EP1456505A1 - Piece a sollicitation thermique - Google Patents

Piece a sollicitation thermique

Info

Publication number
EP1456505A1
EP1456505A1 EP02779098A EP02779098A EP1456505A1 EP 1456505 A1 EP1456505 A1 EP 1456505A1 EP 02779098 A EP02779098 A EP 02779098A EP 02779098 A EP02779098 A EP 02779098A EP 1456505 A1 EP1456505 A1 EP 1456505A1
Authority
EP
European Patent Office
Prior art keywords
deflection
thermally loaded
loaded component
cooling
parts
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Withdrawn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
EP02779098A
Other languages
German (de)
English (en)
Inventor
Kenneth Hall
Sacha Parneix
Remigi Tschuor
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 EP1456505A1 publication Critical patent/EP1456505A1/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Withdrawn legal-status Critical Current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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y10T29/49341—Hollow blade with cooling passage
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/4998—Combined manufacture including applying or shaping of fluent material
    • Y10T29/49988—Metal casting
    • Y10T29/49989—Followed by cutting or removing material

Definitions

  • the invention is based on a thermally loaded component according to the preamble of the first claim.
  • blades are known in which cooling fluid is conducted from the trailing edge region of the blade to the leading edge region via cooling channels formed by partition walls and then blown out via openings in the blade head. In order to cool the trailing edge area of the bucket sufficiently, you blow air out of the rear edge of the blade. Deflection vanes are arranged in order to divert the cooling fluid into the cooling channels.
  • deflection blades are often arranged in the region of the deflection channels.
  • these deflection blades are very fragile and difficult to manufacture using the casting process, even with large components such as for large blades of stationary gas turbines.
  • tensions can form in the cast body because the inner, relatively small-sized parts and the outer parts have different cooling rates. In individual cases, these tensions can lead to cracks in the internal structures, which means that the cast part cannot be used. If the defects are not noticed, the cast part can break during use and e.g. with blades, additional blades and destroy the turbine.
  • the invention is based on the object of avoiding problems with previously known means for deflecting the cooling fluid in a thermally loaded component with at least one cooling channel of the type mentioned at the outset and nevertheless enabling efficient cooling.
  • the deflection device consists of two mutually spaced deflection parts over the height of the cooling channel.
  • the advantages of the invention can be seen, inter alia, in the fact that the function of the deflection device with respect to previously known deflection blades is not impaired by the inventive design of the deflection device.
  • the primary function of the deflection device the prevention of pressure losses and the avoidance of a separation of the cooling fluid flow after the deflection channel is further guaranteed.
  • the deflecting parts according to the invention are arranged in cooling ducts of blades of heat engines.
  • FIG. 1 shows a partial longitudinal section through a blade of a turbine.
  • FIG. 4 shows a cross section through a deflection device according to the invention
  • Fig. 5 shows a cross section through a further inventive
  • FIG. 1 shows a blade 10 of a turbomachine, consisting of a blade 1 and a blade root 11, with which the blade 10 can be mounted on a rotor or stator, not shown.
  • a platform 12 is usually arranged between the airfoil 1 and the airfoil 11 and shields the airfoil and thus the rotor or stator from the fluids flowing around the airfoil.
  • the airfoil 1 has a leading edge region 3, a trailing edge region 4, a suction-side wall 5 and a pressure-side wall 6 (see FIG. 3a), the suction-side and the pressure-side wall being connected to one another in the region of the leading edge 3 and the trailing edge 4, as a result of which a cavity 2 is formed.
  • the front edge region 3 is first acted upon by the fluids flowing around the airfoil 1.
  • the cavity 2 extends essentially in the radial direction through the blade 10 and serves as a cooling fluid passage for a cooling fluid 20.
  • essentially radially extending partition walls 8 are arranged in the cavity 2 in order to generate cooling channels 21.
  • These cooling channels 21 are connected by deflection channels 22, which are designed in such a way that the pressure loss during the deflection is minimal and the heat transfer is as homogeneous as possible in order to avoid local hot zones.
  • additional deflection devices such as deflection blades 9, are arranged in the region of the deflection channels 22.
  • deflecting blades 9 can be designed as desired according to FIGS. 2a, 2b and 2c, e.g. with regard to thickness along the blade, the radius of curvature etc. and must be adapted to the conditions in the deflection channel 22.
  • 3a, 3b and 4 show the deflection vane according to the invention consisting of a first deflection part 9a on the suction side and an opposite second deflection part 9b on the pressure side of the vane.
  • the deflection parts 9a and 9b are at a distance ⁇ from one another, which can be up to 30% of the height 23 of the cooling channel 21 at the location of the deflection parts.
  • the design of the deflecting parts 9a and 9b according to the invention does not impair the function of the deflecting device with respect to previously known deflecting blades.
  • the primary function of the deflection vane is the prevention of pressure losses and the avoidance of a separation of the cooling fluid flow 20 after the deflection channel 22.
  • the deflecting parts can be designed as desired, as shown in FIGS. 2a, 2b and 2c and described above for the deflecting vane.
  • the function of the deflection parts namely the prevention of pressure losses and the avoidance of separation of the cooling fluid flow 20 after the deflection channel 22, is maintained.
  • the distance ⁇ was achieved by arranging a weak point in the deflection vane due to a narrowing or notch 24 in the casting mold.
  • the deflection vane breaks into two parts after the casting process during cooling and the resulting shrinkage, and thus produces the two deflection parts 9a and 9b with the spacing ⁇ .
  • the distance ⁇ and its shape can be set by the design of the notch 24.
  • Such deflection parts can generally be arranged in curvatures of cooling channels of thermally loaded components in order to avoid the problems described above.

