US20090252615A1 - Cooled Turbine Rotor Blade - Google Patents

Cooled Turbine Rotor Blade Download PDF

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Publication number
US20090252615A1
US20090252615A1 US12/310,690 US31069007A US2009252615A1 US 20090252615 A1 US20090252615 A1 US 20090252615A1 US 31069007 A US31069007 A US 31069007A US 2009252615 A1 US2009252615 A1 US 2009252615A1
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US
United States
Prior art keywords
turbine rotor
rotor blade
area
cooled turbine
cooling
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.)
Abandoned
Application number
US12/310,690
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English (en)
Inventor
Heinz-Jürgen Gross
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
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GROSS, HEINZ-JUERGEN
Publication of US20090252615A1 publication Critical patent/US20090252615A1/en
Abandoned 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film 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
    • 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
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a cooled turbine rotor blade.
  • a turbine rotor blade of this generic type and having an airfoil profile is known from EP 0 735 240 A1.
  • a plurality of mutually adjacent cooling channels are provided in order to cool the airfoil profile, are arranged in a meandering shape, and a coolant can flow through them sequentially.
  • the cooling channels in this case each run parallel to the leading edge.
  • Respectively adjacent cooling channels are separated from one another by ribs, with the ribs ending in a direction-reversal area in which the adjacent cooling channels merge into one another.
  • direction-changing blades FIG. 12
  • direction-changing blades FIG. 12
  • a turbine blade is known from U.S. Pat. No. 5,246,340, which has a plurality of mutually parallel cooling channels in the interior.
  • the cooling channels are in each case separated by a rib.
  • An opening which connects two adjacent cooling channels is provided in one of the ribs in the area of the blade tip, through which opening a lateral flow can pass for impingement cooling of the blade airfoil tip.
  • GB 2 106 996 discloses a turbine blade having an impingement cooling insert in the form of a laminate.
  • the object of the present invention is to provide a turbine rotor blade whose life is further improved.
  • the object relating to the provision of a turbine rotor blade of this generic type is achieved by designing this turbine rotor blade according to the characterizing part of claim 1 . It is proposed that at least one of the ribs—seen from the attachment area to the tip area—has an essentially constant rib thickness and is curved toward the leading edge or trailing edge forming a cooling-channel corner area, which has an acute angle in longitudinal section, in the area of the airfoil tip, and that at least one opening is provided, which is arranged in the curvature, connects two adjacent cooling channels and through which a part of the coolant flow of the cooling channel which is adjacent to the corner area can flow into the acute-angled corner area of the cooling channel.
  • the curved rib results in the direction of the cooling air flowing through the cooling channels being changed in a considerably more aerodynamic manner.
  • the direction change is an integral component of the rib, as a result of which the regions with a relatively low flow rate or no flow rate (dead-water regions) in the direction-changing area can be avoided.
  • the flow rate is in consequence kept approximately constant in that cooling channel toward which the rib is curved.
  • the curvature of the rib results in an acute-angled corner area in the adjacent cooling channel, in which dead-water regions could now once again occur.
  • At least one opening is also provided, which is arranged in the curvature and connects the two adjacent cooling channels, and through which a part of the cooling flow can pass over or flow over from one cooling channel into the other cooling channel at an early stage.
  • the opening which is arranged in the curved rib can be provided in a particularly simple form.
  • the casting apparatus which is used for casting the turbine rotor blades comprises, in order to produce the cavities through which a coolant can flow, a casting core which has core elements arranged in a meandering shape.
  • a core support can be provided between two adjacent core elements and, after removal of the casting core from the cast, integral turbine blade, leaves behind it the opening within the curved rib. This results in a stabilized casting core which improves the accuracy of the production method.
  • the terminating wall which is likewise frequently subject to local overheating and is also referred to as a crown base, can also be impingement-cooled on the basis of the coolant jet passing through the opening, in such a way that this likewise makes it possible to cool the terminating wall particularly efficiently.
  • the opening just has to be inclined such that its longitudinal extent is directed at the terminating wall.
  • the rib which is adjacent to the trailing edge is preferably curved in the area of the airfoil tip.
  • the rib seen from the attachment area to the tip area—is curved toward the leading edge thus making it possible to provide an essentially constant flow cross-sectional area in a part of the direction-changing area between two adjacent coolant channels. This reduces the pressure losses in the coolant.
  • the rib has an essentially constant rib thickness along its curvature.
