EP2163726A1 - Aube de turbine dotée d'un rebord arrière modulaire et graduée - Google Patents

Aube de turbine dotée d'un rebord arrière modulaire et graduée Download PDF

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Publication number
EP2163726A1
EP2163726A1 EP08016009A EP08016009A EP2163726A1 EP 2163726 A1 EP2163726 A1 EP 2163726A1 EP 08016009 A EP08016009 A EP 08016009A EP 08016009 A EP08016009 A EP 08016009A EP 2163726 A1 EP2163726 A1 EP 2163726A1
Authority
EP
European Patent Office
Prior art keywords
blade
trailing edge
wall
turbine blade
insert
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.)
Withdrawn
Application number
EP08016009A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Hans-Thomas Dr. Bolms
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 EP08016009A priority Critical patent/EP2163726A1/fr
Priority to PCT/EP2009/059958 priority patent/WO2010028913A1/fr
Publication of EP2163726A1 publication Critical patent/EP2163726A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/186—Film cooling

Definitions

  • the invention relates to a turbine blade for a gas turbine, comprising an aerodynamically curved airfoil comprising a pressure-side blade wall and a suction-side blade wall, which extend from a common, of a working medium vorströmbaren leading edge of the airfoil to a respective trailing edge, wherein the trailing edge of the pressure-side blade wall - related on the direction of the working medium flowing around the blade, is arranged upstream of the trailing edge of the suction-side blade wall.
  • the known turbine blade has a so-called cut-back trailing edge.
  • the cut-back trailing edge of the airfoil is characterized essentially by the fact that openings are not provided centrally between the suction side wall and pressure side wall at the trailing edge for blowing out coolant, but that these openings are arranged behind edge near the pressure side surface of the airfoil, which along the trailing edge are distributed from a platform side end to a blade tip end.
  • the openings are separated from one another by webs extending transversely to the trailing edge extension, so that the coolant flowing out through them can flow out substantially parallel to the working medium flowing around the blade leaf.
  • the webs arranged between the openings are also known in English as "tear drops".
  • the openings arranged at the trailing edge are preceded by a common cavity in the blade interior.
  • three rows of columnar base - in English also known under the name "Pin-Fins" - arranged, which increase the heat transfer of them passing Cooling air and to increase the pressure loss are provided there.
  • casting core is shown there in perspective in FIG.
  • the space occupied by the casting core remains after production of the cast turbine blade as a cavity, wherein the casting core arranged in the openings are filled with casting material.
  • the casting core represents the negative image of the interior of the turbine blade.
  • the object of the invention is therefore to provide an initially mentioned turbine blade for a gas turbine, which is equipped with a cut-back trailing edge with the lowest possible amount of cooling air efficient and sufficiently coolable, and / or used in the manufacture of a casting core in a casting apparatus can be, which is particularly robust.
  • the invention is based on the finding that the cut-back trailing edge usually produced directly with the casting Also separately from the body, which forms the blade at least fundamentally, can be produced.
  • the invention thus provides to form the trailing edge as a modular cut-back trailing edge, which requires that the trailing edge of the pressure-side blade wall - is arranged upstream of the trailing edge of the suction-side blade wall, based on the direction of the working medium flowing around the blade one insert can be inserted into a slot bounded by the trailing edge of the pressure-side blade wall and the suction-side blade wall and can be flowed out of the blade through a coolant that can flow in the interior of the blade. Consequently, the insert replaces the otherwise cast-on webs.
  • the cast turbine core required cast iron core structurally less complex than a known from the prior art casting core. At least those openings in the casting core are eliminated, which are needed to form the webs at the trailing edge of the turbine blade.
  • the casting core known from the prior art has at this point the smallest cross-section which, moreover, is also perforated due to the openings arranged there. Due to the small cross-section and the perforation of the previous casting core could break particularly easily when handled at this point. By eliminating the previously arranged in the casting core openings this is now much more massive at the point in question, which increases its rigidity.
  • the casting core to be used for producing the turbine blade according to the invention is less prone to breakage, which simplifies its handling and reduces costs.
  • the insert could be made of a superalloy.
  • Another advantage is the comparatively exact production of the insert with lower manufacturing spread, compared with the cast configuration of the cut-back trailing edge.
  • the mass flow of the cooling air flowing out through the trailing edge in the region of the webs is adjusted by a suitable choice of the geometry there and its dimensions. Since this geometry no longer has to lie in the region of the casting, but can be in the region of the insert, the mass flow can be set much more accurately due to the small manufacturing tolerances of the insert.
  • the less production scattering of the insert reduces significantly different mass flows. In this respect can be saved by the use of the use of coolant.
  • the manufacturing process can be simplified with respect to the adjustment of the exiting through the trailing edge cooling air.
  • the insert has two mutually opposite walls, which are connected to one another via webs which are spaced apart and extend in the outflow direction of the coolant.
  • the insert has two mutually opposite walls, which are connected to one another via webs which are spaced apart and extend in the outflow direction of the coolant.
  • the region of a side surface of the pressure-side blade wall and / or suction-side blade wall, against which the insert bears is designed to be rectilinear in cross-section. This makes possible the insertion of the insert in the manufacture of the turbine blade by means of a simple rectilinear insertion movement.
  • the slot and the insert disposed therein each extend from a root portion of the airfoil to a tip portion of the airfoil.
