EP1126136B1 - Turbinenschaufel mit luftgekühltem Deckbandelement - Google Patents

Turbinenschaufel mit luftgekühltem Deckbandelement Download PDF

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Publication number
EP1126136B1
EP1126136B1 EP00810966A EP00810966A EP1126136B1 EP 1126136 B1 EP1126136 B1 EP 1126136B1 EP 00810966 A EP00810966 A EP 00810966A EP 00810966 A EP00810966 A EP 00810966A EP 1126136 B1 EP1126136 B1 EP 1126136B1
Authority
EP
European Patent Office
Prior art keywords
cooling
shroud
turbine blade
band element
holes
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.)
Expired - Lifetime
Application number
EP00810966A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1126136A3 (de
EP1126136A2 (de
Inventor
Ibrahim Dr. El-Nashar
Hartmut Haehnle
Rudolf Kellerer
Beat Von Arx
Bernhard Prof.Dr. Weigand
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1126136A2 publication Critical patent/EP1126136A2/de
Publication of EP1126136A3 publication Critical patent/EP1126136A3/de
Application granted granted Critical
Publication of EP1126136B1 publication Critical patent/EP1126136B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular

Definitions

  • the present invention relates to the field of gas turbines. It relates to an air-cooled turbine blade according to the preamble of claim 1.
  • Such a turbine blade is e.g. from US Pat. No. 5,482,435 or US Pat. No. 5,785,496.
  • the known cooling holes occupy comparatively little space within the shroud element. Since a certain minimum thickness of the shroud element is required for introducing the holes in the shroud element, and this or an even greater thickness of the shroud element is maintained in the area outside the holes, there is an unfavorably small ratio of flow-through shroud volume to not Wegströmtem shroud volume. This has the consequence that the cooling of the shroud element is not optimal, and that the shroud element is relatively heavy due to the large proportion of solid material and is therefore exposed to high mechanical stresses during operation due to centrifugal forces.
  • EP-A-1 013 884 discloses a turbine blade with actively cooled shroud element, in which cooling holes in the shroud element run approximately parallel to the direction of movement of the blade tip from inside to outside and open into a recess open towards the outside in front of the outer edge.
  • DE-A-196 01 819 discloses transverse to the direction of movement of the blade extending cooling holes, which branch off from longitudinal distribution channels and open at the ends in the outer space.
  • JP-A-03 194101 shows shroud elements with wide, slot-shaped. Cooling channels in which distributed posts are arranged.
  • JP-A-58 047104 discloses shroud elements with cooling holes extending in the direction of movement of the blade tip, which open directly into the outer space in the direction of the bore.
  • JP-A-08 028303 discloses shroud elements with cooling bores extending in the direction of movement of the blade tip, which open at the ends individually vertically upwards into the outer space.
  • US-A-3 433 015 shows cooled shrouds with restriction sites between the blade tip and the discharge ports.
  • EP-A-0 927 814 discloses oblique cooling holes in the shroud element.
  • the object is solved by the entirety of the features of claim 1.
  • the core of the invention is to design the cooling fluid-carrying cavities in the interior of the shroud element in coordination with the shroud element in shape and dimension so that the volume flowed through by the cooling fluid occupies a high proportion of the total volume of the shroud element. In this way, the weight of the shroud element can be significantly reduced with very efficient cooling.
  • the turbine blade according to the invention is characterized in that the cavities comprise cooling bores extending in the direction of movement of the blade tip, that the cooling bores are thwarted by a plurality of transverse bores, and that the transverse bores to the outside space are shut off by closed ends.
  • This configuration of intersecting cooling holes is geometrically similar to the previously mentioned wide distributed pin arrangement slots. Again, the solid material of the shroud element is significantly reduced and thus saved weight at greatly improved heat transfer.
  • the intersecting cooling holes can be relatively easily introduced into the shroud element by conventional means. Cooling technology particularly favorable cooling holes can be achieved if the cooling holes and the cross holes are made by means of the so-called "STEM drilling" process.
  • a turbine blade is shown in plan view from above.
  • the turbine blade 10 comprises the actual blade profile 23 (which extends perpendicular to the plane of the drawing) and a shroud element 11 arranged transversely thereto on the blade tip, which together with the shroud elements of the other blades (not shown) results in a continuous, annular, mechanically stabilizing shroud.
