EP1006263B1 - Refroidissement d'aube - Google Patents

Refroidissement d'aube Download PDF

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Publication number
EP1006263B1
EP1006263B1 EP98811184A EP98811184A EP1006263B1 EP 1006263 B1 EP1006263 B1 EP 1006263B1 EP 98811184 A EP98811184 A EP 98811184A EP 98811184 A EP98811184 A EP 98811184A EP 1006263 B1 EP1006263 B1 EP 1006263B1
Authority
EP
European Patent Office
Prior art keywords
blade
cooling
channel
drawer
flow
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
EP98811184A
Other languages
German (de)
English (en)
Other versions
EP1006263A1 (fr
Inventor
Hartmut Hähnle
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 Switzerland GmbH
Original Assignee
Alstom Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Priority to DE59810560T priority Critical patent/DE59810560D1/de
Priority to EP98811184A priority patent/EP1006263B1/fr
Priority to US09/450,729 priority patent/US6328532B1/en
Priority to CN99125857.6A priority patent/CN1261673C/zh
Publication of EP1006263A1 publication Critical patent/EP1006263A1/fr
Application granted granted Critical
Publication of EP1006263B1 publication Critical patent/EP1006263B1/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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades

Definitions

  • the invention relates to an internally cooled blade of a turbomachine. especially a gas turbine, with guidance from Flow of a cooling fluid in a cooling channel.
  • turbomachinery especially gas turbines
  • the efficiency of turbomachinery, especially gas turbines, can about an increase in pressure and temperature of the fluid as a parameter determining the cycle process improved become.
  • convection cooling is predominantly used as a cooling method for cooling blades by means of a cooling fluid, mostly cooling air, which is common today.
  • the cooling fluid is passed through the blades, which are each hollow or provided with cooling channels.
  • the material temperature that is set is below the maximum permissible temperature of the blade material.
  • the cooling fluid usually flows out into the main flow via one or more openings in the blade wall.
  • the cooling fluid is also conducted into another internal chamber at the end of the cooling channel and from there into another cooling channel or also into the main flow.
  • Another method for cooling blades is the so-called film cooling.
  • a cooling fluid usually also cooling air, which is supplied in cooling channels, is blown out onto the blade surface through openings in the blade.
  • the cooling fluid forms a separating layer, similar to a fluid film, between the blade wall and the hot flow fluid.
  • the invention has for its object the flow of a Cooling fluids of a cooled blade of a turbomachine to run along a top wall and / or side wall in such a way that its cooling effect is increased.
  • At least one insertion element is arranged in at least one recess in the blade for guiding the cooling fluid, and this insertion element is directly adjacent to the top wall and / or one side wall or both side walls of the blade and at least one flow channel is arranged in the insertion element which is connected to the cooling channel via at least one opening and has at least one outlet opening, the flow channel being formed by means of a groove arranged in the insertion element and the adjacent top wall and / or an adjacent side wall of the blade.
  • the flow channel is usually designed with a smaller flow cross section than the cooling channel. It is particularly expedient to design the outlet opening of the flow channel as a through opening in the adjacent top wall and / or an adjacent side wall.
  • the cooling duct has no further outlet openings, the entire cooling fluid supplied to the cooling duct thus flows through the flow duct. If there are further outlet openings of the cooling channel, the cooling fluid mass flow is divided accordingly. If several cooling channels are arranged in the blade or the cooling channel is subdivided into partial channels, the outlet opening of the flow channel can also expediently open into a further cooling channel or a further partial channel of the cooling channel. It was found that the cooling fluid can be guided in a targeted manner along the adjacent top wall and / or the adjacent side wall by means of such a flow channel. This enables targeted cooling of wall areas that were previously poorly or not at all cooled. In addition, it has been found that the cooling effect of the cooling fluid guided in such a flow channel is often increased.
  • Turbulators which lead to an increase in the degree of turbulence of the cooling fluid flowing through the flow channel are particularly expediently arranged in the flow channel. As a result, the heat transfer of the cooling fluid to the side walls is increased again and the cooling effect is thus increased. Simple transverse webs, for example, can be used as such turbulators in the flow channel.
