of the blades.
  • a blade is subjected to a high temperature in combination with a high strain an excessive long time, creeping of the blade can occur resulting in cracks in the blade material and finally in mechanical failure.
  • the strength of the blade material is dependent on stresses applied during operation, operation temperature and operation time. In order to improve the mechanical integrity and life endurance of the blade it is a common remedy to reduce temperature of the gas flow.
  • a blade for an axial-flow turbine comprising a cooling passage formed inside the blade to direct a cooling medium along and beneath at least one of the suction side surface of the blade and the pressure side surface of the blade such that a core of the blade defined by being jacketed by the cooling passage is thermally isolated towards the blade surface.
  • the blade core is thermally isolated from the blade surface prevents a heat input from outside the blade through the blade surface, in particular from a gas flow surrounding the blade, to the blade core. Therefore, even when the blade surface is heated up to a high temperature, the blade core material remains at a moderate temperature level. Hence, the mechanical integrity of the blade core is high, i.e. creeping of the blade core material is low and the life endurance of the blade core is high.
  • Construction-conditioned the blade core bears the main mechanical load affecting upon the blade during operation.
  • the overall mechanical strength of the blade is generally determined by the mechanical strength of the blade core. Therefore, an increase of the mechanical integrity of the blade core, in particular by thermally isolating the blade core from the blade surface, results in an increased overall mechanical strength of the blade. This is achieved even so when the gas flow temperature is high. Therefore, the blade can be operated with hot gas flow and thereby with high thermal efficiency without suffering from deficiencies in mechanical strength.
  • Preferred for the use of the cooling medium is compressed air.
  • the cooling passage is formed into a helical tube shaped channel encircling the blade core.
  • the cooling passage defines at the pressure side blade surface a pressure side blade surface wall, at the suction side blade surface a suction side blade surface wall, and the cooling passage comprises a plurality of webs extending therethrough thereby connecting the blade core to the respective blade surface wall.
  • the cooling medium flowing through the cooling passage contacts the pressure and suction side blade surface via the pressure side blade surface wall and the suction side blade surface wall, respectively.
  • the provision of the plurality of webs extending through the cooling passage increases the mechanical stability of the blade.
  • the pressure side blade surface wall and the suction side blade surface wall provide aerodynamically effective surfaces, whereas the blade core is provided for carrying mechanical loads. Therefore, the thickness of said walls can be minimized leading to an increase of cooling efficiency. Further, the thickness of the blade core is increased leading to an increase in mechanical strength of the blade core.
  • the plurality of webs is comprised by a plurality of pressure side rips extending along the pressure side of the blade, and/or a plurality of suction side rips extending along the suction side of the blade.
  • cooling channels are defined guiding the cooling medium along the pressure and suction sides of the blade, respectively. Therefore, the cooling medium flow is controlled by the rips, in particular with respect to velocity and flow rate.
  • cooling parameters e.g. blade surface temperature and heat transfer rate
  • said cooling parameters can be adjusted for each blade side individually thereby achieving an optimized cooling for each blade side. Therefore, the required flow rate of the cooling medium can be reduced in order to obtain a desired cooling performance.
  • the mechanical coupling between said walls and the blade core is soft, i.e. a movement of the blade core relative to said walls can be compensated by deforming the rips.
  • This relative movement can occur in particular when said walls and the blade core are reaching different temperature levels. For example, in case the gas flow is hot, the surface of the blade and said walls are consequently heated up, whereas due to the cooling effect of the cooling medium the blade core remains at a moderate temperature level.
  • said walls are thermally expanding resulting in a dilatation toward the blade core. Owing to the soft character of coupling between said walls and the blade core only low thermal stresses, if any, occur in the blade material. This leads to a high mechanical integrity of the blade.
  • this soft connection between said walls and the blade core is desired when the temperature difference between said walls and the blade core is high, i.e. the cooling performance of the cooling medium is high.
  • the rips are slim and elongated formed, their cross sections areas are small. Therefore, the heat transfer from the blade surface to the blade core via the rips is low. Hence, the cooling efficiency within the blade is high.
