EP2252771A1 - Pale pour turbine à gaz - Google Patents

Pale pour turbine à gaz

Info

Publication number
EP2252771A1
EP2252771A1 EP09716976A EP09716976A EP2252771A1 EP 2252771 A1 EP2252771 A1 EP 2252771A1 EP 09716976 A EP09716976 A EP 09716976A EP 09716976 A EP09716976 A EP 09716976A EP 2252771 A1 EP2252771 A1 EP 2252771A1
Authority
EP
European Patent Office
Prior art keywords
control elements
blade
controls
blade according
cooling medium
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Withdrawn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
EP09716976A
Other languages
German (de)
English (en)
Inventor
Jörg KRÜCKELS
Roland DÜCKERSHOFF
Martin Schnieder
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.)
Ansaldo Energia IP UK Ltd
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 EP2252771A1 publication Critical patent/EP2252771A1/fr
Withdrawn legal-status Critical Current

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
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2250/23—Three-dimensional prismatic
    • 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
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to the field of gas turbines. It relates to a blade for a gas turbine according to the preamble of claim 1.
  • a gaseous cooling medium is used, for example a branched off from the compressor of the gas turbine at a suitable point compressed air, sometimes and / or steam, especially if the gas turbine is part of a combined cycle power plant, or otherwise steam of suitable quality and quantity.
  • This cooling medium is passed through arranged in the blade, often running in serpentine cooling channels, this being done via an open, and / or closed cooling path.
  • Trailing edge arranged is substantially parallel to the trailing edge extending slot-shaped opening is ejected, wherein the cooling medium then over the trailing edge and lying between the opening and trailing edge region of B07 / 140-0 2
  • Blade surface strokes Such cooling of the trailing edge is shown in Fig. 3 of US-A-5,813,835 by the reference numerals 208 and 210.
  • Fig. 1 of the present description the basic geometry of the trailing edge cooling is reproduced in a greatly simplified form.
  • the blade 10 which extends in a longitudinal direction, that is to say in the radial direction with respect to the turbine axis, and ends in a blade tip 12, has a leading edge 11 upstream and a trailing edge 13 downstream. Between the leading edge 11 and the trailing edge 13, the blade with a wing profile forms a pressure side 23 and a suction side 24.
  • a parallel extending exit slot 14 for a cooling medium (in particular cooling air) is provided in front of the trailing edge 13, through which the cooling medium exits to the outside and as a cooling stream 16 passes over the trailing edge 13.
  • the cooling medium is supplied to the outlet slot 14 through a cooling channel 15 in the interior of the blade 10.
  • control elements 17 are distributed in the longitudinal direction, by means of which on the one hand the cross-sectional area of the exit slot 14 is reduced (ie controlled) and on the other hand the cooling medium is distributed over the entire length of the exit slot 14.
  • control elements 17 for the control of the cooling flow 16 and thus also for the efficiency of the gas turbine as a whole is the subject of another document, namely US-A1 -2005/0232770.
  • control elements of different design are proposed in the exit slot, which are intended to further reduce the cross-sectional area of the exit slot which can be achieved by casting, but at the same time contribute to increasing the mechanical stability in the slot area or be turbulent.
  • the invention aims to remedy this situation. It is an object of the invention
  • An embodiment of the invention is characterized in that at least two types of control elements with different cross-sectional contour are provided in the row of control elements, that the one of the at least two types of control elements in the flow direction B07 / 140-0 4 of the cooling medium extending elongated, in particular drop-shaped cross-sectional shape, and that the other of the at least two types of control elements has a substantially circular cross-sectional shape. Laboratory tests have confirmed that such an arrangement has proven itself.
  • control elements in the series can be arranged alternately. But it is also conceivable that a plurality of controls of the other type are arranged in series between two controls of the single type. In particular, between two
  • One type of control elements may be arranged two or three controls of the other type in the series.
  • FIG. 1 in a simplified perspective view of the part of a
  • Figure 2 is a schematic representation of the adverse effects of the known trailing edge cooling.
  • Fig. 3 shows a first embodiment of an arrangement of different, reducing the mass flow B07 / 140-0 5
  • Control elements according to the invention with two control types in a simple alternating arrangement
  • Fig. 4 shows a second embodiment of an arrangement of different, reducing the mass flow
  • Control elements according to the invention with two control types in an alternating arrangement, each according to
  • Fig. 5 shows a third embodiment of an arrangement of different, the mass flow reducing controls according to the invention with two control types in an alternating arrangement, each according to
  • Fig. 6 shows a further embodiment of an arrangement of different, the mass flow reducing controls according to the invention with two control types in a targeted alternating arrangement, wherein the teardrop-shaped controls extend beyond the exit slot addition.
  • FIGS. 3-6 Various embodiments for the throttling of the cooling medium flow for the trailing edge of a gas turbine blade according to the invention are shown in FIGS. 3-6. All embodiments have in common that two special types of control elements (throttle elements) 21 and 22 are used.
  • the control element 21 has a teardrop-shaped edge contour, the
  • Control 22 has a circular edge contour, it should be noted immediately that the two edge contours shown, respectively.
  • Cross-sectional areas are not exclusive.
  • the two control types 21 and 22 are arranged alternately (alternately) in the outlet slot 14.
  • the two control types 21 and 22 are arranged so alternately in the exit slot 14 that repeats the order of three elements.
  • two control elements 22 of the circular design are each provided between two control elements 21 of the drop-shaped design.
  • the two types of control elements 21 and 22 are arranged alternately in the outlet slot 14 in such a way that the sequence repeats after four elements, whereby three control elements 22 each are provided between two control elements 21 of the drop-shaped design 5, the local position of the individual control elements 21, 22 in the flow direction is indicated by an auxiliary line 25.
  • they are arranged such that the largest cross-sectional area of all control elements, regardless of their design, in the flow direction in one Plane lie, as the auxiliary line 25 wants to express, ie, the smallest gap between two controls coincides with the plane of their largest cross-sectional areas, thus avoiding that the flow through the one interstices not from the flow through the adjacent Eisenhoffm e is fluidically disturbed, such as by converging or deflected
  • Fig. 6 a configuration is shown, which differs from the preceding Figure 5.
  • the described controls 21, 22 can also be designed so that they do not necessarily occupy the entire cross-sectional width of the exit slot 14, i. one or more of these control elements 21, 22 have along their head-side cross-sectional area an air gap relative to the one flow-through wall of the outlet slot 14.
  • the exiting cooling medium (16) can therefore not only flow outward around the edge contour of the individual control elements 21, 22, but it can also flow out through the existing open air gap along the head-side cross-sectional area of these control elements 21, 22.
  • different constellations can be provided in the series of controls (21, 22) with regard to the number and their sequence of air gaps to be provided, and this also applies to the individual thickness of the air gap. With these precautions, the task-oriented objective can be supported as needed.
  • this restriction varies between 20% and 90%, depending on the particular conditions to be met with respect to the cooling of the trailing edge of the blade.
  • control e.g., drop-shaped

