EP1621730B1 - Gekühltes Bauteil einer Strömungsmaschine und Verfahren zum Giessen dieses gekühlten Bauteils - Google Patents

Gekühltes Bauteil einer Strömungsmaschine und Verfahren zum Giessen dieses gekühlten Bauteils Download PDF

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Publication number
EP1621730B1
EP1621730B1 EP04017673A EP04017673A EP1621730B1 EP 1621730 B1 EP1621730 B1 EP 1621730B1 EP 04017673 A EP04017673 A EP 04017673A EP 04017673 A EP04017673 A EP 04017673A EP 1621730 B1 EP1621730 B1 EP 1621730B1
Authority
EP
European Patent Office
Prior art keywords
cooling
cooling passage
moving blade
turbine moving
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.)
Not-in-force
Application number
EP04017673A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1621730A1 (de
Inventor
Jürgen Dellmann
Gernot Lang
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 DE502004008210T priority Critical patent/DE502004008210D1/de
Priority to AT04017673T priority patent/ATE410586T1/de
Priority to ES04017673T priority patent/ES2312890T3/es
Priority to EP04017673A priority patent/EP1621730B1/de
Priority to CN200510084761.0A priority patent/CN1727643B/zh
Priority to US11/189,409 priority patent/US7824156B2/en
Publication of EP1621730A1 publication Critical patent/EP1621730A1/de
Application granted granted Critical
Publication of EP1621730B1 publication Critical patent/EP1621730B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • 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