  • the rips may extend parallel to turbine axis direction.
  • the rips are formed to be straight and are arranged to extend parallel to each other, wherein the pressure side rips are inclined from the root of the blade to the tip of the blade by a first predetermined angle, and/or the suction side rips are inclined from the blade tip to the blade root by a second predetermined angle.
  • the cooling medium is advantageously guided diagonally along the pressure and suction side blade surface, respectively. Therefore, the time of contact of the cooling medium with the blade surface is high resulting in an increased cooling performance.
  • the pressure side rips are inclined from the root of the blade to the tip of the blade and the suction side rips are inclined from the blade tip to the blade root, at the pressure side the cooling medium is directed from the blade root to the blade tip by the pressure side rips, whereas at the suction side the cooling medium is directed from the blade tip to the blade root by the suction side rips.
  • the first predetermined angle equals the second predetermined angle.
  • the first predetermined angle and/or the second predetermined angle is in a range between 30° and 70°.
  • the blade core comprises a rear end being arranged to be retracted from the trailing edge of the blade such that in the cooling passage between the blade core rear end and the blade trailing edge a cooling medium mixing zone is defined in which the pressure side rips are connected to the suction side rips thereby forming cross-over points.
  • the pressure side rips together with the suction side rips form a stable and reliable structure. Therefore, during operation of the blade the mechanical load of the blade walls in particular at the tailing edge of the blade is reduced.
  • each the plurality of pressure side rips and/or the plurality of suction side rips are formed by a rip matrix comprised by a plurality of outer rips and a plurality of inner rips, wherein the outer and inner rips are formed to be straight and are arranged to extend parallel to each other, wherein the outer rips are inclined from the root of the blade to the tip of the blade by a third predetermined angle and the inner rips are inclined from the blade tip to the blade root by a forth predetermined angle such that the outer rips are connected to the inner rips thereby forming cross-over points.
  • the cross-over points included in the rip matrix have small cross sectional areas. Therefore, in general the heat flux between the blade walls and the blade core is reduced leading to a higher temperature difference between the blade walls and the blade core. Hence, the thermal isolation of the blade core toward the blade walls is more effective thereby increasing the mechanical integrity of the blade core and of the blade.
  • the mechanical coupling of the blade walls to the blade core through the cross-over points is soft. Due to this, the risk of thermal stresses in the blade walls, the blade core, and in particular in the inner and outer rips is reduced.
  • the third predetermined angle equals the forth predetermined angle.
  • the third predetermined angle as well as the forth predetermined angle is in a range between 30° and 70°.
  • the plurality of webs is comprised by a plurality of pin-fins. It is also preferred to combine the rip structure, the rip matrix and/or the pin-fins.
  • the rip structure can be provided at the pressure and suction side of the blade, whereas at the trailing edge of the blade the pin-fins are provided.
  • the blade root is integrally provided at the blade core. Since the blade core is provided in particular for carrying mechanical loads, the integrally provision of the blade root at the blade core increases the overall stability of the blade.
  • the blade core comprises a front end being arranged to be retracted from the leading edge of the blade such that in the cooling passage between the blade core front end and the blade leading edge a cooling medium entry channel is defined adapted to feed the cooling medium to the downstream portion of the cooling passage.
  • the trailing edge of the blade comprises blade trailing edge apertures connecting the cooling passage toward the outside and being adapted to discharge the cooling medium.
  • the cooling system is simple and cost saving in operation.
  • the blade can be integrally formed. However, it is preferred that the pressure side blade surface wall, the suction side surface wall, and the blade core are formed from an individual material, respectively.
  • the blade is preferably manufactured using investment casting, wherein the blade core is hollowly formed in the centre.
  • the blade core comprising the rips can be manufactured at first, and then the blade walls are added for example by diffusion.
  • the blade is a rotor blade or a stator vane. It is also preferred that the blade is adapted to be used in a steam turbine.
  • a rotor blade 1 for a steam turbine comprises a pressure side blade surface 2, a suction side blade surface 4, a leading edge 13, a trailing edge 14, a blade root 11, and a blade tip 12.
  • the rotational axis of the steam turbine is denoted with x
  • the circumferential direction of the blade rotation is denoted with y
  • the radial axis along the blade height is denoted with z.