Landscapes

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

Abstract

Une pale (20) pour turbine à gaz possède, dans la direction longitudinale, un bord avant et un bord arrière (13) entre lesquels la pale (20) s'étend transversalement à la direction longitudinale en formant un côté refoulement et un côté aspiration. La pale est dotée, près du bord arrière (13), d'une fente de sortie (14) qui s'étend dans la direction longitudinale et qui est destinée à la sortie de fluide de refroidissement ; une rangée d'éléments de commande (21, 22) destinés à commander le débit massique de fluide de refroidissement sortant de la fente de sortie (14) est disposée dans la fente de sortie (14), lesdits éléments de commande étant distribués dans la direction longitudinale. Une telle pale permet d'effectuer un refroidissement uniforme du bord arrière, même avec un débit massique de fluide de refroidissement fortement réduit, en prévoyant une suite d'éléments de commande (21, 22) de différentes conformations dans la rangée d’éléments de commande (21, 22).
EP09716976A 2008-03-07 2009-02-17 Pale pour turbine à gaz Withdrawn EP2252771A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH3512008 2008-03-07
PCT/EP2009/051846 WO2009109462A1 (fr) 2008-03-07 2009-02-17 Pale pour turbine à gaz

Publications (1)

Publication Number Publication Date
EP2252771A1 true EP2252771A1 (fr) 2010-11-24

Family

ID=39493694

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09716976A Withdrawn EP2252771A1 (fr) 2008-03-07 2009-02-17 Pale pour turbine à gaz

Country Status (4)

Country Link
US (1) US8182225B2 (fr)
EP (1) EP2252771A1 (fr)
JP (1) JP5436457B2 (fr)
WO (1) WO2009109462A1 (fr)

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US20120315139A1 (en) * 2011-06-10 2012-12-13 General Electric Company Cooling flow control members for turbomachine buckets and method
US8882461B2 (en) * 2011-09-12 2014-11-11 Honeywell International Inc. Gas turbine engines with improved trailing edge cooling arrangements
US9051842B2 (en) 2012-01-05 2015-06-09 General Electric Company System and method for cooling turbine blades
US9175569B2 (en) 2012-03-30 2015-11-03 General Electric Company Turbine airfoil trailing edge cooling slots
US9017026B2 (en) * 2012-04-03 2015-04-28 General Electric Company Turbine airfoil trailing edge cooling slots
US20130302176A1 (en) * 2012-05-08 2013-11-14 Robert Frederick Bergholz, JR. Turbine airfoil trailing edge cooling slot
US9145773B2 (en) * 2012-05-09 2015-09-29 General Electric Company Asymmetrically shaped trailing edge cooling holes
US20130302179A1 (en) * 2012-05-09 2013-11-14 Robert Frederick Bergholz, JR. Turbine airfoil trailing edge cooling hole plug and slot
US10100645B2 (en) * 2012-08-13 2018-10-16 United Technologies Corporation Trailing edge cooling configuration for a gas turbine engine airfoil
EP2832956A1 (fr) * 2013-07-29 2015-02-04 Siemens Aktiengesellschaft Aube de turbine avec corps de refroidissement en forme de profil aérodynamique
US9732617B2 (en) 2013-11-26 2017-08-15 General Electric Company Cooled airfoil trailing edge and method of cooling the airfoil trailing edge
KR101565452B1 (ko) * 2013-12-17 2015-11-04 한국항공우주연구원 가스 터빈 엔진의 에어포일
US10830072B2 (en) 2017-07-24 2020-11-10 General Electric Company Turbomachine airfoil
US11352902B2 (en) * 2020-08-27 2022-06-07 Aytheon Technologies Corporation Cooling arrangement including alternating pedestals for gas turbine engine components
CN114876583B (zh) * 2022-04-18 2024-03-22 杭州汽轮控股有限公司 一种涡轮动叶尾缘的冷却结构

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Also Published As

Publication number Publication date
WO2009109462A1 (fr) 2009-09-11
US8182225B2 (en) 2012-05-22
US20110085915A1 (en) 2011-04-14
JP5436457B2 (ja) 2014-03-05
JP2011513636A (ja) 2011-04-28

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