Definitions

  • the invention relates to a cooled turbine blade of a gas turbine, in which can be acted upon by the working medium outer wall, a cooling channel is provided, which is flowed through along its longitudinal axis by a cooling fluid.
  • a heat exchanger tube which has along its longitudinal axis, extending inside and twisted around the main flow direction ribs.
  • the ribs serve to enlarge the inner surface of the tube and to generate a twist in the medium flowing through the tube. This is intended to increase the heat transfer compared to a smooth tube.
  • a turbine blade is known as a cooled component of a gas turbine.
  • the hot working fluid generated in a gas turbine by the combustion of a fuel flows along the blades of the rotor to generate rotational energy.
  • they are cooled by means of air or steam.
  • the blades of the gas turbine have a channel extending in the interior of the blade in the region of a leading edge and extending in the radial direction of the rotor. A cooling fluid flowing in this channel cools the particularly thermally stressed leading edge.
  • a blade is eg from the DE 197 38 065 A1 known.
  • FIG. 10 shows the US 2004/96313 A1 a hollow turbine blade with a leading edge channel, which is connected to a downstream in the flow direction of the hot gas lying second cooling channel via a connecting channel.
  • the connecting channel runs approximately parallel to the outer wall of the turbine blade and flows tangentially into the leading edge channel.
  • the connecting channel is also, with respect to the main flow direction of the hot gas, slightly inclined at an angle between 5 ° and 45 ° in order to provide for improved cooling the inflow channel along cooling air flowing with a directed around the channel axis swirl. It is also proposed to provide the leading edge channel with one or more vanes with identical inclination as the connecting channel, which impart additional swirl to the incoming cooling air, or which maintain the swirl of the cooling air.
  • the guide elements and grooves can be provided.
  • the object of the invention is to provide a cooled turbine blade for a gas turbine, which can be cooled more efficiently to increase efficiency.
  • a means be provided in the cooling channel, which imparts a twist to the flowing cooling fluid and that the cooling channel has on its inner surface at least one turbulator element, which is only in the region or the part of the cooling channel periphery is provided, which faces the suction-side outer wall.
  • the swirl in the cooling fluid increases the heat transfer. Consequently, the component can be cooled more efficiently, which can be used either to a cooling fluid savings or to a greater heat dissipation. In both cases, the cooling effect is increased, which leads either by an increased hot gas temperature to an improved efficiency or by a lowered thermal component load to improve the economy.
  • An angular momentum on the cooling fluid may be generated if the means for imparting the twist is formed as at least one guide element arranged on the inner surface of the cooling channel, which extends along a helix having a pitch angle of 45 ° or greater. Accordingly, in the cooling fluid flow locally another component in the circumferential direction of the cooling channel is impressed, which represents the twist around the main flow direction.
  • the cooling channel in the manner of a multi-start screw several guide elements with identical pitch angles, thereby creating a flowing in the center of the cooling channel core flow, from which directed transversely to the main flow direction Form part streams as continuous branches. Therefore, all flow channel segments existing between the vanes can communicate with each other.
  • the formation of a controlled and effective core flow over the vane tips in the longitudinal axis leads to increased power values with respect to the heat transfer.
  • the central core flow can form centrally in the interior of the cooling channel if each guide element projects into the cooling channel with a radial extent which is less than half the diameter of the cooling channel.
  • the cooling channel does not have a massive core in the center.
  • each guide element is approximately 0.2 times the diameter of the cooling channel.
  • the guide element protrudes into the cooling channel with a radial extent, which is different along the helical profile of the guide element.
  • the turbulator when the turbulator is formed as a transversely to the helical line of the guide element extending rib or aligned or staggered portions of a rib or nubs, an increase in the heat transfer can be achieved.
  • the turbulence in the cooling fluid caused by the turbulator element can also be used for local adaptation and for increasing the heat transfer.
  • Particularly advantageous is the embodiment in which the turbulator elements protrude with a radial extent in the cooling channel, which is less than the radial extent of the guide elements.
  • the radial extent of each turbulator element is approximately 0.1 times the diameter of the cooling channel.
  • the cross section of the means for impressing the twist in the manner of a pointed thread shaped like a trapezoidal thread, in the manner of a saw thread or in the manner of a round thread.
  • the component is a turbine vane or a turbine blade and the cooling channel extends in the region of a leading edge in the blade longitudinal direction.
  • the means for imparting a twist during casting be produced by inserting the corresponding guide element structure and / or the turbulator element structure into a casting core to be used for forming a cooling channel in the casting mold prior to insertion is incorporated.
  • FIG. 6 shows a gas turbine 11 with a compressor 13, a combustion chamber 15 and a turbine unit 17, which follow one another along a rotor 19 of the gas turbine 11.
  • a working machine for. B. a generator (not shown) coupled.
  • Both in the compressor 13 and in the turbine unit 17 are consecutively provided in blade rings 21, 25 vanes 23 and blades 27.
  • the guide vanes 23 and rotor blades 27 of the turbine unit 17 are cooled with a cooling fluid KF, for example air or steam, so that they are at the temperatures prevailing there of the hot working medium A can withstand.
  • a cooling fluid KF for example air or steam
  • Such a vane 23 is as a cooled component 28 in Fig. 1 shown.
  • the guide blade 23 has a blade root 31, a platform region 33 and an airfoil 35 successively along the blade axis 29.
  • the airfoil 35 extends with a pressure-side outer wall 36 and suction-side outer wall 38 of a leading edge 37 to a trailing edge 39.
  • cooling channel 41 is arranged on the inner surface of a guide member 43 is arranged, the protrudes into the cooling channel 41.
  • Fig. 2 shows a section through the airfoil 35 of a turbine blade, which may be formed as a vane 23 or as a blade 27.
  • a diameter D projecting into the four guide elements 43 in the manner of a four-speed screw.