Landscapes

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

Abstract

La présente invention concerne une pièce à sollicitation thermique (1, 10) qui est parcourue par au moins un canal de refroidissement (21) destiné au passage d'un liquide de refroidissement (20). Au niveau d'une partie incurvée (22) du canal de refroidissement (21) se trouve un système de déviation (9) servant à rassembler le flux de liquide de refroidissement (20) dans son intégralité. Le système de déviation (9) est composé, dans le sens de la hauteur (23) du canal de refroidissement (21), de deux parties de déviation (9a, 9b) espacées entre elles.
EP02779098A 2001-12-10 2002-12-04 Piece a sollicitation thermique Withdrawn EP1456505A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH225101 2001-12-10
CH22512001 2001-12-10
PCT/CH2002/000661 WO2003054356A1 (fr) 2001-12-10 2002-12-04 Piece a sollicitation thermique

Publications (1)

Publication Number Publication Date
EP1456505A1 true EP1456505A1 (fr) 2004-09-15

Family

ID=4568221

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02779098A Withdrawn EP1456505A1 (fr) 2001-12-10 2002-12-04 Piece a sollicitation thermique

Country Status (4)

Country Link
US (1) US7137784B2 (fr)
EP (1) EP1456505A1 (fr)
AU (1) AU2002342500A1 (fr)
WO (1) WO2003054356A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005012803A1 (de) * 2005-03-19 2006-09-21 Alstom Technology Ltd. Laufschaufel für eine Gasturbinenstufe
US7303376B2 (en) * 2005-12-02 2007-12-04 Siemens Power Generation, Inc. Turbine airfoil with outer wall cooling system and inner mid-chord hot gas receiving cavity
US7955053B1 (en) 2007-09-21 2011-06-07 Florida Turbine Technologies, Inc. Turbine blade with serpentine cooling circuit
EP2143883A1 (fr) * 2008-07-10 2010-01-13 Siemens Aktiengesellschaft Aube de turbine et moyau de coulée de fabrication
US8985940B2 (en) * 2012-03-30 2015-03-24 Solar Turbines Incorporated Turbine cooling apparatus
US9228439B2 (en) * 2012-09-28 2016-01-05 Solar Turbines Incorporated Cooled turbine blade with leading edge flow redirection and diffusion
US20140093388A1 (en) * 2012-09-28 2014-04-03 Solar Turbines Incorporated Cooled turbine blade with leading edge flow deflection and division
CN107407150A (zh) * 2015-03-17 2017-11-28 西门子能源有限公司 具有非约束性流动转向引导结构的涡轮叶片
KR101691095B1 (ko) * 2015-04-20 2016-12-29 연세대학교 산학협력단 가스터빈 블레이드 내부 곡관부 이후의 냉각 성능 국소 조절을 위한 가이드 베인 구조
DE102015112643A1 (de) * 2015-07-31 2017-02-02 Wobben Properties Gmbh Windenergieanlagen-Rotorblatt
US10184341B2 (en) 2015-08-12 2019-01-22 United Technologies Corporation Airfoil baffle with wedge region
US10012092B2 (en) 2015-08-12 2018-07-03 United Technologies Corporation Low turn loss baffle flow diverter
US10450874B2 (en) * 2016-02-13 2019-10-22 General Electric Company Airfoil for a gas turbine engine
US10815791B2 (en) * 2017-12-13 2020-10-27 Solar Turbines Incorporated Turbine blade cooling system with upper turning vane bank
US10774657B2 (en) 2018-11-23 2020-09-15 Raytheon Technologies Corporation Baffle assembly for gas turbine engine components
EP3862537A1 (fr) * 2020-02-10 2021-08-11 General Electric Company Polska sp. z o.o. Tuyère de turbine refoidie et segment d'aube de guidage de turbine
CN111852574A (zh) * 2020-07-27 2020-10-30 北京全四维动力科技有限公司 涡轮叶片及包括其的燃气轮机

Citations (1)

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Publication number Priority date Publication date Assignee Title
EP1223308A2 (fr) * 2000-12-16 2002-07-17 ALSTOM (Switzerland) Ltd Refroidissement d'une composante d'une turbomachine

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Patent Citations (1)

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Publication number Priority date Publication date Assignee Title
EP1223308A2 (fr) * 2000-12-16 2002-07-17 ALSTOM (Switzerland) Ltd Refroidissement d'une composante d'une turbomachine

Also Published As

Publication number Publication date
US7137784B2 (en) 2006-11-21
US20050042096A1 (en) 2005-02-24
WO2003054356A1 (fr) 2003-07-03
AU2002342500A1 (en) 2003-07-09

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Inventor name: PARNEIX, SACHA

Inventor name: TSCHUOR, REMIGI

Inventor name: HALL, KENNETH

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Effective date: 20070625

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Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH

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Owner name: ANSALDO ENERGIA IP UK LIMITED

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