EP2933435A1 - Aube de turbine et turbine associée - Google Patents

Aube de turbine et turbine associée Download PDF

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Publication number
EP2933435A1
EP2933435A1 EP14164723.0A EP14164723A EP2933435A1 EP 2933435 A1 EP2933435 A1 EP 2933435A1 EP 14164723 A EP14164723 A EP 14164723A EP 2933435 A1 EP2933435 A1 EP 2933435A1
Authority
EP
European Patent Office
Prior art keywords
rib
turbine blade
turbine
rib member
height
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Withdrawn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
EP14164723.0A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Björn Buchholz
Daniela Koch
Marco Schüler
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP14164723.0A priority Critical patent/EP2933435A1/fr
Priority to PCT/EP2015/056399 priority patent/WO2015158514A1/fr
Publication of EP2933435A1 publication Critical patent/EP2933435A1/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Withdrawn legal-status Critical Current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
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the invention relates to a turbine blade with a turbine blade in which a cavity is formed, which is divided by a rib member whose rib height extends from a front wall of the turbine blade to a rear wall of the turbine blade.
  • the invention further relates to a turbine, in particular a gas turbine, with at least one turbine stage comprising a plurality of turbine blades.
  • a turbine blade of this type is equipped with an internally cooled turbine blade in order to withstand even high temperatures prevailing in the turbine, especially in a hot gas turbine, thermally and mechanically.
  • an internally cooled turbine blade has a cavity through which a cooling medium can be passed.
  • a rib member or a plurality of rib elements is arranged.
  • the cavity can also be subdivided into different cooling channels.
  • the turbine blades are often subjected to higher thermal and mechanical loads.
  • the object of the invention is achieved by a turbine blade with a turbine blade in which a cavity is formed, which is divided by a rib member whose rib height extends from a front wall of the turbine blade to a rear wall of the turbine blade, wherein the rib cross section of the rib member is configured in that the stresses caused by thermal differences between the front and rear side walls within the rib element can be compensated by means of an improved deformability of the rib element.
  • this rib element can deform significantly better than previously, so that in particular thermally induced stresses in the turbine blade can be much better absorbed by the present rib element, whereby specifically the front and rear wall of the turbine blade through a The rigidity inherent in the rib element is less stressed.
  • the rib element has a lower rigidity and conversely better suspension properties.
  • an improved deformability can be achieved in a structurally simple manner if the rib element has a rib cross section which is different from a substantially rectangular rib cross section.
  • the turbine blade according to the invention is preferably a turbine blade of a gas turbine and especially of a hot gas turbine, since relevant turbine blades are subject to particularly high thermal loads, so that it is these turbine blades which can be developed particularly advantageously by the invention.
  • the rib cross section is configured such that the rib element has an improved bending capacity transversely to its longitudinal extent.
  • the rib element is at least partially arcuate in the direction of the rib height.
  • An arcuately shaped rib element arranged between the front and rear side wall can deform much better and / or bend much laterally with respect to its rib height radially laterally than a substantially rectangular-shaped rib element can do. Specifically, this can increase the bending ability of the rib member.
  • a sufficiently rigid but nevertheless resilient rib member can be provided when the rib member is curved over the entire rib height.
  • the rib member is continuously curved from the front side wall to the rear side wall or arched.
  • the arcuate rib element in this case preferably has a continuous curvature. That is, the present rib member is preferably continuously curved from the front side wall to the rear side wall.
  • the rib element has a concave longitudinal side surface, it can deform much more favorably in relation to a substantially rectangular rib element or bend in a defined direction.
  • This concave longitudinal side surface extends in the longitudinal direction of the rib member and is clamped between the front and rear side wall.
  • this concave longitudinal side surface faces the rear, tapered turbine blade edge.
  • the fin element can be targeted to deform on a front turbine blade edge.
  • the rib element has a convexly configured longitudinal side surface.
  • the rib element can - with sufficient strength - deform even better or bend in a defined direction when the concave longitudinal side surface opposite longitudinal side surface is convex.
  • This convex longitudinal side surface is preferably facing the front turbine blade edge.
  • the rib element has a variable rib cross section in the direction of the rib height.
  • this variable rib cross section it is possible in a structurally particularly simple way to impart to the present ribbed element a further improved deformability and / or bending capacity.
  • Conventional fin elements of known turbine blades have a substantially rectangular cross-section, whereby these conventional rib elements inherent only significantly lower deformation and / or bending capacity.
  • the rib element is designed to be waisted in the direction of the rib height.
  • this area can be designed less stiff.
  • the rib element has a cross-sectional weakening in the direction of the rib height, which increases in the direction of the central longitudinal axis of the turbine blade leaf. This also makes it possible to increase the deformation and / or bending capacity of the in particular continuously curved rib element.
  • the rib element is designed to be thicker at its transition areas to the front and rear wall than in a region between them, a cross-sectional weakening of the rib element can be realized in a structurally simpler manner.
  • the rib element has the smallest rib thickness in the center in relation to the rib height, the rib element can be designed with particularly good flexural elastic properties, in short flexural elasticity.
  • a relevant center width of the rib element is at least only half as strong as the transition region.