  • the blade 1 comprises at its pressure side a pressure side blade surface wall 3 defining the pressure side blade surface 2, and at its suction side a suction side blade surface wall 5 defining the pressure side blade surface 4. Further, the blade 1 comprises a blade core 8 being integrally formed with the blade root 11.
  • a cooling passage is formed separating the blade core 8 from the pressure side surface blade wall 3 as well as from suction side blade surface wall 5.
  • the cooling passage comprises an entry channel 19 with a U-shaped cross section and being arranged in the vicinity of the leading edge 13 and extending in parallel thereto from the blade root 11 to the blade tip 11.
  • the entry channel 11 is provided with an entry chamber 20 having an enlarged cross section with respect to the entry channel 19.
  • the cooling passage comprises a pressure side cooling passage 6 and a suction side cooling passage 7.
  • the pressure and suction side cooling passages 6, 7 are formed into a substantially equally spaced gap defining the pressure side blade surface wall 3 and the suction side blade surface wall 5 as a boundary wall with constant thickness.
  • Cooling air is flown through the cooling passage for thermally isolating the blade core 8 from the pressure and suction side blade surfaces 2, 3 by cooling down the pressure and suction side blade surface walls 3, 4.
  • the inlet flow of the cooling air through the entry channel 19 is shown in figures 1 and 2 with arrows 23.
  • the entry channel 19 runs into the pressure side cooling passage 6 as well as into the suction side cooling passage 7.
  • a front end 9 of the blade core 8 forms the inner boundary of the entry channel 19 such that the inlet flow of the cooling air 23 is separated into a first branch guided to the pressure side cooling passage 6 and a second branch guided to the.suction side cooling passage 7.
  • a rear end 10 of the blade core 8 is arranged retracted from and parallel to the trailing edge 14, wherein between the trailing edge 14 and the blade core rear end 10 both the pressure and suction side cooling passages 6, 7 merge together thereby forming a mixing zone 21.
  • cooling air discharging from the pressure and suction side cooling passages 6, 7 is mixed together in the mixing zone 21.
  • the trailing edge 14 comprises trailing edge apertures 22 such that cooling air having passed the entry chamber 20, the entry channel 19, the pressure side cooling passage 6 as well as the suction side cooling passage 7, and the mixing zone 21 is discharged through the trailing edge apertures 22 towards the outside.
  • the outlet flow of the cooling air through the trailing edge apertures 22 is shown in figures 1 and 2 with arrows 24.
  • the blade 1 is provided with fourteen pressure side rips 15 extending through the pressure side cooling passage 6, and with fourteen suction side rips 16 extending through the suction side cooling passage 7.
  • the rips 15, 16 are formed slim and straight and define between each other channels to be passed through by cooling air.
  • the pressure side rips 15 are inclined from the blade root 11 to the blade tip 12 seen from the leading edge 13 to the trailing edge 13.
  • the inclination is denoted by ⁇ and has a value of 60°.
  • the suction side rips 16 are inclined from the blade tip 12 to the blade root 11 seen from the leading edge 13 to the trailing edge 13.
  • the inclination is denoted by ⁇ and has a value of 60°.
  • the pressure side rips 15 and the suction side rips 16 meet and connect each other thereby forming a grid like rip matrix comprising cross-over points 18.
  • the blade 1 is provided with a rip matrix 17 extending through the pressure side cooling passage 6 and through the suction side cooling passage 7.
  • the rip matrix 17 is comprised by fourteen outer rips 17a facing the blade surface and fourteen inner rips 17b facing the blade core 8.
  • the outer rips 17a are inclined from the blade root 11 to the blade tip 12 seen from the leading edge 13 to the trailing edge 13.
  • the inclination is denoted by ⁇ ' and has a value of 60°.
  • the inner rips 17b are inclined from the blade tip 12 to the blade root 11 seen from the leading edge 13 to the trailing edge 13.
  • the inclination is denoted by ⁇ ' and has a value of 60°.
  • the rips 17a, 17b are formed slim and straight and define between each other channels to be passed through by cooling air. Further, the outer rips 17a and the inner rips 17b meet and connect each other thereby forming the rip matrix 17 comprising cross-over points 18. Since the channels formed by the outer rips 17a and the channels formed by the inner rips 17b are arranged to one another and are connected to each other, cooling air passing through the cooling passages 6, 7 is swirled.
  • Cooling air having passed the pressure side cooling passage 6 and the suction side cooling passage 7 is directly flown through the trailing edge apertures 22 through outside.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06024322A 2006-11-23 2006-11-23 Aube d' une turbine à écoulement axial Ceased EP1925780A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06024322A EP1925780A1 (fr) 2006-11-23 2006-11-23 Aube d' une turbine à écoulement axial

