WO2015158514A1 - Aube de turbine et turbine - Google Patents

Aube de turbine et turbine Download PDF

Info

Publication number
WO2015158514A1
WO2015158514A1 PCT/EP2015/056399 EP2015056399W WO2015158514A1 WO 2015158514 A1 WO2015158514 A1 WO 2015158514A1 EP 2015056399 W EP2015056399 W EP 2015056399W WO 2015158514 A1 WO2015158514 A1 WO 2015158514A1
Authority
WO
WIPO (PCT)
Prior art keywords
rib
turbine blade
turbine
height
fin
Prior art date
Application number
PCT/EP2015/056399
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Björn Buchholz
Daniela Koch
Marco Schüler
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2015158514A1 publication Critical patent/WO2015158514A1/fr

Links

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 ⁇ nenschaufelblatt, in which a cavity is formed, which is divided by a rib member whose Rip ⁇ pen altar extends from a front side wall of the turbine blade to a rear side wall of the turbine blade.
  • the invention further relates to a turbine insbeson ⁇ particular a gas turbine, with at least one turbine stage comprehensively a plurality of turbine blades.
  • a turbine blade for a flow rotary machine with a cavity ausbil ⁇ forming airfoil in which the pressure side wall and the suction side wall are interconnected by an intermediate wall, wherein the intermediate wall in a Anschlußbe ⁇ rich to the pressure and / or suction side wall at least from section ⁇ has a perforation in order to increase the elasticity of the intermediate wall in the connection area.
  • the partition may be cumulatively U-shaped to enhance the effect.
  • a blade for gas turbine engines which has a hollow blade ⁇ body, are within which inserts removably inserted to go ⁇ visually divide the cavity of the blade body a more effective cooling.
  • One of the insert parts has a curved plate which extends between a front side and a rear side of the blade body ⁇ . By means of this curved plate, the blade interior is divided into a front and a rear blade part.
  • EP 1 944 467 A2 shows a turbine guide vane of a gas turbine engine.
  • the turbine vane has a flow profile which forms a front hollow space and a front edge cavity, wherein the front cavity and the front edge cavity are separated by a rib.
  • a plurality of openings is provided, through which cooling air from the front cavity to the front edge Cavity can flow to cool the turbine blade advantageously ⁇ .
  • EP 1 630 353 A2 teaches an internally cooled gas turbine blade with a supporting profile wing.
  • the Tragpro ⁇ fil wing consists of an outer wall, which forms pressure and suction surfaces, wherein the outer wall is supported by an inner ⁇ structure, and wherein parts of the inner structure partially carry a constricted cross-section, in order to heat input into the inner structure to reduce .
  • the object of the invention to further develop generic turbine shop ⁇ feln such that at least the above-mentioned disadvantages overcome and critical stress states can be avoided even better.
  • 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 Turbi ⁇ nenschaufelblatts, wherein the rib cross section of the rib member so is configured such that the Rippenele- ment at least partly bogenför ⁇ mig is configured in the direction of the rib height, so that the induced thermal differentiation ⁇ zen between the front and rear side wall within the fin member voltages by means of an improved deformability of the fin member are kompensier- bar, wherein the rib member has a cross-sectional weakening in the direction of the fin height, which increases in the direction of the central longitudinal axis of the turbine blade, in order to increase the deformation and / or bending capacity of the rib member.
  • this rib element can deform significantly better than previously, so that in particular thermally conditional stresses in the turbine blade can be much better absorbed by the front ⁇ lying rib element, whereby in particular the front and rear side wall of the turbine blade are less loaded by an inherent stiffness of the rib member.
  • the rib member has a ge ⁇ ringere rigidity and better in reverse 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 deformation and / or bending ability is significantly improved, since the rib member in the direction of the rib height has a cross-sectional weakening, which increases in the direction of the central longitudinal axis of the turbine blade. Also thereby the deformation and / or Bie ⁇ ge réelle of particular continuously curved fin member can be increased.
  • the inventive turbine blade is preferably a turbine blade of a gas turbine and spe ⁇ essential a hot gas turbine, since this effect turbine acting ⁇ feln are thermally most heavily loaded, so that this turbine blades may just be developed particularly advantageously by the invention.
  • the rib cross-section of the ⁇ art is configured such that the rib member has transversely to its longitudinal extent an improved bendability is.
  • the drawbacks described at the outset can be overcome in a structurally simple manner.
  • the rib element is designed in the direction of the fin height at least partially arcuately from ⁇ is.
  • 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. Especially as a result, the bending ability of the fin element can be increased.
  • 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.
  • an associated center width of the rib element is at least only half as strong as the transition region.
  • a sufficiently rigid, yet resilient ribs well ⁇ element can be provided when the rib member is configured curved over the entire rib height.
  • the rib element is continuously curved from the pre ⁇ side wall to the rear side wall or bow ⁇ shaped.
  • the arcuate rib element in this case preferably has a continuous curvature. That is, the present Rippenele ⁇ ment is from the front wall to the rear wall be ⁇ vorzugt continuously curved.
  • the rib element has a concavely configured L Lucasssei ⁇ ten Design on, it can deform substantially more favorable with respect to a substantially rectangular-shaped fin member or deflect in a defined direction.
  • This concave longitudinal side surface extends in the longitudinal direction of the rib ⁇ element and is clamped between the front and rear side wall.
  • this concave longitudinal side surface of the rear, tapered turbine blade edge edge is ⁇ supplied.
  • 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 - deformed 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.
  • a clearly defined bending direction can be specified. It is advantageous if that the rib element has in direction of rib height a variable rib cross-section ⁇ .
