EP3199759A1 - Aube de turbine pour une turbomachine thermique - Google Patents

Aube de turbine pour une turbomachine thermique Download PDF

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Publication number
EP3199759A1
EP3199759A1 EP16153374.0A EP16153374A EP3199759A1 EP 3199759 A1 EP3199759 A1 EP 3199759A1 EP 16153374 A EP16153374 A EP 16153374A EP 3199759 A1 EP3199759 A1 EP 3199759A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
cooling
airfoil
cooling channel
cover element
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Withdrawn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
EP16153374.0A
Other languages
German (de)
English (en)
Inventor
York Mick
Andreas Heselhaus
Robert Kunte
Uwe Paul
Bärbel Pöhler
Marcel SCHLÖSSER
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 EP16153374.0A priority Critical patent/EP3199759A1/fr
Publication of EP3199759A1 publication Critical patent/EP3199759A1/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Withdrawn legal-status Critical Current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
    • 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
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet

Definitions

  • the invention relates to a turbine blade for a thermal turbomachine, comprising an airfoil which can be flowed around by a hot gas and which has a suction-side sidewall and a pressure-side sidewall, the main flow direction of the hot gas being viewed from a common leading edge to a trailing edge and along a direction to the main flow direction Substantially perpendicular longitudinal axis extending from a first end of the airfoil to this opposite the second end of the airfoil, wherein in the airfoil interior at least one cooling channel is provided, which is bounded by a plurality of inner surfaces, of which at least one of the first side wall inner surface at least partially the inside of one of the two Is side walls, and having an access through which a cooling medium can be flowed from outside the turbine blade in the cooling passage, wherein the turbine blade at the entrance with a cover member mitinde st comprises an opening.
  • a corresponding turbine blade is for example from the WO 2009/153108 A2 known.
  • a throttle plate is provided at the entrance of the cooling air duct, which reduces the amount of cooling medium flowing into the interior of the turbine blade.
  • two holes are provided whose position appears optional.
  • the object of the invention is therefore to provide a turbine blade whose cover plate enables improved cooling.
  • the covering element comprises means which impart a twist to the cooling medium which can be flowed into the cooling channel.
  • the invention is based on the finding that by introducing an additional velocity component in the circumferential direction, a heat transfer increase based on a purely parralel to the longitudinal axis of the cooling channel flowing cooling medium is made possible, so that the cooling medium can efficiently cool the wall surrounding the cooling channel. This is referred to below as cyclone cooling.
  • the metal sheets which are generally formed as cover elements at an access of the cooling channel, have means for generating a twist of the cooling medium which can flow in the cooling channel.
  • the cover element comprises a swirl generator, preferably in the form of a drum, as a means for generating a swirl, in which - based on a central axis of the swirl generator - at least one, preferably a plurality of tangentially oriented Einstrompassagen along the circumference of the swirl generator are provided distributed. Due to the tangentially oriented Einstrompassagen then flows from the outside (or from inside) into the swirl generator a cooling medium (or off), which cause a helical flow in the interior (or outside) of the swirl generator. The helical flow then flows in concentric circles around the neutral chord of the cooling channel, so that in said
  • Cooling channel which adjoins the swirl generator, which can spread the swirling flow with an additional Geschindmaschineskomponente in the circumferential direction for heat transfer increase.
  • the cover element can have, as a means for generating the swirl, guide elements which impress a flow component oriented in the circumferential direction to the cooling medium flowing through the openings. This also makes it possible to ensure a swirling flow inside the cooling channel.
  • the cover may extend partially into the cooling channel.
  • the cover member may preferably comprise a tubular portion in which impingement cooling holes are provided.
  • the wall surrounding the cooling duct can be cooled down upstream and can be cooled downstream by the swirling cooling, which can also be referred to as cyclone cooling.
  • the turbine blade may be formed both as a guide blade and as a blade.
  • the cover is attached to an underside of the usually fir-tree or dovetail-shaped blade root.
  • FIG. 1 shows a perspective view of a longitudinal section through a turbine blade 10.
  • the turbine blade 10 comprises along a virtual longitudinal axis 12 successively a mounting portion 18, a platform 16 and an aerodynamically curved airfoil 14.
  • the airfoil 14 includes two side walls 20, 22, of which the first pressure side (20) and the second suction side (22) is arranged.
  • the side walls 20, 22 extend from a common in FIG. 1 Not shown leading edge to a common trailing edge 24.
  • the blade 14 is - as the position of the cutting plane makes it clear - hollow.
  • This cavity is also referred to as cooling channel 28 and has at least one access 34.
  • the access 34 is located at the one of the two ends 32 of the airfoil 14th
  • FIG. 1 Of the two ends of the airfoil, there is only one end in FIG. 1 shown.
  • the blade blade 14 When the turbine blade 10 is configured as a guide blade, as shown, the blade blade 14 usually has a transversely extending platform 16 at both of its ends 32. For blades with so-called shrouds this is also true. Solely freestanding turbine blades have a platform only at one of their two blade ends, wherein in a turbine free-standing vane rather untypical and freestanding rather blades are common. Common are freestanding blades. Relative to the installation position in an example axially through-flowable gas turbine is usually spoken of an inner platform and an outer platform, based on the machine axis of the gas turbine. Then also the longitudinal axis 12 is perpendicular to the machine axis. In the embodiment shown here, the platform 16 is arranged radially outward.