  • the airfoil 23 is internally hollow and is traversed by one or more cooling air channels 18 (indicated by dashed lines in Fig. 1) which direct cooling air from the blade root to the blade tip (see, e.g., Fig. 2 of US-A-5,482,435).
  • the shroud element 11 has on its upper side (22 in FIG. 2) two ribs 12 and 13 extending parallel in the direction of movement of the blade tip, which together with the opposite housing wall 20 of the gas turbine form a cavity 21 connected by gaps with the surroundings (FIG. 2).
  • cooling bores 16, 16 'and 17, 17' (dashed lines in Fig. 1 and 2), starting from the center to the outside.
  • the cooling holes may be of uniform shape, but may also be configured differently.
  • the cooling bores 16, 17 are designed as bores with a largely constant diameter, while the cooling bores 16 ', 17' are designed as diffusers with a cross-section widening in the direction of flow.
  • the cooling bores 16, 16 'and 17, 17' are on the input side with the cooling air channel 18 in connection and are supplied by this with cooling air (or other cooling fluid).
  • the cooling holes 16, 17 do not extend entirely to the lateral end or edge of the shroud element 11, but each open from the side in an elongated, from the top into the shroud element 11 recessed recess 14 or 15. This ensures that the cooling air always passes through the cooling holes, even if two (adjacent) shroud elements in mechanical Standing in contact.
  • each of the cooling bores 16, 16 'and 17, 17' can also be associated with a separate depression.
  • blowing out the cooling air leads upward to a "blowing" of the cavity 21 in the shroud (FIG. 2).
  • This leads to an increase in the pressure in the gap between shroud element 11 and housing wall 20 and thus contributes to a reduction of the penetrating mass flow of hot gas 24 at.
  • the mixing temperature is lowered in this area, whereby the thermal load of the shroud element 11 is reduced from the top 22 ago.
  • the cooling bores 16, 16 'and 17, 17' preferably on the input side, i. in the region of the cooling air supply to the profile 23, each equipped with a throttle point 19. This makes it possible to selectively limit the cooling air mass flow and to obtain a much more efficient cooling.
  • FIGS. 3 and 4 An alternative form of weight reduction is shown in FIGS. 3 and 4.
  • a wide slot 25 and 26 is provided in the interior of the shroud element 11 instead of a plurality of cooling holes on both sides of the blade profile, which extends from the central cooling air channel 18 to the lateral recesses 14 and 15 and opens there.
  • the slots 25, 26 lead because of their continuous width to a significant weight reduction and ensure over the entire width evenly distributed cooling
  • each throttle 19 or 19 ' may be provided to limit the cooling air mass flow, the throttle points each at the input side (throttle points 19) and / or the output side (throttling points 19 ') of the slots 25, 26 are positioned.
  • the cooling through the slots 25, 26 can be further increased in its effect, if a distributed arrangement (an "array") of pins 27 is provided as means for improving the heat transfer in the slots.
  • the pins 7 increase the turbulence of the cooling air flow and provide additional surfaces for heat transfer. In addition, they act mechanically stabilizing as they pass in the slots from wall to wall.
  • the number and arrangement of the pins in the "array" can be changed as part of optimizing the cooling effect.
  • FIG. 5 and 6 An embodiment of the inventive method of weight reduction is shown in Fig. 5 and 6.
  • a "matrix" of parallel cooling holes 16, 17 (drilling axis 29) and these crossing transverse bores 28 (drilling axis 30) generated in their effect in terms of weight reduction and cooling comparable to the pin-occupied slots of Fig. 3 and 4 is.
  • the cooling holes 16, 17 and the transverse bores 28 are preferably made by the so-called "STEM drilling" method, which is described in detail in US-A-5,306,401, as are the cooling holes in Figs. This makes it possible (by changing the feed) to provide the cooling bores 16, 17 and transverse bores 28 with internal roughness such as turbulators or ribs.
  • the cooling holes 16, 17 and transverse holes 28 are to the side by after drilling locked ends 31 and 32 shut off.
  • the cooling bores 16, 17 also have here preferably throttle points 19 and open into laterally arranged, upwardly open recesses 14, 15th

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00810966A 1999-12-28 2000-10-19 Turbinenschaufel mit luftgekühltem Deckbandelement Expired - Lifetime EP1126136B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19963377A DE19963377A1 (de) 1999-12-28 1999-12-28 Turbinenschaufel mit aktiv gekühltem Deckbandelement
DE1996377 1999-12-28