  • the present fin member may be disposed nearly arbitrarily aligned within the cavity of the turbine airfoil. However, a particularly good stress reduction can be achieved on the turbine blade, when the fin element is aligned in the longitudinal extent of the turbine blade.
  • the object of the invention is also achieved by a turbine, in particular a gas turbine, having at least one turbine stage comprising a multiplicity of turbine blades, wherein the at least one turbine stage comprises turbine blades according to one of the preceding features.
  • a turbine equipped with the turbine blades according to the invention can be operated with less maintenance. Furthermore, this increases the running time of the turbine, since the material of the present turbine blades is less heavily loaded.
  • the rib is made with the turbine blade sheet monolith.
  • the turbine blade is one in which at least the turbine bucket blade and its inside rib have been produced by the casting process.
  • the in the Figures 1 and 2 shown turbine blade 1 a hot gas turbine 2 has a turbine blade 3 with a hollow profile 4.
  • the hollow profile 4 encloses a cavity 5 of the turbine blade 1 substantially through a front side wall 6 of the turbine blade 3 and through a rear side wall 7 of the turbine blade 3.
  • the front side wall 6 forms the pressure side 8 and the rear side wall 7 accordingly the suction side 9 of the turbine blade 1 the turbine blade 1 during operation of the hot gas turbine 2 in the flow direction 10 of the hot gas (not shown) is flown. It is understood that by the flow direction 10, the pressure side 8 and thus also the Front side wall 6 is subjected to higher thermal stress than the suction side 9 and thus as the rear side wall. 7
  • a rib member 15 Within the cavity 5 is located to stabilize the hollow section 4 of the preferably cast turbine blade on the one hand and for dividing the hollow section 4 on the other hand, a rib member 15, so that the cavity 5 is divided in this embodiment into two main cooling channels 16 and 17.
  • the rib member 15 extends within the hollow section 4 with its rib length 18 in the longitudinal direction 19 of the turbine blade 3 from a portion 20 of a turbine blade not shown here to an end portion 21 of a turbine blade tip also not shown here.
  • the rib member 15 is further disposed diametrically within the hollow profile 4, so that the ripple member 15 further extends from a turbine blade leading edge 22 to a rear turbine blade trailing edge 23 ( FIG. 2 ).
  • the ripple element 15 further extends with its rib height 25 between the front side wall 6 and the rear side wall 7, wherein the rib element 15 merges into the front side wall 6 in a first transition region 26 and into the rear side wall 7 in a second transition region 27.
  • the rib member 15 in these transition regions 26 and 27 has a greater width 28 than the central width 29 in the middle 30 and at the height of the central longitudinal axis 31 of the Rippelelements 15.
  • the rib member 15 is thinner in the middle 30 designed as at its transition regions 26 and 27.
  • the ripple element 15 there the lowest rib thickness, which is equal to the center width 29.
  • the rib element 15 has a variable rib cross section 35 in the direction 32 of the rib height 25.
  • This new variable rib section 35 is shown in FIG FIG. 1 consistently lined.
  • the rib element 15 or the rib cross section 35 of the rib element 15 alone is configured in such a way that, in particular, it has an improved deformability than has hitherto been the case with conventional rectangular rib cross sections.
  • the conventional rectangular ausgestalte rib cross section is at least partially still shown as a dash-dotted line.
  • the rib element 15 or the rib cross-section 35 of the rib element 15 is configured in such a way that the stresses caused by thermal differences between the front and rear side walls 6, 7 within the rib element 15 can be compensated by means of this improved deformability of the rib element 15.
  • the rib member 15 is designed arcuate in this embodiment, so that the rib member 15 inherent thereby improved suspension properties.
  • the rib element 15 or the rib cross-section 35 is configured in such a way that the rib element 15 has an improved bending capacity transversely to its longitudinal extent 36, that is to say transversely to its rib length 18.
  • the rib member 15 may flex laterally in the direction 37 toward the turbine bucket blade leading edge 22 when forces acting on the rib member 15 in the direction 32 of the rib height 25.
  • the rib element 15 or its rib cross-section 35 is configured in such a way, the rib element 15 can deflect in the transverse direction 37 by compressive forces acting in the direction 32 of the rib height 25, in order to avoid stress peaks within the turbine blade 1 caused thereby.
  • a conventional rectangular designed rib element (see dash-dotted line), however, would only be compressed, which would result in adverse voltage increases not only in the rectangular rib element itself but also in the front and rear walls 6 and 7.
  • the rib element 15 is arranged curved between the front side wall 6 and the rear side wall 7 such that a concave longitudinal side surface 38 faces the turbine blade edge trailing edge 23.
  • This concave longitudinal surface side 38 is designed to be continuously curved from the front side wall 6 to the rear side wall 7.
  • a convexly shaped longitudinal surface side 39 of the rib element 15 faces the turbine blade leaf leading edge 22. This assists that the rib element 15 can always bend only in the direction of the turbine blade leaf leading edge 22 when 25 forces act on the rib element 15 in the direction 32 of the rib height.
  • the convex longitudinal surface side 39 is designed to be continuously curved between the transition regions 26 and 27.
  • rib element 40 in addition to the rib element 15 according to the invention in the area of the turbine blade trailing edge, another rib element 40 is provided whose shape, however, does not matter for the present invention because of the small rib height (not shown here).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14164723.0A 2014-04-15 2014-04-15 Aube de turbine et turbine associée Withdrawn EP2933435A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14164723.0A EP2933435A1 (fr) 2014-04-15 2014-04-15 Aube de turbine et turbine associée
PCT/EP2015/056399 WO2015158514A1 (fr) 2014-04-15 2015-03-25 Aube de turbine et turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14164723.0A EP2933435A1 (fr) 2014-04-15 2014-04-15 Aube de turbine et turbine associée