  • cover element 36 attached to the airfoil 14, it is only partially closed, since a plurality of openings 38 are provided in the cover element 36.
  • the cover member 36 is secured to the remainder of the turbine bucket, the cast bucket body, in a conventional manner, such as by a welded joint.
  • the hot gas of the gas turbine flows from the leading edge to the trailing edge 24.
  • the airfoil 14 is internally cooled.
  • the turbine blade 10 is supplied via the openings 38 cooling air, which along the cooling channel 28, the side walls 20, 22 flows cooling.
  • Cooling channel 28 from the cooling air flows through not shown further cooling channels to arranged at the trailing edge 24 outlet openings 40, at which the cooling air leaves the turbine blade 10.
  • the outlet openings 40 are designed as so-called "cut-back openings". However, this is irrelevant to the invention. They could also alternatively be arranged as central outlet openings at the trailing edge 24.
  • the four openings 38 are designed as bores, their longitudinal axes do not extend perpendicular to the flat surface 37 of the cover 36. Rather, the bore axes of the openings 38 are inclined so that they each have a tangential component for the incoming Provide cooling medium K, so that in the cooling channel 28 can form a flow that is swirling: flowing in the cooling channel 28 cooling medium K flows quasi on one or more helical lines around the neutral chord of the cooling channel, which lies in the centroid of the cross section of the cooling channel.
  • the openings 38 are inclined relative to the Abdeckelementsenkrechten that they impose the incoming cooling medium K the swirl.
  • guide elements may be provided on the surface of the cover element facing the cooling channel 28, which, for example, are inclined with respect to a surface perpendicular.
  • FIG. 2 shows the access-side region of the cooling channel 28 of an alternative turbine blade 110 in a further schematic representation.
  • the cooling channel 28 is bounded by inner surfaces 21, 23 which are part of the side walls 20 and 22 respectively.
  • the access 34 of the cooling channel 28 is through a cover member 136 according to a second embodiment covered.
  • the cover element 136 is configured in the shape of a cylinder hat and thereby has a collar-shaped ring 137, on whose inner diameter a swirl generator 139 is provided.
  • the swirl generator 139 is in the form of a drum and in this embodiment does not extend into the cooling channel 28, but protrudes outwards.
  • a lid 140 is provided at the outer end of the swirl generator 139.
  • openings 138 are also provided.
  • FIG. 3 shows the cross section through the swirler 139 along the section line III-III.
  • the swirl generator 139 is configured hollow inside and has an outer diameter d a , which is comparatively large compared to its inner diameter d i .
  • the swirl generator 139 is made comparatively thick-walled.
  • two inflow passages 143 which are aligned tangentially with respect to a central axis 44 of the swirler 139, extend.
  • Each inflow passage 143 may also be designed as a row of holes or as a slot.
  • the turbine blade 110 is supplied with the cooling medium K from outside. This flows laterally into the swirl generator 139 through the inflow passages 143. Due to the comparatively thick-walled design, the cooling medium K guided through the inflow passages 143 is directed into the interior of the swirl generator 139. This flows therein with a directed around the central axis 44 twist. Subsequently, the cooling medium flows into the cooling channel 28, where it continues to be swirling, where it cools the inner surfaces 21, 23 of the side walls 20, 22 and thus the blade 14.
  • the value for the average channel height B K for example, between 1 cm and 4 cm and for the wall thickness WS of the cover 136, for example, between 0.5 mm and 2 mm.
  • variants of cover elements 36 are also conceivable in which openings 138 are missing in the collar-shaped ring 137. This applies in particular to variants in which the first distance b 1 is selected to be zero.
  • the apertures 138 may be employed as well as the apertures 38 of the first embodiment to further aid in the cyclonic action of the vortex generator 139.
  • FIG. 4 shows a third turbine blade 210 with a third embodiment of a cover 236. However, only the differences from the second embodiment will be explained below.
  • the cover element 236 is designed in such a way that, in addition to cyclone cooling, it additionally effects a partial impingement cooling of the cooling channel or of the inner surfaces 21, 23 allows.
  • the cover element 236 is formed as a shortened impingement cooling insert with a tubular section 245 compared to the length of the cooling channel.
  • Impact cooling openings 247 are provided in the tubular section 245, wherein the tubular section 245 is preferably not circular in cross-section, but rather resembles the cross-sectional contour of the mostly trapezoidal cooling channel 28.
  • the tubular portion 245 has an inflow-side end 34 with an opposing bottom 249.
  • the swirl generator 139 is attached to the floor 249 via a support wall 251. In order to obtain a flat cover member 36, the tubular portion 245 and the swirl generator 139 overlap. In the bottom 249 and the swirl-supporting openings 38 are arranged.
  • the airfoil 14 is impingement-cooled in a first section D and cyclone-cooled in a second section M.
  • FIG. 5 A fourth exemplary embodiment of a cover element 336 in the form of a combined impact-cooling insert with a swirl generator 339 is shown in FIG FIG. 5 illustrated in which the swirl generator 339 and the tubular portion 245 for the impingement cooling with respect to the longitudinal axis of the cooling channel 28, not as in FIG. 4 overlapping, but are arranged axially offset from each other.
  • the swirl generator 339 according to this embodiment comprises eight rectilinear inflow passages 343 arranged with respect to the center axis 44 and the third diameter d a like a secant.
  • Each inflow passage 343 may be configured as a single bore, as a series of holes or as a slot.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16153374.0A 2016-01-29 2016-01-29 Aube de turbine pour une turbomachine thermique Withdrawn EP3199759A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16153374.0A EP3199759A1 (fr) 2016-01-29 2016-01-29 Aube de turbine pour une turbomachine thermique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16153374.0A EP3199759A1 (fr) 2016-01-29 2016-01-29 Aube de turbine pour une turbomachine thermique