  • the inner face of the terminating wall is equipped with turbulators, thus making it possible to improve the cooling of the terminating wall or of the crown base in a simple manner.
  • a coolant it is possible for a coolant to flow sequentially or else in parallel through the adjacent cooling channels. If the flow passes in parallel through the coolant channels, care must be taken to ensure that there is an adequate pressure gradient between them, in order to obtain a coolant flow which passes through the opening.
  • FIGURE shows a longitudinal section through a turbine rotor blade according to the invention with cooling channels arranged in a meandering shape.
  • the FIGURE shows a longitudinal section through a turbine rotor blade 10 which is produced by a casting method.
  • the turbine rotor blade 10 which is therefore integral, has an attachment area 12 , with a firtree-shaped cross section, with a platform 14 and an airfoil profile 16 arranged thereon.
  • the airfoil profile 16 which has an aerodynamically profiled cross section, is formed by a suction-side blade wall and a pressure-side blade wall, which each extend from a leading edge 18 to a trailing edge 20 and in this case surround a cavity, which is arranged in the interior of the airfoil profile 16 and in which a plurality of cooling channels 22 a , 22 b , 22 c , 22 d are provided.
  • the cooling channels 22 are adjacent to one another and each run approximately parallel to the leading edge 18 .
  • the mutually adjacent cooling channels 22 are each separated from one another in places by a rib 24 a , 24 b , 24 c which connects the pressure-side blade wall to the suction-side blade wall.
  • the cooling channels 22 are bounded by a terminating wall 28 in the area of the airfoil tip 27 which is opposite the attachment area 12 .
  • the terminating wall 28 is also referred to as a crown base.
  • the turbine rotor blade 10 which is illustrated in the FIGURE has a cooling channel 22 a on the leading-edge side to which, on the attachment side, a coolant 29 , for example cooling air or cooling vapor, can be supplied.
  • a coolant 29 for example cooling air or cooling vapor
  • the cooling air that is supplied cools the area of the leading edge 18 of the airfoil profile 16 using conventional cooling methods, for example convection cooling, impingement cooling and/or film cooling.
  • the coolant 29 which can be supplied to the root end of the cooling channel 22 b , flows along the channel 22 b to the airfoil tip 27 , and its direction is then changed in a direction-changing area 30 in order to reverse its flow direction, specifically toward the attachment area 12 .
  • the rib 24 c which is adjacent to the trailing edge 20 is curved in the area of the airfoil tip 27 , with a constant rib thickness D.
  • the curvature 32 is such that the rib 24 c —seen from the attachment area 12 to the tip area 26 —is curved toward the leading edge 18 .
  • An acute-angled corner area 34 is formed by the curvature 32 of the rib 24 c , which is adjacent to the trailing edge 20 , in the cooling channel 22 d in the area of the airfoil tip 27 .
  • An opening 40 is provided in the rib 24 c in the area of the curvature 32 , through which opening 40 the coolant 29 which is flowing in the direction-changing area 30 can partially flow out therefrom and can flow into the corner area 34 by virtue of the pressure ratio there. If required, a plurality of openings 40 may also be provided in order to influence the flow more specifically in the corner areas 34 .
  • the corner area 34 can therefore be adequately cooled. Areas with reduced coolant flow rates and in consequence with inadequate cooling are therefore reliably avoided at this point.
  • the coolant jet passing through the opening 40 impinges on the inner face 42 of the terminating wall 28 and in this case provides impingement cooling for the airfoil tip 27 .
  • turbulators 44 can also be provided on the inner face 42 of the terminating wall 28 , further enlarging the surface area to be cooled.
  • the coolant 29 which flows along the inner face 42 of the terminating wall 28 can further increase the heat transfer coefficient on the cooling-air side by virtue of the stimulation of turbulence, thus making it possible to achieve even better cooling of the crown base.
  • the rib 24 a may merge, curved in the direction of the trailing edge 20 , into the terminating wall 28 in the tip area 26 of the turbine rotor blade 10 , with one or more openings likewise being provided in the curvature.
  • the invention specifies a turbine rotor blade 10 for an axial-flow gas turbine, in particular a stationary gas turbine, which is equipped with an attachment area 12 , an airfoil profile 16 and a plurality of cooling channels 22 which are arranged in a meandering shape in the interior of the airfoil profile 16 .
  • the invention proposes that at least one of the ribs 24 run in a curved form toward the leading edge 18 or toward the trailing edge 20 in the area of the airfoil tip 27 , with the rib thickness D remaining constant, and that at least one opening 40 be provided in the curvature 32 of the rib 24 , through which opening 40 a portion of the coolant 29 which is flowing in the direction-changing area 30 can pass into the adjacent cooling channel 22 d.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Separation By Low-Temperature Treatments (AREA)
US12/310,690 2006-09-04 2007-06-27 Cooled Turbine Rotor Blade Abandoned US20090252615A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06018490A EP1895096A1 (de) 2006-09-04 2006-09-04 Gekühlte Turbinenlaufschaufel
EP06018490.0 2006-09-04
PCT/EP2007/056425 WO2008028702A1 (de) 2006-09-04 2007-06-27 Gekühlte turbinenlaufschaufel