  • the slot and the insert disposed therein each extend from a root portion of the airfoil to a tip portion of the airfoil.
  • the insert is soldered or welded to the pressure-side blade wall and / or suction-side blade wall. This is particularly easy to accomplish and advantageous if the use has two opposing walls. Passage of the cooling air flowing inside the turbine blade through a gap between a wall of the insert and the immediately opposite side surface of the respective blade wall can thus be avoided.
  • the turbine blade is formed as a cast turbine blade in the form of a vane or blade having at least one platform transverse to the airfoil.
  • FIG. 1 the cross-section through the airfoil 12 of a turbine blade 10 according to the invention is shown schematically.
  • the turbine blade 10 may be formed both as a stationary blade of a stationary gas turbine but also as a blade.
  • the generally in the casting process and thus fundamentally integral turbine blade 10 has a foot region not shown for attachment of the turbine blade 10 on a blade carrier or in the case of a blade on a rotor of the gas turbine.
  • a platform 14 from which the aerodynamically curved airfoil 12 extends to a leaf tip which is not further visible due to the sectional view.
  • the aerodynamically curved airfoil 12 essentially comprises a suction-side vane wall 16 and a pressure-side vane wall 18.
  • Both vane walls 16, 18 extend from a common leading edge 20 to a trailing edge region 22 of the airfoil 12.
  • the airfoil 12 is hollow in its interior arranged cavities 24 are divided by itself from the pressure-side blade wall 18 to the suction-side blade wall 16 and extending from the foot to the blade tip region ribs 26.
  • the cavities 24 can be flowed through sequentially, in parallel or in any combination of a coolant, for example cooling air, whereby the coolant flowing in the cavity 24 adjacent to the trailing edge region 22 can be guided through channels 28 to openings 30 which are arranged on the pressure side in the trailing edge region 22.
  • pin fins 32 arranged in rows or in fields can be provided, which bring about turbulence and deflection of the cooling air flowing to the openings 30 should, in order to absorb the heat energy present in the blade walls 16, 18 during operation of the gas turbine and transported away therefrom.
  • the in FIG. 1 schematically illustrated turbine blade 10 to a turbine blade 10 with a so-called. Cut-back trailing edge.
  • the openings 30 arranged in the trailing edge region 22 are distributed uniformly along the trailing edge extension from the platform-side region of the trailing edge to the tip-side region of the trailing edge and are separated from one another by webs.
  • FIG. 2 is the trailing edge region 22 according to FIG. 1 shown in detail, but with the suppression of the inventive use to be provided there.
  • the in FIG. 2 Rear edge region 22 shown is part of a main body of the airfoil 12, which has been produced in one piece in a casting process.
  • suction-side blade wall 16 extends to its rear edge 36, whereas a trailing edge 38 of the pressure-side blade wall 18, based on the direction of the working fluid flowing around the blade 12, upstream of the trailing edge 36 of the suction-side blade wall 16 is arranged.
  • a slot 42 is provided between the trailing edge 38 of the pressure-side blade wall 18 and that side surface 40 of the suction-side blade wall 16, which faces the trailing edge 38 of the pressure-side blade wall 18.
  • the slot 42 extends over the entire height of the airfoil 16, which is detected perpendicular to the plane of the drawing. The height of the airfoil 12 is thus detected between the platform 14 and the tip of the airfoil 12.
  • FIG. 3 Insert shown in cross section 44 is inserted from the outside into the slot 42 and secured there.
  • the insert 44 essentially comprises two walls 46, 48, between which a plurality of webs 50 (see FIG. 4 ) are arranged to the two walls 46, 48 together connect and design the insert 44 as a unit.
  • Channels 52 are thus present between the webs 50, through which the coolant flowing inside the turbine blade 10, for example cooling air, can exit from the turbine blade 10.
  • the channels 52 open as arranged in the surface of the insert 44 openings 30, which in FIG. 1 are shown only schematically.
  • FIG. 5 shows in cross section according to FIG. 2 the trailing edge region 22 of the turbine blade 10 according to the invention, in which the insert 44 is arranged in the slot 42 and secured by soldering or welding.
  • the wall 48 of the insert 44 is connected to the trailing edge 38 of the pressure-side blade wall 18.
  • the wall 46 is connected to the side surface 40 of the suction side vane wall 16. In the soldered or welded areas in each case the respective wall surfaces are in a straight line to each other, whereby the insert 44 is relatively easy to position.
  • the invention provides a turbine blade 10 for a gas turbine, in which the trailing edge region 22 designed in the manner of a cut-back trailing edge is modular.
  • a slot 42 extending from the platform to the blade tip is provided on the pressure side, in which an insert component 44 is arranged, in which the webs 50 typical for a cut-back trailing edge are formed are.
  • the insert 44 thus has disposed between the webs 50 channels 52 which open into openings 30, from which the flowable in the interior of the airfoil 10 coolant from the airfoil 10 can be flowed out.
  • a core further thickened in the trailing edge region for the production of the cast airfoil 12 can be used, whereby its mechanical integrity is improved and this tends less to break during its handling.
  • the amount of cooling air exiting at the trailing edge comparatively accurate be adjusted by means of a non-cast, conventionally made insert 44.
  • the insert 44 has not only arranged in the trailing edge region webs 50.
  • the insert 44 also includes the usual way further inside the turbine blade 10 upstream pin-fins 32, wherein the insert 44 may also form a minor part of the pressure-side blade wall 18, as in FIG. 5 is exemplified by the reference numeral 54.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08016009A 2008-09-11 2008-09-11 Aube de turbine dotée d'un rebord arrière modulaire et graduée Withdrawn EP2163726A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP08016009A EP2163726A1 (fr) 2008-09-11 2008-09-11 Aube de turbine dotée d'un rebord arrière modulaire et graduée
PCT/EP2009/059958 WO2010028913A1 (fr) 2008-09-11 2009-07-31 Aube de turbine à bord de fuite étagé modulaire