Publications (1)

Publication Number Publication Date
EP3199759A1 true EP3199759A1 (fr) 2017-08-02

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Family Applications (1)

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EP16153374.0A Withdrawn EP3199759A1 (fr) 2016-01-29 2016-01-29 Aube de turbine pour une turbomachine thermique

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EP (1) EP3199759A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20190041702A (ko) * 2017-10-13 2019-04-23 두산중공업 주식회사 버킷의 쓰로틀 플레이트 결합구조와 이를 포함하는 회전체 및 가스터빈
DE102020007518A1 (de) 2020-12-09 2022-06-09 Svetlana Beck Verfahren zum Erreichen von hohen Gastemperaturen unter Verwendung von Zentrifugalkraft

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19834376A1 (de) * 1998-07-30 2000-02-03 Asea Brown Boveri Verfahren, Einrichtung und Anwendung des Verfahrens zum Kühlen von Leitschaufeln in einer Gasturbinenanlage
WO2009153108A2 (fr) 2008-05-26 2009-12-23 Alstom Technology Ltd. Turbine à gaz pourvue d'une aube directrice
US7665965B1 (en) * 2007-01-17 2010-02-23 Florida Turbine Technologies, Inc. Turbine rotor disk with dirt particle separator
EP2703603A2 (fr) * 2012-09-04 2014-03-05 Rolls-Royce Deutschland Ltd & Co KG Aube de turbine à gaz dotée d'un élément générateur de tourbillon et son procédé de fabrication
EP2899370A1 (fr) * 2014-01-16 2015-07-29 Doosan Heavy Industries & Construction Co., Ltd. Aube de turbine à canal de refroidissement tourbillonnaire et procédé de refroidissement associé

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19834376A1 (de) * 1998-07-30 2000-02-03 Asea Brown Boveri Verfahren, Einrichtung und Anwendung des Verfahrens zum Kühlen von Leitschaufeln in einer Gasturbinenanlage
US7665965B1 (en) * 2007-01-17 2010-02-23 Florida Turbine Technologies, Inc. Turbine rotor disk with dirt particle separator
WO2009153108A2 (fr) 2008-05-26 2009-12-23 Alstom Technology Ltd. Turbine à gaz pourvue d'une aube directrice
EP2703603A2 (fr) * 2012-09-04 2014-03-05 Rolls-Royce Deutschland Ltd & Co KG Aube de turbine à gaz dotée d'un élément générateur de tourbillon et son procédé de fabrication
EP2899370A1 (fr) * 2014-01-16 2015-07-29 Doosan Heavy Industries & Construction Co., Ltd. Aube de turbine à canal de refroidissement tourbillonnaire et procédé de refroidissement associé

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20190041702A (ko) * 2017-10-13 2019-04-23 두산중공업 주식회사 버킷의 쓰로틀 플레이트 결합구조와 이를 포함하는 회전체 및 가스터빈
DE102020007518A1 (de) 2020-12-09 2022-06-09 Svetlana Beck Verfahren zum Erreichen von hohen Gastemperaturen unter Verwendung von Zentrifugalkraft
WO2022122062A1 (fr) 2020-12-09 2022-06-16 Beck, Svetlana Procédé pour obtenir des températures élevées de gaz à l'aide d'une force centrifuge

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