Publications (3)

Publication Number Publication Date
EP1126136A2 EP1126136A2 (de) 2001-08-22
EP1126136A3 EP1126136A3 (de) 2004-05-19
EP1126136B1 true EP1126136B1 (de) 2006-06-14

Family

ID=7934748

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00810966A Expired - Lifetime EP1126136B1 (de) 1999-12-28 2000-10-19 Turbinenschaufel mit luftgekühltem Deckbandelement

Country Status (4)

Country Link
US (1) US6464460B2 (zh)
EP (1) EP1126136B1 (zh)
CN (1) CN1278018C (zh)
DE (2) DE19963377A1 (zh)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6869270B2 (en) * 2002-06-06 2005-03-22 General Electric Company Turbine blade cover cooling apparatus and method of fabrication
ATE348942T1 (de) 2003-07-23 2007-01-15 Alstom Technology Ltd Verfahren zur aufbereitung und verfahren zur herstellung einer turbinenschaufel
EP1515000B1 (de) * 2003-09-09 2016-03-09 Alstom Technology Ltd Beschaufelung einer Turbomaschine mit konturierten Deckbändern
US20060280610A1 (en) * 2005-06-13 2006-12-14 Heyward John P Turbine blade and method of fabricating same
GB2430170B (en) * 2005-09-15 2008-05-07 Rolls Royce Plc Method of forming a cast component
US20070201980A1 (en) * 2005-10-11 2007-08-30 Honeywell International, Inc. Method to augment heat transfer using chamfered cylindrical depressions in cast internal cooling passages
US7686581B2 (en) * 2006-06-07 2010-03-30 General Electric Company Serpentine cooling circuit and method for cooling tip shroud
US7762774B2 (en) * 2006-12-15 2010-07-27 Siemens Energy, Inc. Cooling arrangement for a tapered turbine blade
US7568882B2 (en) * 2007-01-12 2009-08-04 General Electric Company Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method
US7946817B2 (en) * 2008-01-10 2011-05-24 General Electric Company Turbine blade tip shroud
US7946816B2 (en) * 2008-01-10 2011-05-24 General Electric Company Turbine blade tip shroud
US20090180894A1 (en) * 2008-01-10 2009-07-16 General Electric Company Turbine blade tip shroud
US8057177B2 (en) * 2008-01-10 2011-11-15 General Electric Company Turbine blade tip shroud
US8322986B2 (en) * 2008-07-29 2012-12-04 General Electric Company Rotor blade and method of fabricating the same
GB0901129D0 (en) * 2009-01-26 2009-03-11 Rolls Royce Plc Rotor blade
CH700686A1 (de) * 2009-03-30 2010-09-30 Alstom Technology Ltd Schaufel für eine gasturbine.
CN102069365B (zh) * 2009-11-25 2014-12-10 中国江南航天工业集团林泉电机厂 一种散热器的制造方法及散热器
US8444372B2 (en) 2011-02-07 2013-05-21 General Electric Company Passive cooling system for a turbomachine
EP2713009B1 (en) * 2012-09-26 2015-03-11 Alstom Technology Ltd Cooling method and system for cooling blades of at least one blade row in a rotary flow machine
CN107438717B (zh) * 2015-04-15 2021-10-08 罗伯特·博世有限公司 自由梢端型轴流式风扇组件
US10947898B2 (en) * 2017-02-14 2021-03-16 General Electric Company Undulating tip shroud for use on a turbine blade
JP6636668B1 (ja) * 2019-03-29 2020-01-29 三菱重工業株式会社 高温部品、高温部品の製造方法及び流量調節方法
US11255198B1 (en) * 2021-06-10 2022-02-22 General Electric Company Tip shroud with exit surface for cooling passages

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US6254345B1 (en) * 1999-09-07 2001-07-03 General Electric Company Internally cooled blade tip shroud

Also Published As

Publication number Publication date
CN1278018C (zh) 2006-10-04
DE19963377A1 (de) 2001-07-12
EP1126136A3 (de) 2004-05-19
CN1301911A (zh) 2001-07-04
EP1126136A2 (de) 2001-08-22
DE50012982D1 (de) 2006-07-27
US20010006600A1 (en) 2001-07-05
US6464460B2 (en) 2002-10-15

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