  • the recess and the insertion element are preferably designed with a rectangular or slot-shaped cross section.
  • the cross section to be considered here is the cross section perpendicular to the insertion direction of the insertion element. It is particularly expedient to design the dimensions of the cutout and of the insertion element with respect to one another in the form of an interference fit. As a result, the insert element can be inserted into the recess by means of a positive fit. The insertion element is often also soldered appropriately. Furthermore, it is advantageous to arrange the insertion element perpendicular to the blade height direction in the recess. In an advantageous embodiment, at least the insertion element has a shoulder or a continuously reducing cross-section.
  • the cross section of the insertion element is advantageously reduced in the insertion direction of the insertion element into the recess.
  • the cutout is expediently designed in the same way, so that the insert element can be inserted into the cutout by means of a positive fit.
  • Both the recess and the insert element expediently extend from the suction side to the pressure side of the blade.
  • the recess can be manufactured and processed in a simple manner in terms of production technology.
  • the outer contour of the insert element is advantageously adapted to the contour of the blade profile at the point of the recess. In this way, tripping point-like transitions in the course of the wall contour of the blade are avoided. Such tripping point-like transitions would lead to higher flow losses in the main flow of the turbomachine.
  • Figure 1 shows an internally cooled blade 110 in a turbomachine with a recess 121 according to the invention and a Insert element arranged according to the invention in the recess 120.
  • the illustrated blade 110 is in the area of Insert element 120 executed without a cover tape.
  • the Indian The cooling channel running in blade 110 is not shown in FIG. 1.
  • the recess 121 and the insertion element 120 are here in the area of the blade tip in an advantageous Design approximately perpendicular to the blade height direction 118 arranged.
  • the recess 121 and the insertion element 120 in the area of maximum Blade thickness arranged in the blade and extend in the longitudinal direction of the blade only over a portion of the Shovel.
  • the arrangement of the insert element and the recess in a shovel can also be used on another the position of the blade shown.
  • the illustration shows the recess 121 and the insertion element 120 has a rectangular cross section.
  • the one looked at here Cross section is the cross section perpendicular to the direction of insertion of the insert element.
  • the dimensions of the recess 121 and the insert element 120 are expedient to one another here realized as a press fit.
  • the insert element fixed in the recess by soldering. hereby it is possible in a simple and inexpensive way to fix the insert element in the recess.
  • the exterior The contour of the insert element 120 is the blade profile contour adjusted at the point of the recess. Consequently become stumbling point-like transitions in the contour course the shovel avoided.
  • FIG. 2 the arrangement according to the invention of the insertion element 220 in the cutout 221 of the blade 210 is shown in perspective in a section through the blade 210.
  • the blade 210 which is hollow on the inside, has, in addition to a pressure-side and a suction-side wall 211, a top wall 212 which closes off the cavity inside the blade.
  • the cavity inside the blade serves here as a one-piece cooling channel 213 of the blade 210.
  • the cooling fluid 230 is fed to the blade through a feed opening in the blade root (not shown in the figure).
  • the insertion element 220 shown in FIG. 2 is arranged in the blade tip region approximately perpendicular to the blade height direction in the recess 221.
  • the recess 221 and the insert element 220 extend only over a partial area of the blade 210, whereas both the recess 221 and the insert element 220 extend continuously in the blade thickness direction from the pressure side to the suction side of the blade.
  • the outer contours of the insert element 220 are expediently adapted to the outer profile contours of the blade 210, and thus the pressure-side and suction-side blade profile contours.
  • the recess 221 and the insert element 220 are each designed with a cross-section which is matched to one another and are joined together by means of an interference fit.
  • the flat top of the insert element 220 directly adjoins the inside of the blade of the top wall 212.
  • the insert element 220 in the illustrated embodiment of the invention has a plurality of grooves such that two grooves, which are arranged separately from one another on the upper side of the insert element 220, form two flow channels 222 together with the top wall 212. These flow channels 222 thus run parallel to the top wall 212 along this.
  • the flow channels 222 are connected to the cooling channel 213 of the blade 210 via further openings 223 arranged in the front end face of the insertion element 220. Cooling fluid 230 can thus flow from the cooling channel 213 into the flow channels 222.
  • the illustrated flow channels 222 and the openings 223 are designed as rectangular grooves; the designs of the grooves are, however, basically freely selectable.
  • an outlet opening 224 realized as a passage opening is arranged in the top wall 212 or in the side wall 211 for each flow duct 222.
  • FIG 3 shows the arrangement of the passage opening 224 in the Sidewall 211 of the blade in an enlargement.
  • the Through opening 224 is designed as a bore and runs inclined to the surface of the side wall 211.
  • the passage opening opens at the closed end of the Flow channel 222 in this.
  • the angle of attack of the passage opening 224 was advantageously chosen here so that emerging Fluid the smallest possible misalignment to the has the main flow flowing around the blade.
  • Cooling fluid 230 in the blade 210 has a higher resting pressure as the main flow fluid flowing around the blade, this flows from the cooling channel 213 to the flow channel 222 added cooling fluid through the passage openings 224 in the mainstream. A continuous one is thus formed Cooling fluid flow through the flow channels and through openings out.
  • FIG. 4 shows a side view of a section through an internally cooled blade with a further embodiment of the insert element 320 arranged according to the invention in the recess 321.
  • the section runs in the center of the blade and shows, in addition to the cut top wall 312 of the blade, a section of the cooling channel 313 running in the blade.
  • the arrangement of the recess 321 was chosen here such that a part of the recess 321 extends into the top wall 312.
  • the insertion element 320 inserted into the recess 321 is also proportionally fitted into the top wall 312 here.
  • the insert element 320 expediently has a rectangular cross section. The insert element is thus positioned in the recess by means of a positive fit.
  • the insert element and the cutout can also be designed with other cross sections, for example with oval, trapezoidal, rhomboidal or polygonal cross sections, which, however, are then in turn to be coordinated with one another.
  • the insert element 320 in the illustrated embodiment has two grooves, which are shown in the middle in FIG. 4. The groove arranged on the upper side of the insert element, together with the adjacent top wall 312, forms a flow channel 322 running parallel to the top wall 312 on the underside of the top wall 312. This flow channel 322 is via the opening 323 through the second one on the front side of the insert element 320 arranged groove is formed, connected to the cooling channel 313.
  • the opening 323 could also be designed as a bore provided in the insert element 320.
  • a passage opening 324 is made in the top wall 312 by means of an obliquely positioned bore.
  • This passage opening 324 opens into the flow channel 322 at the end of the flow channel 322 which is closed toward the cooling channel 313.
  • Cooling fluid 330 flows from the cooling channel 313 via the flow channel 322 arranged in the insertion element 320 into the passage opening 324 and from there onto the top of the top wall 312 and thus into the main flow flowing around the blade.
  • a targeted cooling of the wall adjoining the flow channel 322 is established.
  • the passage opening 324 can be designed with a larger cross section due to the upstream arrangement of the flow channel 322 and the pressure loss occurring in the flow channel 322 compared to an arrangement without an upstream flow channel. This leads to a low risk of clogging the passage openings during the operation of a turbomachine due to foreign particles.
  • FIG Cut through an internally cooled shovel The The cooling duct shown here is through an intermediate wall 417 divided into two sub-channels 415, 416.
  • the inventive Arrangement of the insert element 420 in the recess 421 of the Blade in the embodiment of the invention shown here corresponds to the arrangement according to FIG. 4. This correspondence limits the freely and independently selectable Embodiments of the invention in FIGS. 4 and 5 not a.
  • the cooling fluid flows out 430 not in the main flow, but is by means of the insertion element 420 from the first sub-channel 415 of the cooling channel deflected into the second subchannel 416.
  • the one in the insert element For this purpose, 420 arranged flow channel 422 is by means of an opening 423 with the respective subchannels 415, 416 connected. That in the flow channel 422 along the top wall 412 from the first subchannel 415 into the second subchannel 416 flowing cooling fluid 430 leads to a targeted Cooling the top wall 412.

Landscapes

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

Claims (6)

  1. Ailette (_10) d'une turbomachine, en particulier d'une turbine à gaz, avec un canal de refroidissement (_13) se prolongeant dans l'ailette, à travers lequel s'écoule un fluide réfrigérant, le canal de refroidissement (_13) présentant outre une ouverture d'alimentation, au moins une ouverture supplémentaire (_24) et pour entraíner le fluide réfrigérant (_30), au moins un élément insérable (_20) est disposé dans au moins un évidement (_21) de l'ailette, et cet élément insérable (_20) est directement contigu à la paroi de recouvrement (_12) et/ou à une paroi latérale (_11) ou à deux parois latérales (_11) de l'ailette (_10) et dans laquelle est disposé au moins un canal d'écoulement (_22) dans l'élément insérable (_20), lequel canal d'écoulement (_22) est relié au canal de refroidissement (_13) par au moins une ouverture (_23) et présente au moins une ouverture de sortie (_24), caractérisée en ce que le canal d'écoulement (_22) est formé au moyen d'une rainure disposée dans l'élément insérable (_20) et de la paroi de recouvrement contiguë (_12) et/ou d'une paroi latérale contiguë (_11) de l'ailette (_10).
  2. Ailette selon la revendication 1, caractérisée en ce que l'ouverture de sortie (_24) est réalisée sous la forme d'une ouverture de passage dans la paroi de recouvrement (12) ou la paroi latérale (_11) contiguës de l'ailette (_10).
  3. Ailette selon la revendication 1, caractérisée en ce que l'élément insérable (_20) et l'évidement (_21) sont réalisés avec une section rectangulaire ou en forme de fente.
  4. Ailette selon la revendication 1, caractérisée en ce que l'élément insérable (_20) et l'évidement (_21) sont disposés perpendiculairement ou approximativement perpendiculairement à la direction de la hauteur de l'ailette (118).
  5. Ailette selon la revendication 1, caractérisée en ce que l'élément insérable (_20) et l'évidement (_21) présentent un talon ou une réduction de section à prolongement continu.
  6. Ailette selon la revendication 1, caractérisée en ce que l'élément insérable (_20) et l'évidement (_21) s'étendent en passant du côté aspiration vers le côté compression de l'ailette (_10), et le contour externe de l'élément insérable (_20) est adapté au profil de l'ailette.
EP98811184A 1998-11-30 1998-11-30 Refroidissement d'aube Expired - Lifetime EP1006263B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE59810560T DE59810560D1 (de) 1998-11-30 1998-11-30 Schaufelkühlung
EP98811184A EP1006263B1 (fr) 1998-11-30 1998-11-30 Refroidissement d'aube
US09/450,729 US6328532B1 (en) 1998-11-30 1999-11-30 Blade cooling
CN99125857.6A CN1261673C (zh) 1998-11-30 1999-11-30 叶片冷却

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98811184A EP1006263B1 (fr) 1998-11-30 1998-11-30 Refroidissement d'aube

Publications (2)

Publication Number Publication Date
EP1006263A1 EP1006263A1 (fr) 2000-06-07
EP1006263B1 true EP1006263B1 (fr) 2004-01-07

Family

ID=8236462

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98811184A Expired - Lifetime EP1006263B1 (fr) 1998-11-30 1998-11-30 Refroidissement d'aube

Country Status (4)

Country Link
US (1) US6328532B1 (fr)
EP (1) EP1006263B1 (fr)
CN (1) CN1261673C (fr)
DE (1) DE59810560D1 (fr)