Publications (1)

Publication Number Publication Date
US20090252615A1 true US20090252615A1 (en) 2009-10-08

Family

ID=37718882

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/310,690 Abandoned US20090252615A1 (en) 2006-09-04 2007-06-27 Cooled Turbine Rotor Blade

Country Status (10)

Country Link
US (1) US20090252615A1 (https=)
EP (2) EP1895096A1 (https=)
JP (1) JP2010502872A (https=)
CN (1) CN101512106A (https=)
AT (1) ATE458126T1 (https=)
DE (1) DE502007002880D1 (https=)
ES (1) ES2340338T3 (https=)
PL (1) PL2059655T3 (https=)
RU (1) RU2410546C2 (https=)
WO (1) WO2008028702A1 (https=)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100232975A1 (en) * 2009-03-10 2010-09-16 Honeywell International Inc. Turbine blade platform
US20130048243A1 (en) * 2011-08-26 2013-02-28 Hs Marston Aerospace Ltd. Heat exhanger apparatus
US20180283183A1 (en) * 2017-04-03 2018-10-04 General Electric Company Turbine engine component with a core tie hole
CN113464209A (zh) * 2020-03-31 2021-10-01 通用电气公司 具有带有偏移肋的冷却回路的涡轮机转子叶片

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2954798B1 (fr) * 2009-12-31 2012-03-30 Snecma Aube a ventilation interieure
CN102943693A (zh) * 2012-11-29 2013-02-27 哈尔滨汽轮机厂有限责任公司 一种高效冷却的中低热值燃机透平动叶
EP3123000B1 (en) 2014-03-27 2019-02-06 Siemens Aktiengesellschaft Blade for a gas turbine and method of cooling the blade
FR3021697B1 (fr) * 2014-05-28 2021-09-17 Snecma Aube de turbine a refroidissement optimise
FR3021699B1 (fr) * 2014-05-28 2019-08-16 Safran Aircraft Engines Aube de turbine a refroidissement optimise au niveau de son bord de fuite
US10508548B2 (en) * 2017-04-07 2019-12-17 General Electric Company Turbine engine with a platform cooling circuit
US11021961B2 (en) * 2018-12-05 2021-06-01 General Electric Company Rotor assembly thermal attenuation structure and system
DE102019108811B4 (de) * 2019-04-04 2024-02-29 Man Energy Solutions Se Laufschaufel einer Strömungsmaschine
CN110410158B (zh) * 2019-08-16 2022-04-12 杭州汽轮动力集团有限公司 一种燃气轮机的涡轮转子叶片