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08016009A EP2163726A1 (fr) 2008-09-11 2008-09-11 Aube de turbine dotée d'un rebord arrière modulaire et graduée

Publications (1)

Publication Number Publication Date
EP2163726A1 true EP2163726A1 (fr) 2010-03-17

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP08016009A Withdrawn EP2163726A1 (fr) 2008-09-11 2008-09-11 Aube de turbine dotée d'un rebord arrière modulaire et graduée

Country Status (2)

Country Link
EP (1) EP2163726A1 (fr)
WO (1) WO2010028913A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2907969A1 (fr) * 2014-02-14 2015-08-19 Siemens Aktiengesellschaft Aube de turbine et procédé de fabrication ou de restauration d'une aube de turbine
EP3192970A1 (fr) * 2016-01-15 2017-07-19 General Electric Technology GmbH Aube de turbine à gaz et procédé de fabrication
CN109014056A (zh) * 2018-10-10 2018-12-18 成都航宇超合金技术有限公司 用于铸造涡轮叶片基准转移的定位浇注工装

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104169470B (zh) 2012-03-28 2016-09-28 通用电器技术有限公司 用于从陶瓷部分分离金属部分的方法
EP2781691A1 (fr) 2013-03-19 2014-09-24 Alstom Technology Ltd Procédé de reconditionnement d'une partie de la trajectoire des gaz chauds d'une turbine à gaz

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6551063B1 (en) * 2001-12-20 2003-04-22 General Electric Company Foil formed structure for turbine airfoil trailing edge
WO2003042503A1 (fr) 2001-11-14 2003-05-22 Honeywell International Inc. Aube ou pale de turbine a gaz refroidi interne
EP1847684A1 (fr) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Aube de turbine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003042503A1 (fr) 2001-11-14 2003-05-22 Honeywell International Inc. Aube ou pale de turbine a gaz refroidi interne
US6551063B1 (en) * 2001-12-20 2003-04-22 General Electric Company Foil formed structure for turbine airfoil trailing edge
EP1847684A1 (fr) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Aube de turbine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2907969A1 (fr) * 2014-02-14 2015-08-19 Siemens Aktiengesellschaft Aube de turbine et procédé de fabrication ou de restauration d'une aube de turbine
WO2015120995A1 (fr) 2014-02-14 2015-08-20 Siemens Aktiengesellschaft Aube de turbine et procédé de fabrication ou de rectification d'une aube de turbine
EP3192970A1 (fr) * 2016-01-15 2017-07-19 General Electric Technology GmbH Aube de turbine à gaz et procédé de fabrication
CN107023325A (zh) * 2016-01-15 2017-08-08 通用电器技术有限公司 燃气涡轮叶片及制造方法
US10669858B2 (en) 2016-01-15 2020-06-02 General Electric Technology Gmbh Gas turbine blade and manufacturing method
CN107023325B (zh) * 2016-01-15 2021-03-12 通用电器技术有限公司 燃气涡轮叶片及制造方法
CN109014056A (zh) * 2018-10-10 2018-12-18 成都航宇超合金技术有限公司 用于铸造涡轮叶片基准转移的定位浇注工装

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Publication number Publication date
WO2010028913A1 (fr) 2010-03-18

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