  • 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 interpreted less stiff.
  • a cross-sectional weakening of the rib member can be realized structurally easier.
  • the present rib element can be arranged almost arbitrarily aligned within the cavity of the turbine blade ⁇ blade. 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 ⁇ sondere a gas turbine, with at least one turbine stage comprising a plurality of turbine blades, wherein the at least one turbine stage turbine blades comprises according to any 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 runtime 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 blade ⁇ and its inner rib arranged in the casting method has been produced.
  • Figure 1 schematically illustrates a cross-sectional view of a Turbi ⁇ nenschaufelblatts a turbine blade of a hot gas turbine; and
  • FIG. 2 schematically shows a partially sectioned plan view of the turbine blade blade from FIG. 1.
  • the turbine blade 1 of a hot gas turbine 2 shown in FIGS. 1 and 2 has a turbine blade 3 with a hollow profile 4.
  • the hollow section 4 in this case encloses a cavity 5 of the turbine blade 1 essentially constituted by a front side wall 6 of the turbine blade 3 as well as by a rear wall 7 of the turbine blade 3.
  • the front side wall 6 in this case forms the pressure side 8 and the rear side wall 7, accordingly, the suction side 9 of the turbine blade 1 ,
  • the pressure side 8 and thus the front side wall 6 is thermally more stressed 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 Turbinenschau ⁇ fel one hand, and for dividing the hollow profile walls 4 ⁇ hand, a rib member 15, so that the cavity is divided into the 5 ⁇ sem embodiment into two main cooling channels. 16 and 17
  • the fin member 15 a extends inside the hollow profile 4 with its rib length 18 in the longitudinal direction 19 of the turbine blade 3 of a portion 20 of a non-ge here ⁇ showed turbine blade up to an end portion 21 here also not shown turbine blade tip.
  • the rib member 15 is further arranged diametrically within the hollow profile 4, so that the ripple member 15 ver ⁇ beyond running from a turbine blade leading edge 22 to a rear turbine blade trailing edge 23 ver ( Figure 2).
  • the cogging element 15 further extends with its rib height 25 between the front wall 6 and the rear ⁇ side wall 7, wherein the rib member 15 passes into a first transition area 26 in the front wall 6 and in a second transition region 27 in the rear side wall. 7
  • the rib element 15 has 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 ripple element 15.
  • the Rip ⁇ penelement 15 is designed thinner in the middle 30 than at its transition regions 26 and 27.
  • the ripple element 15 has the lowest rib thickness there, 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.
  • the rib element 15 or the rib cross-section 35 of the rib element 15 alone is designed in such a way that it has, in particular, an improved deformability than has hitherto been the case with conventional rectangular-shaped rib cross-sections.
  • the conventional rectangularly configured rib cross-section is at least partially shown as a dot-dash line.
  • the fin member 15 and the rib cross is ⁇ section 35 of the fin member 15 is now in such a way that the are compensated by thermal differences between the front and rear side wall 6, 7 caused within the fin member 15 voltages by means of this improved deformability of the fin member 15th
  • the rib member 15 is designed arcuate in this embodiment, so that the rib member 15 inherent here ⁇ by improved suspension properties.
  • the rib member 15 or the cross-ribs is ⁇ section 35 configured such that the fin member 15 has transversely to its longitudinal extent 36, that is transverse to its length ribs 18 provide an improved bendability.
  • 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 that 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 compressed, which would have adverse voltage increases not only in the rechtecki ⁇ gene rib element itself but also in the front and rear walls 6 and 7.
  • the rib element 15 is arranged in such a curved manner between the front side wall 6 and the rear side wall 7 that a concave longitudinal side surface 38 of the turbine blade edge trailing edge 23 faces.
  • This concave longitudinal surface side 38 is configured 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 acting in the direction 32 of the rib height 25 forces on the rib member 15.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une aube de turbine (1) comprenant une pale (3) dans laquelle est ménagée une cavité (5) qui est divisée par une nervure (15) dont la hauteur (25) s'étend d'une paroi latérale avant (6) de la pale à une paroi latérale arrière (7) de ladite pale (3), la section transversale (35) de la nervure (15) étant telle que la nervure (15) possède une configuration au moins partiellement incurvée dans le sens (32) de la hauteur (25) de sorte que les contraintes générées par des différences thermiques entre les parois latérales avant et arrière (6, 7) dans la nervure (15) peuvent être compensées par une capacité de déformation améliorée de la nervure (15). La nervure (15) présente dans le sens (32) de sa hauteur (25) une résistance moindre en coupe transversale qui augmente en direction de l'axe longitudinal médian (31) de la pale (3) afin d'augmenter la capacité de déformation et/ou de flexion de la nervure.
PCT/EP2015/056399 2014-04-15 2015-03-25 Aube de turbine et turbine WO2015158514A1 (fr)

Applications Claiming Priority (2)

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

Publications (1)

Publication Number Publication Date
WO2015158514A1 true WO2015158514A1 (fr) 2015-10-22

Family

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Family Applications (1)

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

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109057872A (zh) * 2018-08-01 2018-12-21 常州金坛环保设备有限公司 一种汽轮机叶片

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10053990B2 (en) * 2016-05-12 2018-08-21 General Electric Company Internal rib with defined concave surface curvature for airfoil

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 (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109057872A (zh) * 2018-08-01 2018-12-21 常州金坛环保设备有限公司 一种汽轮机叶片
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

Also Published As

Publication number Publication date
EP2933435A1 (fr) 2015-10-21

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