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5246340A (en) * 1991-11-19 1993-09-21 Allied-Signal Inc. Internally cooled airfoil
US5462405A (en) * 1992-11-24 1995-10-31 United Technologies Corporation Coolable airfoil structure
US5902093A (en) * 1997-08-22 1999-05-11 General Electric Company Crack arresting rotor blade
US20050084370A1 (en) * 2003-07-29 2005-04-21 Heinz-Jurgen Gross Cooled turbine blade

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SU902541A1 (ru) * 1979-04-09 1995-02-09 Уфимский авиационный институт им.Орджоникидзе Охлаждаемая лопатка турбины
GB2106996A (en) * 1981-09-30 1983-04-20 Rolls Royce Cooled rotor aerofoil blade for a gas turbine engine
SU1332933A2 (ru) * 1985-04-29 2005-12-10 К.С. Нетесов Рабочая лопатка газовой турбины
SU1275963A1 (ru) * 1985-06-11 2006-01-27 О.С. Чернилевский Охлаждаемая лопатка
DE4443696A1 (de) * 1994-12-08 1996-06-13 Abb Management Ag Gekühlte Turbinenschaufel
JPH11200805A (ja) * 1998-01-14 1999-07-27 Toshiba Corp 構造要素の冷却方法、冷却用流路付構造要素および冷却用流路付ガスタービン翼
US7118325B2 (en) * 2004-06-14 2006-10-10 United Technologies Corporation Cooling passageway turn

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5246340A (en) * 1991-11-19 1993-09-21 Allied-Signal Inc. Internally cooled airfoil
US5462405A (en) * 1992-11-24 1995-10-31 United Technologies Corporation Coolable airfoil structure
US5902093A (en) * 1997-08-22 1999-05-11 General Electric Company Crack arresting rotor blade
US20050084370A1 (en) * 2003-07-29 2005-04-21 Heinz-Jurgen Gross Cooled turbine blade

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100232975A1 (en) * 2009-03-10 2010-09-16 Honeywell International Inc. Turbine blade platform
US8147197B2 (en) * 2009-03-10 2012-04-03 Honeywell International, Inc. Turbine blade platform
US20130048243A1 (en) * 2011-08-26 2013-02-28 Hs Marston Aerospace Ltd. Heat exhanger apparatus
US9260191B2 (en) * 2011-08-26 2016-02-16 Hs Marston Aerospace Ltd. Heat exhanger apparatus including heat transfer surfaces
US20180283183A1 (en) * 2017-04-03 2018-10-04 General Electric Company Turbine engine component with a core tie hole
US11021967B2 (en) * 2017-04-03 2021-06-01 General Electric Company Turbine engine component with a core tie hole
CN113464209A (zh) * 2020-03-31 2021-10-01 通用电气公司 具有带有偏移肋的冷却回路的涡轮机转子叶片

Also Published As

Publication number Publication date
RU2410546C2 (ru) 2011-01-27
EP2059655B1 (de) 2010-02-17
PL2059655T3 (pl) 2010-07-30
WO2008028702A1 (de) 2008-03-13
EP2059655A1 (de) 2009-05-20
EP1895096A1 (de) 2008-03-05
RU2009112405A (ru) 2010-10-20
CN101512106A (zh) 2009-08-19
JP2010502872A (ja) 2010-01-28
ES2340338T3 (es) 2010-06-01
DE502007002880D1 (de) 2010-04-01
ATE458126T1 (de) 2010-03-15

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Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GROSS, HEINZ-JUERGEN;REEL/FRAME:022389/0435

Effective date: 20090210

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION