EP1114976A2 - Dispositif de refroidissement d'une paroi d'un conduit comprenant au moins une ailette - Google Patents

Dispositif de refroidissement d'une paroi d'un conduit comprenant au moins une ailette Download PDF

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Publication number
EP1114976A2
EP1114976A2 EP00811044A EP00811044A EP1114976A2 EP 1114976 A2 EP1114976 A2 EP 1114976A2 EP 00811044 A EP00811044 A EP 00811044A EP 00811044 A EP00811044 A EP 00811044A EP 1114976 A2 EP1114976 A2 EP 1114976A2
Authority
EP
European Patent Office
Prior art keywords
rib
flow channel
flow
cooling
rib 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Withdrawn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
EP00811044A
Other languages
German (de)
English (en)
Other versions
EP1114976A3 (fr
Inventor
Alexander Dr. Beeck
Bernhard Dr. Bonhoff
Sacha Dr. Parneix
Bernhard Prof. Dr. Weigand
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.)
GE Vernova GmbH
Original Assignee
Alstom Power Schweiz AG
Alstom SA
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 Power Schweiz AG, Alstom SA filed Critical Alstom Power Schweiz AG
Publication of EP1114976A2 publication Critical patent/EP1114976A2/fr
Publication of EP1114976A3 publication Critical patent/EP1114976A3/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Withdrawn legal-status Critical Current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
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F1/00—Tubular elements; Assemblies of tubular elements
    • F28F1/10—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
    • F28F1/40—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only inside the tubular element
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F13/00—Arrangements for modifying heat-transfer, e.g. increasing, decreasing
    • F28F13/06—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
    • F28F13/12—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by creating turbulence, e.g. by stirring, by increasing the force of circulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
    • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
    • 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
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase 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
    • Y10T137/00—Fluid handling
    • Y10T137/206—Flow affected by fluid contact, energy field or coanda effect [e.g., pure fluid device or system]
    • Y10T137/2087—Means to cause rotational flow of fluid [e.g., vortex generator]
    • Y10T137/2093—Plural vortex generators

Definitions

  • the invention relates to a device for cooling a flow channel surrounding flow channel wall with at least one, in a through the Flow medium passing through flow channel inducing flow eddies Rib element on the side of the flow channel wall facing the flow channel is appropriate and its shape and size under one certain heat transfer coefficients and a certain one by which Overflow of the rib element with the flow medium in this connected Pressure loss are selected.
  • the turbine blades, as well as the combustion chamber walls combined with cooling channels through which in the Relative to the temperatures of the hot gases, relatively cold air is fed in is branched off, for example, from the air compressor stage for cooling purposes.
  • the cooling air flow flowing through the cooling channels cools the cooling channel walls and is warmed up by them.
  • precautions have been taken by which the thermal coupling between Coolant and cooling channel wall can be optimized. So it is known that targeted by providing ribs on the inner wall of the cooling channel turbulent flow components within that passing through the cooling channel Coolant flow can be generated, the flow components perpendicular have on the cooling channel wall.
  • the proportion of the coolant mass flow which comes into direct thermal contact with the cooling channel walls, be significantly increased, which also significantly improves the cooling effect becomes.
  • straight ribs that are arranged obliquely to the main flow direction as is found has relatively stable and pronounced secondary flow vortices, which lead to increased mixing of the boundary layer near the cooling channel wall, through the increasingly cold cooling air can reach the hot cooling channel walls.
  • the invention has for its object a device for cooling a Flow channel wall surrounding the flow channel with at least one, in one fluid flowing through the flow channel inducing rib element, that on the, facing the flow channel Side of the flow channel wall is attached and its shape and size below Given a certain heat transfer coefficient and a certain by the flow medium flowing over the rib element in it associated pressure loss are chosen to develop such that the cooling effect of the flow medium passing through the flow channel is further increased should be done without, by optimizing shape and size of the fin element existing heat transfer coefficient between the cooling channel wall and flow medium and without increasing the connected by the overflow of the rib element with the flow medium Suffering from pressure loss. Measures to increase the cooling effect are said to also with regard to their manufacture with little effort and low manufacturing costs be connected.
  • a device according to the preamble of claim 1 is such trained that the rib element while largely maintaining its original shape and / or size its facing the flow channel Has surface enlarging contours.
  • the idea according to the invention is based on the optimization of the outer rib contour with the aim of increasing the heat transfer surface between the rib and flow medium, however the heat transfer coefficient defined by the spatial shape the rib and the pressure loss caused by the rib shape should remain essentially unaffected in the flow medium.
  • FIG. 1 A side of a cooling duct wall 1 is shown in cross section in FIG. on the flow channel inner wall two rib elements 2, 3 are provided are, which each have a rectangular cross section.
  • a cooling channel delimited by four side walls, two of which are opposite Side walls are provided with rib elements, each in the direction of flow are arranged one after the other in multiple succession.
  • Figure 1a is only in Longitudinal section of a half of a cooling channel 4 shown, the rib elements provided cooling channel walls are spaced from each other by the width H (shown is only the cooling channel up to H / 2).
  • H shown is only the cooling channel up to H / 2
  • the fin height e is approximately 10% of the cooling channel height H, which at the same time also corresponds to the hydraulic diameter of the cooling channel.
  • the ratio of the distance p between two rib elements 2, 3 arranged directly adjacent in the longitudinal direction of the cooling channel and the rib height e is approximately 10.
  • FIG. 2 shows a further embodiment of a rib element, which has a rectangular cross section and three grooves 6 for the purpose of enlarging the surface having. In addition, the edges are rounded.
  • FIGS. 3a-d other cross-sectional shapes can also be used can be used for the rib elements, with surface enlarging Measures are not based solely on indentations in the rib elements are limited.
  • FIG. 3a shows a conventional rectangular rib, which extends over its entire length has a constant cross-section.
  • the rectangular rib shown in Figure 3b has a along its extent increasing rectangular cross-section.
  • its cross-sectional shape is semicircular and a continuous in the longitudinal direction of the ribs has increasing semicircle diameter.
  • for a surface enlargement changes all geometry parameters of the rib element like rib height, rib width, distance between two adjacent ribs in relation to their height as well as the inclination of the rib axis.
  • FIGS. 4a-d there are combinations of grooves or grooves and specific changes in cross-section shown along the longitudinal axis of the ribs.
  • Figure 4a shows one Rectangular rib with a constant rib cross-section and one worked into it Groove.
  • Figure 4b shows a rib element with a rectangular groove and with in the longitudinal direction of the ribs increasing rectangular cross-section and one semicircular incorporated recess.
  • FIG. 4c shows a triangular cross-sectional shape Ribs on both side flanks of straight recesses are provided.
  • FIG. 4d has an original semicircular design Cross section on, in which a parabolic recess is incorporated.
  • Three-dimensional depressions can also be worked into the rib elements are, as is apparent from Figures 5a - 5c.
  • Figure 5a is a rectangular rib with a rectangular shape Wells shown.
  • Figure 5b shows a semicircular in cross section trained rib with cylindrical recesses.
  • Figure 5c instructs on its surface three-dimensional cubic body, through which a special large surface area enlargement is possible.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Geometry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Cooling Or The Like Of Semiconductors Or Solid State Devices (AREA)
EP20000811044 1999-12-28 2000-11-07 Dispositif de refroidissement d'une paroi d'un conduit comprenant au moins une ailette Withdrawn EP1114976A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19963374 1999-12-28
DE1999163374 DE19963374B4 (de) 1999-12-28 1999-12-28 Vorrichtung zur Kühlung einer, einen Strömungskanal umgebenden Strömungskanalwand mit wenigstens einem Rippenelement