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06024322A EP1925780A1 (fr) 2006-11-23 2006-11-23 Aube d' une turbine à écoulement axial

Publications (1)

Publication Number Publication Date
EP1925780A1 true EP1925780A1 (fr) 2008-05-28

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ID=37680582

Family Applications (1)

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EP06024322A Ceased EP1925780A1 (fr) 2006-11-23 2006-11-23 Aube d' une turbine à écoulement axial

Country Status (1)

Country Link
EP (1) EP1925780A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011050025A3 (fr) * 2009-10-20 2011-12-22 Siemens Energy, Inc. Plan de sustentation incorporant des structures de refroidissement effilées définissant des passages de refroidissement
WO2013077761A1 (fr) 2011-11-25 2013-05-30 Siemens Aktiengesellschaft Profil aérodynamique à passages de refroidissement
US9366143B2 (en) 2010-04-22 2016-06-14 Mikro Systems, Inc. Cooling module design and method for cooling components of a gas turbine system
JP2018115601A (ja) * 2017-01-18 2018-07-26 川崎重工業株式会社 タービン翼の冷却構造
FR3065985A1 (fr) * 2017-05-02 2018-11-09 Safran Aircraft Engines Promoteur de turbulences d'ecoulements de ventilation pour une aube
CN109026173A (zh) * 2018-10-18 2018-12-18 哈尔滨电气股份有限公司 一种适用于20-30mw等级的燃机第二级动叶的冷却结构
CN112832875A (zh) * 2021-02-03 2021-05-25 东方电气集团东方汽轮机有限公司 一种汽轮机汽缸的补汽腔室结构
CN114412577A (zh) * 2022-01-24 2022-04-29 杭州汽轮机股份有限公司 涡轮动叶长叶片

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2823892A (en) * 1952-06-09 1958-02-18 Gen Motors Corp Turbine buckets
US2823829A (en) 1956-02-01 1958-02-18 Milton A Frater Nesting and stacking container
FR2150474A1 (fr) 1971-08-24 1973-04-06 Cabot Corp
FR2150475A1 (fr) * 1971-08-25 1973-04-06 Rolls Royce
GB2094895A (en) 1981-03-16 1982-09-22 Mtu Muenchen Gmbh Turbine blade
EP1277918A1 (fr) 2001-07-18 2003-01-22 FIATAVIO S.p.A. Aube de guidage à doubles parois pour une turbine à gaz
WO2005083235A1 (fr) 2004-02-27 2005-09-09 Siemens Aktiengesellschaft Pale ou aube pour une turbomachine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2823892A (en) * 1952-06-09 1958-02-18 Gen Motors Corp Turbine buckets
US2823829A (en) 1956-02-01 1958-02-18 Milton A Frater Nesting and stacking container
FR2150474A1 (fr) 1971-08-24 1973-04-06 Cabot Corp
FR2150475A1 (fr) * 1971-08-25 1973-04-06 Rolls Royce
GB2094895A (en) 1981-03-16 1982-09-22 Mtu Muenchen Gmbh Turbine blade
EP1277918A1 (fr) 2001-07-18 2003-01-22 FIATAVIO S.p.A. Aube de guidage à doubles parois pour une turbine à gaz
WO2005083235A1 (fr) 2004-02-27 2005-09-09 Siemens Aktiengesellschaft Pale ou aube pour une turbomachine

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011050025A3 (fr) * 2009-10-20 2011-12-22 Siemens Energy, Inc. Plan de sustentation incorporant des structures de refroidissement effilées définissant des passages de refroidissement
CN102753787A (zh) * 2009-10-20 2012-10-24 西门子能量股份有限公司 具有锥形冷却通路的翼型
US8920111B2 (en) 2009-10-20 2014-12-30 Siemens Energy, Inc. Airfoil incorporating tapered cooling structures defining cooling passageways
CN102753787B (zh) * 2009-10-20 2015-11-25 西门子能量股份有限公司 具有锥形冷却通路的翼型
US9366143B2 (en) 2010-04-22 2016-06-14 Mikro Systems, Inc. Cooling module design and method for cooling components of a gas turbine system
WO2013077761A1 (fr) 2011-11-25 2013-05-30 Siemens Aktiengesellschaft Profil aérodynamique à passages de refroidissement
JP2018115601A (ja) * 2017-01-18 2018-07-26 川崎重工業株式会社 タービン翼の冷却構造
FR3065985A1 (fr) * 2017-05-02 2018-11-09 Safran Aircraft Engines Promoteur de turbulences d'ecoulements de ventilation pour une aube
CN109026173A (zh) * 2018-10-18 2018-12-18 哈尔滨电气股份有限公司 一种适用于20-30mw等级的燃机第二级动叶的冷却结构
CN112832875A (zh) * 2021-02-03 2021-05-25 东方电气集团东方汽轮机有限公司 一种汽轮机汽缸的补汽腔室结构
CN112832875B (zh) * 2021-02-03 2022-08-30 东方电气集团东方汽轮机有限公司 一种汽轮机汽缸的补汽腔室结构
CN114412577A (zh) * 2022-01-24 2022-04-29 杭州汽轮机股份有限公司 涡轮动叶长叶片
CN114412577B (zh) * 2022-01-24 2024-03-15 杭州汽轮动力集团股份有限公司 涡轮动叶长叶片

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