Publications (1)

Publication Number Publication Date
EP2933435A1 true EP2933435A1 (fr) 2015-10-21

Family

ID=50513702

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14164723.0A Withdrawn EP2933435A1 (fr) 2014-04-15 2014-04-15 Aube de turbine et turbine associée

Country Status (2)

Country Link
EP (1) EP2933435A1 (fr)
WO (1) WO2015158514A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170328220A1 (en) * 2016-05-12 2017-11-16 General Electric Company Internal rib with defined concave surface curvature for airfoil
US12196106B2 (en) 2022-11-10 2025-01-14 Rolls-Royce Plc Tie for a component

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109057872B (zh) * 2018-08-01 2021-01-05 常州金坛环保设备有限公司 一种汽轮机叶片
CN110985133A (zh) * 2019-11-18 2020-04-10 南京航空航天大学 一种用于流动换热实验的涡轮叶片带肋内冷通道

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4257734A (en) * 1978-03-22 1981-03-24 Rolls-Royce Limited Guide vanes for gas turbine engines
EP1630353A2 (fr) * 2004-08-25 2006-03-01 Rolls-Royce Plc Aube de turbine à gaz à refroidissement interne
EP1944467A2 (fr) * 2007-01-11 2008-07-16 United Technologies Corporation Flux d' écoulement de circuit de refroidissement pour une section d' aube de turbine
WO2013139926A1 (fr) * 2012-03-22 2013-09-26 Alstom Technology Ltd Aube de turbine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4257734A (en) * 1978-03-22 1981-03-24 Rolls-Royce Limited Guide vanes for gas turbine engines
EP1630353A2 (fr) * 2004-08-25 2006-03-01 Rolls-Royce Plc Aube de turbine à gaz à refroidissement interne
EP1944467A2 (fr) * 2007-01-11 2008-07-16 United Technologies Corporation Flux d' écoulement de circuit de refroidissement pour une section d' aube de turbine
WO2013139926A1 (fr) * 2012-03-22 2013-09-26 Alstom Technology Ltd Aube de turbine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170328220A1 (en) * 2016-05-12 2017-11-16 General Electric Company Internal rib with defined concave surface curvature for airfoil
CN107366554A (zh) * 2016-05-12 2017-11-21 通用电气公司 具有用于翼型件的限定凹面曲率的内部肋
US10053990B2 (en) * 2016-05-12 2018-08-21 General Electric Company Internal rib with defined concave surface curvature for airfoil
US12196106B2 (en) 2022-11-10 2025-01-14 Rolls-Royce Plc Tie for a component

Also Published As

Publication number Publication date
WO2015158514A1 (fr) 2015-10-22

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