Publications (2)

Publication Number Publication Date
EP1114976A2 true EP1114976A2 (fr) 2001-07-11
EP1114976A3 EP1114976A3 (fr) 2001-10-31

Family

ID=7934745

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20000811044 Withdrawn EP1114976A3 (fr) 1999-12-28 2000-11-07 Dispositif de refroidissement d'une paroi d'un conduit comprenant au moins une ailette

Country Status (3)

Country Link
US (1) US6446710B2 (fr)
EP (1) EP1114976A3 (fr)
DE (1) DE19963374B4 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1500895A3 (fr) * 2003-07-22 2005-04-06 Modine Manufacturing Company Conduit pour échangeur de chaleur
EP2284363A1 (fr) * 2009-07-07 2011-02-16 Rolls-Royce plc Passage de transfert de chaleur
ITMI20110788A1 (it) * 2011-05-09 2012-11-10 Ansaldo Energia Spa Pala di turbina a gas
WO2014139738A1 (fr) * 2013-03-13 2014-09-18 Siemens Aktiengesellschaft Brûleur à jet de gaz comportant un canal de refroidissement dans la plaque de base
EP2993403A1 (fr) * 2014-09-05 2016-03-09 Mitsubishi Hitachi Power Systems, Ltd. Chambre de combustion de turbine à gaz
EP3276128A1 (fr) * 2016-07-25 2018-01-31 Siemens Aktiengesellschaft Élément de paroi pouvant être refroidi

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US7007482B2 (en) * 2004-05-28 2006-03-07 Power Systems Mfg., Llc Combustion liner seal with heat transfer augmentation
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US20070201980A1 (en) * 2005-10-11 2007-08-30 Honeywell International, Inc. Method to augment heat transfer using chamfered cylindrical depressions in cast internal cooling passages
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JP4485583B2 (ja) * 2008-07-24 2010-06-23 トヨタ自動車株式会社 熱交換器及びその製造方法
US20120000072A9 (en) * 2008-09-26 2012-01-05 Morrison Jay A Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components
FR2938637B1 (fr) * 2008-11-18 2013-01-04 Cie Mediterraneenne Des Cafes Conduit de circulation d'un fluide
US20110033311A1 (en) * 2009-08-06 2011-02-10 Martin Nicholas F Turbine Airfoil Cooling System with Pin Fin Cooling Chambers
US8894367B2 (en) * 2009-08-06 2014-11-25 Siemens Energy, Inc. Compound cooling flow turbulator for turbine component
JP5455962B2 (ja) * 2011-04-06 2014-03-26 三菱重工業株式会社 冷却構造の製造方法
US8807945B2 (en) 2011-06-22 2014-08-19 United Technologies Corporation Cooling system for turbine airfoil including ice-cream-cone-shaped pedestals
US9297532B2 (en) * 2011-12-21 2016-03-29 Siemens Aktiengesellschaft Can annular combustion arrangement with flow tripping device
CA2887454A1 (fr) * 2012-10-24 2014-05-01 Alstom Technology Ltd. Combustion sequentielle avec melangeur de gaz d'appoint
US9869279B2 (en) * 2012-11-02 2018-01-16 General Electric Company System and method for a multi-wall turbine combustor
EP3660401B1 (fr) * 2013-05-23 2021-10-06 Raytheon Technologies Corporation Panneau intérieur pour une chambre de combustion d'une turbine à gaz
JP6108982B2 (ja) * 2013-06-28 2017-04-05 三菱重工業株式会社 タービン翼及びこれを備える回転機械
WO2015032936A1 (fr) * 2013-09-09 2015-03-12 Siemens Aktiengesellschaft Chambre de combustion d'une turbine à gaz et outil et procédé permettant de produire des canaux de refroidissement dans un composant d'une turbine à gaz
KR102138327B1 (ko) * 2013-11-15 2020-07-27 한화에어로스페이스 주식회사 터빈
US9551229B2 (en) * 2013-12-26 2017-01-24 Siemens Aktiengesellschaft Turbine airfoil with an internal cooling system having trip strips with reduced pressure drop
US20170159487A1 (en) * 2015-12-02 2017-06-08 General Electric Company HT Enhancement Bumps/Features on Cold Side
KR101797370B1 (ko) * 2016-07-04 2017-12-12 두산중공업 주식회사 가스터빈 블레이드
US10830448B2 (en) * 2016-10-26 2020-11-10 Raytheon Technologies Corporation Combustor liner panel with a multiple of heat transfer augmentors for a gas turbine engine combustor
KR20180065728A (ko) * 2016-12-08 2018-06-18 두산중공업 주식회사 베인의 냉각 구조
KR102099307B1 (ko) * 2017-10-11 2020-04-09 두산중공업 주식회사 라이너 냉각을 촉진하는 난류 생성 구조 및 이를 포함하는 가스 터빈용 연소기
EP3473961B1 (fr) 2017-10-20 2020-12-02 Api Heat Transfer, Inc. Échangeur de chaleur
CN108386234B (zh) * 2018-02-23 2021-03-16 西安交通大学 一种以柱排肋片为基本冷却单元的燃机叶片内部冷却结构
FR3089549B1 (fr) * 2018-12-07 2021-01-29 Safran Aircraft Engines Aube creuse de turbomachine équipée de perturbateurs primaires et de perturbateurs secondaires
CN111271133B (zh) * 2020-03-09 2021-04-09 北京南方斯奈克玛涡轮技术有限公司 一种有复杂肋片结构内冷通道的涡轮导向器叶片
CN112282861A (zh) * 2020-11-20 2021-01-29 西安热工研究院有限公司 一种透平叶片内部扰流装置
FR3124822B1 (fr) * 2021-07-02 2023-06-02 Safran Aube de turbomachine equipee d’un circuit de refroidissement et procede de fabrication a cire perdue d’une telle aube
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1500895A3 (fr) * 2003-07-22 2005-04-06 Modine Manufacturing Company Conduit pour échangeur de chaleur
EP2284363A1 (fr) * 2009-07-07 2011-02-16 Rolls-Royce plc Passage de transfert de chaleur
US8511977B2 (en) 2009-07-07 2013-08-20 Rolls-Royce Plc Heat transfer passage
ITMI20110788A1 (it) * 2011-05-09 2012-11-10 Ansaldo Energia Spa Pala di turbina a gas
WO2014139738A1 (fr) * 2013-03-13 2014-09-18 Siemens Aktiengesellschaft Brûleur à jet de gaz comportant un canal de refroidissement dans la plaque de base
US10088163B2 (en) 2013-03-13 2018-10-02 Siemens Aktiengesellschaft Jet burner with cooling duct in the base plate
EP2993403A1 (fr) * 2014-09-05 2016-03-09 Mitsubishi Hitachi Power Systems, Ltd. Chambre de combustion de turbine à gaz
US10443845B2 (en) 2014-09-05 2019-10-15 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
EP3276128A1 (fr) * 2016-07-25 2018-01-31 Siemens Aktiengesellschaft Élément de paroi pouvant être refroidi

Also Published As

Publication number Publication date
EP1114976A3 (fr) 2001-10-31
DE19963374B4 (de) 2007-09-13
DE19963374A1 (de) 2001-07-12
US20020005274A1 (en) 2002-01-17
US6446710B2 (en) 2002-09-10

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