EP1219781B1 - Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine - Google Patents

Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine Download PDF

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Publication number
EP1219781B1
EP1219781B1 EP01128807A EP01128807A EP1219781B1 EP 1219781 B1 EP1219781 B1 EP 1219781B1 EP 01128807 A EP01128807 A EP 01128807A EP 01128807 A EP01128807 A EP 01128807A EP 1219781 B1 EP1219781 B1 EP 1219781B1
Authority
EP
European Patent Office
Prior art keywords
platform
cooling
blade
turbine
passage
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
EP01128807A
Other languages
German (de)
English (en)
Other versions
EP1219781A2 (fr
EP1219781A3 (fr
Inventor
Alexander Dr. Beeck
Stefan Dr. Florjancic
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 EP1219781A2 publication Critical patent/EP1219781A2/fr
Publication of EP1219781A3 publication Critical patent/EP1219781A3/fr
Application granted granted Critical
Publication of EP1219781B1 publication Critical patent/EP1219781B1/fr
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
    • F01D5/14—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
    • 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
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F05B2240/801—Platforms for stationary or moving blades 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • the invention relates to an apparatus and a method for cooling a platform of a turbine blade, which provides a blade root, an airfoil with an arrival and trailing edge and a blade tip with a platform and which is at least partially penetrated radially by at least one cooling channel, with at least one, connected via an outlet opening on the platform outlet channel is connected.
  • Cooling problems of the aforementioned type occur in particular in turbine blades, which are used in gas turbine plants.
  • the turbine blades are flowed around by the hot gases generated within the combustion chamber.
  • the aspect of targeted cooling of gas turbine blades plays a major role in the design and layout of such systems.
  • part of the pre-compressed air within the compressor stage for cooling purposes is specifically discharged for cooling and thus removed from the further combustion process for cooling. Rather, the cooling air passes through cooling duct systems, which are provided both in rotating and stationary system components, in the area of the turbine stages to cool the there, the hot gases directly exposed plant components.
  • Blades on radial cooling passages through which the cooling air fed from the side of the rotor assembly is guided longitudinally to the turbine blades, which exits through respectively provided on the blade surface cooling air openings and mixes with the hot gases.
  • turbine blades have platforms or so-called shrouds on their side remote from the rotor assembly to minimize leakage currents that may form between the turbine blade tips and fixed equipment components.
  • platforms and shrouds help to effectively damp vibrations that form along the turbine blades during operation of the gas turbine.
  • US Pat. No. 5,482,435 describes a cooling channel system within a platform through which cooling air is passed and thus effectively contributes to the cooling of the platform.
  • the cooling air passes through a centrally oriented radially to the turbine blade cooling channel in the region of the platform in which the cooling air passes through two sub-channels to the outside.
  • the partial cooling channels provided in the platform extend in such a way that the cooling air emerging from the platform is oriented almost perpendicular to the main flow direction of the hot gases flowing through the gas turbine. This, however, on the one hand causes the flow behavior of the main flow is significantly irritated, whereby the aerodynamic efficiency is permanently impaired. On the other hand, the cooling air emerging from the platform can not contribute to the energy gain or improved energy conversion within the gas turbine.
  • the invention has for its object to provide an apparatus and a method for cooling a platform of a turbine blade according to the preamble of claim 1 such that on the one hand effective cooling of the platform is ensured, on the other hand, however, is ensured that the main flow, which rests directly on the turbine blade, as little as possible is impaired so as not to degrade the aerodynamic conditions within the turbomachine. Rather, it should be achieved that in addition to the above effective cooling effect, an additional energy gain can be achieved by the exit of the cooling air from the platform.
  • claim 1 describes a device according to the invention.
  • the subject matter of claim 7 is a method according to the invention.
  • the concept of the invention advantageously further features are the subject of the dependent claims and the entire description in particular with reference to the exemplary embodiments.
  • a device for cooling a platform of a turbine blade which provides a blade root, an airfoil with an arrival and trailing edge, and a blade tip with a platform and which is at least partially penetrated radially by at least one cooling channel, with at least one, via a Outlet opening is connected to the platform emerging outlet channel, further developed in that the outlet channel adjacent to the outlet opening has a channel longitudinal direction which extends in projection along the turbine blade largely coparallel to the flow direction of the outlet directly overflowing, local flow field of a relatively flowing past the turbine blade mass flow.
  • the cooling device according to the invention is applicable to all turbine blades, which are provided with a platform.
  • the advantages associated with the measure according to the invention are explained in more detail below using the example of the turbine guide vane within a gas turbine plant.