  • the diameter D is described by a dividable in sections boundary of the cooling channel cross-section, which belongs to an area equal to the cooling channel cross-section circle.
  • the guide elements 43 run in the direction of a center 49 of the cooling channel 41 analogous to a saw thread pointed.
  • the cross section of the guide elements could also be trapezoidal triangular.
  • Fig. 3 The main flow direction of the cooling fluid KF runs along the longitudinal axis 45 of the cooling channel 41.
  • the helical line 44 of the guide element 43 with respect to each plane perpendicular to the longitudinal axis 45, a pitch angle S. on, which is 45 ° or larger.
  • the guide element 43 protrudes with a radial extent h 1 in the circular cross-section in the cooling channel 41, which is on the order of 0.2 times the diameter D.
  • Fig. 3 transverse to the helix 44 the guide elements 43 extending rib or knob-shaped Turbulatormaschine 47, the radial extent h 2 is smaller than that of the guide elements 43, in particular of the order of 0.1 times the diameter D.
  • the airfoil 35 of the turbine blade is flowed around by the working medium A.
  • the cooling fluid KF for example compressor air
  • the cooling channel 41 in the direction of the longitudinal axis 45.
  • the guide elements 43 imprint the cooling fluid KF a transverse to the main flow direction, in particular in the circumferential direction, directed flow component.
  • a swirling core flow flowing in the center 49 is generated, which rotates about the longitudinal axis 45 of the cooling channel 41.
  • the angular momentum exerted on the cooling fluid KF allows the core flow to flow to the outer edge of the cooling passage 41 into the pocket-shaped flow passage segments 50.
  • the radial extent h 1 of the guide elements 43 can extend over the circumference and / or length of the cooling channel 41 rising and decreasing, so that a different sized transverse partial flow can be achieved.
  • the turbulator elements 47 are to be arranged in the flow channel sectors 50 at the parts of the circumference of the cooling channel 41 of the blades 27, which are to be designated in the direction of rotation of the rotor 19 as a leading part of the circumference of the cooling channel 41 with locally lower pressure in the cooling fluid flow, ie the turbulator elements 47th are arranged on the side of the cooling channel 41, which faces the suction-side outer wall 38 (see Fig. 2 ).
  • the volume flow rate of the cooling fluid flow decreases, and at the same time, the cooling fluid flow rate and the local heat transfer inducing turbulence increase.
  • the turbulent amplification of the cooling effect is locally supported by the flow guidance in the region of the rib structure via the specifically placed turbulator elements 47 on the leading side in the rotating system channel side, so that the adverse effect of the centrifugal force field on the heat transfer of the cooling fluid flow is reduced and a smoothing of local temperature gradients and a Improvement of the low-cycle fatigue behavior is brought about.
  • Fig. 4 shows a combustion chamber heat shield 55 as a cooled component 28 of a gas turbine engine.
  • the combustion chamber heat shield 55 has an outer wall 36a which can be acted upon by a hot working medium and in which a plurality of cooling channels 41 are provided for cooling the same.
  • the channels 41 are each formed with four guide elements 43 in the manner of a four-speed screw.
  • Fig. 5 shows the rotor 19 of a gas turbine 11 with a blade attached thereto 27.
  • a respective guide vane 23 is disposed adjacent.
  • a guide ring 61 of the blade tip 52 is opposite.
  • the guide ring 61 limits the flow channel of the turbine unit 17 radially outward.
  • a plurality of cooling channels 41 are arranged, in which the cooling fluid KF can flow, wherein a plurality of guide elements 43 impose an angular momentum or a twist on the cooling fluid KF.
  • turbulators 47 are applicable in the areas of the cooling passage circumference of combustion heat shields 55 and / or guide rings 61, which is closest to the hot gas loaded outer wall.
  • Fig. 5 Analogous to Fig. 2 is in Fig. 5 provided in the blade 27 in the region of the leading edge 37 of the cooling channel 41, in which the guide member 43, the cooling fluid KF imparting a twist.
  • the pitch angle S of the helix 44 is increased in comparison to the radially inner region 67, which leads to an acceleration of the cooling fluid KF. It can thus be a targeted influencing the flow velocity of the cooling fluid KF and the heat transfer.
  • the cooled component 28, in particular a moving blade 27, is known to be produced in the casting process.
  • the means for impressing a swirl ie the guide elements 43 and possibly the turbulator elements, are already taken into account during casting by incorporating the corresponding guide element structure and / or the turbulator element structure before a casting core to be used for forming a cooling channel in a casting mold becomes.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04017673A 2004-07-26 2004-07-26 Gekühltes Bauteil einer Strömungsmaschine und Verfahren zum Giessen dieses gekühlten Bauteils Not-in-force EP1621730B1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE502004008210T DE502004008210D1 (de) 2004-07-26 2004-07-26 Gekühltes Bauteil einer Strömungsmaschine und Verfahren zum Giessen dieses gekühlten Bauteils
AT04017673T ATE410586T1 (de) 2004-07-26 2004-07-26 Gekühltes bauteil einer strömungsmaschine und verfahren zum giessen dieses gekühlten bauteils
ES04017673T ES2312890T3 (es) 2004-07-26 2004-07-26 Elemento enfriado de una turbomaquina y procedimiento de moldeo de este elemento enfriado.
EP04017673A EP1621730B1 (de) 2004-07-26 2004-07-26 Gekühltes Bauteil einer Strömungsmaschine und Verfahren zum Giessen dieses gekühlten Bauteils
CN200510084761.0A CN1727643B (zh) 2004-07-26 2005-07-20 流体机械的冷却构件及其铸造方法和有该构件的燃气轮机
US11/189,409 US7824156B2 (en) 2004-07-26 2005-07-26 Cooled component of a fluid-flow machine, method of casting a cooled component, and a gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04017673A EP1621730B1 (de) 2004-07-26 2004-07-26 Gekühltes Bauteil einer Strömungsmaschine und Verfahren zum Giessen dieses gekühlten Bauteils

Publications (2)

Publication Number Publication Date
EP1621730A1 EP1621730A1 (de) 2006-02-01
EP1621730B1 true EP1621730B1 (de) 2008-10-08

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EP04017673A Not-in-force EP1621730B1 (de) 2004-07-26 2004-07-26 Gekühltes Bauteil einer Strömungsmaschine und Verfahren zum Giessen dieses gekühlten Bauteils

Country Status (6)

Country Link
US (1) US7824156B2 (es)
EP (1) EP1621730B1 (es)
CN (1) CN1727643B (es)
AT (1) ATE410586T1 (es)
DE (1) DE502004008210D1 (es)
ES (1) ES2312890T3 (es)

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US20070014664A1 (en) 2007-01-18
DE502004008210D1 (de) 2008-11-20
CN1727643B (zh) 2010-12-15
ES2312890T3 (es) 2009-03-01
US7824156B2 (en) 2010-11-02
EP1621730A1 (de) 2006-02-01
ATE410586T1 (de) 2008-10-15
CN1727643A (zh) 2006-02-01

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