Families Citing this family (17)

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Publication number Priority date Publication date Assignee Title
WO2001049975A1 (fr) * 2000-01-06 2001-07-12 Damping Technologies, Inc. Amortisseur pour moteur a turbine
DE10064265A1 (de) * 2000-12-22 2002-07-04 Alstom Switzerland Ltd Vorrichtung und Verfahren zur Kühlung einer Plattform einer Turbinenschaufel
US6749400B2 (en) * 2002-08-29 2004-06-15 General Electric Company Gas turbine engine disk rim with axially cutback and circumferentially skewed cooling air slots
US6976826B2 (en) * 2003-05-29 2005-12-20 Pratt & Whitney Canada Corp. Turbine blade dimple
DE102005013464B3 (de) * 2005-03-21 2006-08-24 Voith Turbo Gmbh & Co. Kg Verfahren zur Herstellung eines Schaufelrades mit in einzelnen Schaufeln integrierten Öffnungen, insbesondere Auslassöffnungen
EP1847696A1 (fr) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Composant pour un système de post-combustion dans une turbine à gaz et turbine à gaz associée.
US7721844B1 (en) 2006-10-13 2010-05-25 Damping Technologies, Inc. Vibration damping apparatus for windows using viscoelastic damping materials
US8082707B1 (en) 2006-10-13 2011-12-27 Damping Technologies, Inc. Air-film vibration damping apparatus for windows
US8167572B2 (en) * 2008-07-14 2012-05-01 Pratt & Whitney Canada Corp. Dynamically tuned turbine blade growth pocket
US20130051976A1 (en) * 2011-08-29 2013-02-28 General Electric Company Flow control module for a turbomachine
US10914320B2 (en) * 2014-01-24 2021-02-09 Raytheon Technologies Corporation Additive manufacturing process grown integrated torsional damper mechanism in gas turbine engine blade
US9645120B2 (en) 2014-09-04 2017-05-09 Grant Nash Method and apparatus for reducing noise transmission through a window
US9752440B2 (en) * 2015-05-29 2017-09-05 General Electric Company Turbine component having surface cooling channels and method of forming same
US10787932B2 (en) 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
BE1026579B1 (fr) * 2018-08-31 2020-03-30 Safran Aero Boosters Sa Aube a protuberance pour compresseur de turbomachine
CN110142426B (zh) * 2019-06-12 2023-12-08 温岭市文昌数控机床设备有限公司 一种数控刀塔冷却结构
US12215597B1 (en) * 2024-01-26 2025-02-04 Pratt & Whitney Canada Corp. Gas turbine engine rotor blade geometry and method for selecting same

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BE795073A (fr) * 1972-03-02 1973-05-29 Gen Electric Procede pour la fabrication d'aubes creuses
FR2176315A5 (en) * 1972-03-15 1973-10-26 Neu Ets Turbine blades - of metal deposited on a lightweight (polyamide) or fusible core
US3867068A (en) * 1973-03-30 1975-02-18 Gen Electric Turbomachinery blade cooling insert retainers
GB1551678A (en) * 1978-03-20 1979-08-30 Rolls Royce Cooled rotor blade for a gas turbine engine
JPS5390509A (en) * 1977-01-20 1978-08-09 Koukuu Uchiyuu Gijiyutsu Kenki Structure of air cooled turbine blade
US5405242A (en) * 1990-07-09 1995-04-11 United Technologies Corporation Cooled vane
US5259730A (en) * 1991-11-04 1993-11-09 General Electric Company Impingement cooled airfoil with bonding foil insert
DE19709607A1 (de) * 1997-03-08 1998-09-10 Abb Research Ltd Leitschaufel für Dampfturbinen

Also Published As

Publication number Publication date
CN1255581A (zh) 2000-06-07
EP1006263A1 (fr) 2000-06-07
CN1261673C (zh) 2006-06-28
DE59810560D1 (de) 2004-02-12
US6328532B1 (en) 2001-12-11

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