  • the cooling device according to the invention also on platforms of stationary vanes.
  • the inventive measure is not limited to the use of turbine blades within gas turbine stages of gas turbine plants, but can be used in all turbomachinery in which appropriate Cooling problems occur, for example within compressors or similar turbomachines.
  • the inventive arrangement of the outlet channel within the platform through which cooling air exits through an outlet opening is according to the invention oriented such that the cooling air that flows out of the platform preferably has the same flow direction, with the main flow of hot gases, the turbine blade and thus the The platform itself flows around.
  • the cooling channel preferably runs slightly inclined to the platform top side.
  • the outlet opening may be attached to the downstream end edge of the platform, so that the cooling air flowing out of the platform is oriented co-parallel to the hot gases flowing around the platform.
  • the outlet opening of the cooling channel on the platform is preferably downstream of the leading edge of the turbine blade, so that it is ensured that the longest possible cooling channel section extends within the platform, so that the most effective cooling effect can be achieved.
  • Cooling provisions within the platform which in the case of turbine blades are subject to high centrifugal forces due to their radial spacing from the axis of rotation, play an important role in positively influencing the creep behavior of the blade material in the region of the platform, i. Material distortions or deformations by softening of the material with simultaneous action of high centrifugal forces are reduced or eliminated by effective cooling measures. Due to the cooling measure according to the invention within the platform material creep can be significantly reduced.
  • the main advantage associated with the inventive cooling channel system within the platform is the additional energy gain associated with the targeted co-parallel flow exit of the cooling air relative to the turbine blade flowing around mainstream, can be achieved.
  • the cooling air flowing out of the cooling channel oriented according to the invention through the outlet opening on the platform contributes to a measurable energy gain, which results from the interplay of an additional impulse contribution to the drive of the turbine blade and a comparatively negligible irritation or disturbance Main flow of the turbine blade flows around the hot gases.
  • a plurality of correspondingly oriented cooling channels are incorporated within a platform, whereby the advantageous effects described above with regard to cooling effect and additional energy contribution can be increased. Further details regarding possible exemplary embodiments can be taken in detail from the following exemplary embodiments.
  • a multiplicity of techniques known per se are suitable for introducing the cooling channel or a multiplicity of appropriately oriented cooling channels into the platform.
  • Particularly suitable for this purpose are EDM (Electro-Discharge Machining) or conventional drilling techniques using laser beam, electrochemical methods and water jet techniques.
  • FIG. 1 shows a plan view of an axial arrangement consisting of a row of guide blades 1 and a blade row 2 arranged downstream in the direction of flow.
  • the platforms 3 of a vane 4 and a rotor blade 5 can be seen, with the vane 4 or blade 5 extends perpendicularly away from the viewer along the plane of the drawing.
  • the inclination of the flow direction with respect to the axial direction immediately downstream of a turbine blade row is essentially due to the inclination of the turbine blade blades relative to the main flow and the peripheral speed.
  • the platforms 3 are cooling channels 7, preferably arranged in the region of the downstream end edge 8 of the platforms 3 such that cooling air escapes parallel to the main flow 6 from the cooling channels 7.
  • the longitudinal axes of the cooling channels 7 are arranged parallel to the turbine blade in the region immediately upstream of the outflow edge 9.
  • FIG 2 the upper part of a longitudinal section through a turbine blade is shown, which is for example designed as a blade 5 and in its upper Area provides a platform 3.
  • the blade 5 has a radially extending main cooling channel 10, in which cooling air from the side of the blade root, not shown, enters the region of the platform 3.
  • the main cooling channel 10 unilaterally open a plurality of cooling channels 11, which extend obliquely to the platform top 12 and each provide an outlet opening 13 at this. Cooling air, which exits through the outlet channels 11 through the respective outlet opening 13 on the platform top 3, is slightly inclined to the platform top 12, however, directed in the flow direction of the main flow 6.
  • Further cooling channels 14 open via corresponding further outlet openings on the platform top and are supplied via suitable provided additional cooling air channels 15 with cooling air.
  • the platform 3 of the rotor blade 5 shown in FIG. 2 provides a typically formed labyrinth seal 16 under which a cooling channel volume 17 with a correspondingly downstream outlet 18 is provided directly.
  • FIG. 3 shows a plan view of a platform 3, under which, extending in the longitudinal direction, a moving blade 5 is provided.
  • the rotor blade 5 has various hollow channels extending longitudinally of the turbine blade, from which cooling air flows out of the hollow channel 10 in the direction of the platform.
  • a cooling air system connects, through which the individual cooling channels 13 and 14 is supplied with appropriate cooling air.
  • the cooling air flows along the arrow directions indicated in the individual channels and exits at the corresponding outlet openings 13, 14 on the upper side 12 of the platform 3.

Claims (7)

  1. Dispositif pour refroidir une plate-forme (3) d'une aube de turbine, qui présente une base d'aube, une lame d'aube avec une arête d'attaque et une arête de fuite, ainsi qu'une pointe d'aube avec une plate-forme (3), et qui est au moins en partie traversée radialement par au moins un canal de refroidissement qui est connecté à au moins un canal de sortie sortant par une ouverture de sortie au niveau de la plate-forme, caractérisé en ce que le canal de sortie (7, 11) présente, en position adjacente à l'ouverture de sortie (13), une orientation longitudinale de canal qui s'étend en projection le long de l'aube de la turbine essentiellement parallèlement à la direction d'écoulement d'un champ d'écoulement (6) local, débordant directement par-dessus l'ouverture de sortie, d'un flux massique passant relativement devant l'aube de turbine, et en ce que la plate-forme (3) présente un côté supérieur de plate-forme (12) opposé radialement à la lame d'aube de turbine, sur lequel est prévue l'ouverture de sortie (13).
  2. Dispositif selon la revendication 1, caractérisé en ce que le canal de sortie (7, 11) présente, en position adjacente à l'ouverture de sortie (13), une orientation longitudinale de canal qui s'étend en projection le long de l'aube de turbine essentiellement parallèlement à la coupe axiale de la lame d'aube de turbine dans la région directement en amont de l'arête de fuite.
  3. Dispositif selon la revendication 1 ou 2, caractérisé en ce qu'un fluide de refroidissement, de préférence de l'air de refroidissement, peut s'écouler à travers le canal de sortie (7, 11), et quitte l'ouverture de sortie (13) pratiquement dans la direction de l'écoulement vers le champ d'écoulement local (6).
  4. Dispositif selon l'une quelconque des revendications 1 à 3, caractérisé en ce que l'aube de turbine est intégrée dans une turbomachine, de préférence dans une turbine à gaz, à travers laquelle le flux massique est dirigé axialement.
  5. Dispositif selon l'une quelconque des revendications 1 à 4, caractérisé en ce que l'ouverture de sortie (13) est disposée à proximité de l'extrémité de la plate-forme (3) opposée à l'écoulement.
  6. Dispositif selon l'une quelconque des revendications 1 à 5, caractérisé en ce que l'aube de turbine est une aube directrice, de préférence une aube mobile à l'intérieur d'une turbine à gaz.
  7. Procédé de refroidissement d'une plate-forme d'une aube de turbine, qui présente une base d'aube, une lame d'aube avec une arête d'attaque et une arête de fuite, ainsi qu'une pointe d'aube avec une plate-forme, et qui est au moins en partie traversée radialement par au moins un canal de refroidissement qui est connecté à au moins un canal de sortie sortant par une ouverture de sortie au niveau de la plate-forme, caractérisé en ce que la plate-forme (3) présente un côté supérieur de plate-forme (12) opposé radialement à la lame d'aube de turbine, sur lequel est prévue l'ouverture de sortie (13), en ce qu'un fluide de refroidissement, de préférence de l'air de refroidissement, est guidé à travers le canal de refroidissement et le canal de sortie, et sort de la plate-forme, de telle sorte que le fluide de refroidissement quitte la plate-forme avec un écoulement pratiquement parallèlement dans la direction d'un courant massique s'écoulant autour de l'aube de turbine.
EP01128807A 2000-12-22 2001-12-04 Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine Expired - Lifetime EP1219781B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10064265A DE10064265A1 (de) 2000-12-22 2000-12-22 Vorrichtung und Verfahren zur Kühlung einer Plattform einer Turbinenschaufel
DE10064265 2000-12-22

Publications (3)

Publication Number Publication Date
EP1219781A2 EP1219781A2 (fr) 2002-07-03
EP1219781A3 EP1219781A3 (fr) 2004-01-21
EP1219781B1 true EP1219781B1 (fr) 2007-05-02

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EP01128807A Expired - Lifetime EP1219781B1 (fr) 2000-12-22 2001-12-04 Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine

Country Status (3)

Country Link
US (1) US6641360B2 (fr)
EP (1) EP1219781B1 (fr)
DE (2) DE10064265A1 (fr)

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Also Published As

Publication number Publication date
US20020098078A1 (en) 2002-07-25
US6641360B2 (en) 2003-11-04
DE50112433D1 (de) 2007-06-14
DE10064265A1 (de) 2002-07-04
EP1219781A2 (fr) 2002-07-03
EP1219781A3 (fr) 2004-01-21

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