EP1167689A1 - Configuration d'une aube de turbine refroidissable - Google Patents

Configuration d'une aube de turbine refroidissable Download PDF

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Publication number
EP1167689A1
EP1167689A1 EP00113298A EP00113298A EP1167689A1 EP 1167689 A1 EP1167689 A1 EP 1167689A1 EP 00113298 A EP00113298 A EP 00113298A EP 00113298 A EP00113298 A EP 00113298A EP 1167689 A1 EP1167689 A1 EP 1167689A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
trailing edge
flow
channel
blade according
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Withdrawn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
EP00113298A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
Michael Strassberger
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 EP00113298A priority Critical patent/EP1167689A1/fr
Priority to JP2002504770A priority patent/JP4683818B2/ja
Priority to US10/311,935 priority patent/US6835046B2/en
Priority to PCT/EP2001/006502 priority patent/WO2001098634A1/fr
Priority to CNB018113273A priority patent/CN1283901C/zh
Priority to EP01949387A priority patent/EP1292760B1/fr
Priority to DE50115690T priority patent/DE50115690D1/de
Publication of EP1167689A1 publication Critical patent/EP1167689A1/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Withdrawn legal-status Critical Current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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • 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
    • 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

Definitions

  • the invention relates to a turbine blade through which cooling fluid flows according to the preamble of claim 1.
  • Such a turbine blade through which cooling fluid flows has internal ones Flow channels separated by inner walls are.
  • the turbine blade is exposed to the working fluid flows around. It can be a turbine blade of a gas turbine act. Then the working fluid is gas.
  • the turbine blade is inclined towards the incoming working fluid so that in the usual way a force component in the circumferential direction the turbine is created. Therefore, the outflow direction of the Working fluids essentially the direction along the Turbine blade in which the working fluid flows around it.
  • the type mentioned is a turbine blade in the back of a turbine. There is the working fluid already relaxed and cooled so far that only low-cooled turbine blades are used. This means that only a lower flow of Cooling fluid is provided by the turbine. Because of the low A meandering structure works through Flow channels for the cooling fluid in low-cooled turbine blades not satisfactory. Because of the slow Flow rate of the cooling fluid would this in Initial area of a meandering flow channel too strong cool and be overheated in the end area and there consequently cool too little. With the mentioned turbine blades can also the flow rate of the Cooling fluids with regard to the centrifugal forces that occur the turbine rotation is too low.
  • the turbine blade is simply along its length Radial extent through which the cooling fluid flows.
  • simple Flow - that is practical for flow channels without reversals with respect to the radial direction of the cooling fluid flow - the above problems do not occur.
  • the resulting cooling fluid flow then has the desired, local - practically at any location of the flow channel predominantly to only radially outwards directed radial flow components.
  • the invention has the advantage that it is a homogeneous cooling the turbine blade, especially in the area of the edges, allowed.
  • the area is particularly problematic here of the trailing edge duct, in which the fluidic requirements e.g. a narrowing of the turbine blade desire.
  • a triple benefit is achieved: this is how it works namely possible for the first time, the rear edge of an inventive Turbine blade to cool effectively and homogeneously at the same time a thin trailing edge (in the sense of an improved Aerodynamics). Furthermore, for the trailing edge channels a natural outflow of the cooling fluid is achieved, which also allows the ones in front of the trailing edge channels front flow channels in their geometry and in particular in their outflow behavior to the technical requirements adapt.
  • front flow channels Apply more discharge length along the brushing edge can than was previously the case. Because the trailing edge channels on the one hand, further in the outflow direction to the rear edge are displaced and, on the other hand, evade through their curved shape, can the front flow channels fill in the free space. The front flow channels can due to the local cross flow components the trailing edge channels should also be bent such that they also have local cross-flow components. Thereby is a different use of space within the cooling volume of the Turbine blade given with better utilization of the cooling air.
  • the flow channels can be shaped such that cross flow components in the outflow direction and in the opposite direction are. However, preference is given exclusively or predominantly Cross flow components are provided in the outflow direction.
  • the cross flow components cause a flow through the Trailing edge that was not previously available. Through use of the cross flow components mentioned will Cooling fluid further automatically to the outflow openings led in the rear edge.
  • a trailing edge channel and / or a front one Flow channel at least in sections, in particular with his / her outer radial sections, from the radial direction turn in the outflow direction.
  • the turning sections are rounded.
  • the turning sections then run without edges with curvature.
  • trailing edge channels There can be several trailing edge channels.
  • the last trailing edge duct when viewed in the outflow direction practically exclusively brought into the rear edge Outflow openings provided.
  • the last trailing edge channel can also be at a radial distance end radially in front of the brushing edge. According to the invention this channel does not need any outflow openings at all in the rubbing edge. It only makes one special effective shaping of the turbine blade - in particular with regard to the efficiency of the turbine.
  • a radially continuous trailing edge channel be present, which both introduced into the brushing edge Outflow openings and introduced into the rear edge Has outflow openings.
  • a radial one Trailing edge channel forms the transition between one front flow channel and a trailing edge channel that only Has outflow openings in the rear edge are introduced.
  • the trailing edge channel has a smooth transition. Thereby can use the available cooling volume effectively become.
  • the last trailing edge channel can be radial outflow openings located further in the rear edge and the radially continuous trailing edge channel radially further out, inserted in the rear edge Have outflow openings.
  • an opening that is a breakthrough in the interior between the two flow channels is then interrupted at the point of the opening.
  • the continuous connection serves to ensure pourability in the To make sense of the core location.
  • the invention achieves that the local, resulting, effective internal cross-section practically over the entire length of a flow channel except for the flow resistance of the flow channel practically negligible cross-sectional deviations is the same size.
  • the cross-sectional deviations are preferably less than twenty percent and especially less than ten percent of the internal cross-section mentioned.
  • the resulting effective total cross-sectional area of the Inflow openings are preferably equal to the total cross-sectional area the outflow openings of a flow channel, the respective total cross-sectional area the inner cross-section of the associated flow channel.
  • a turbine blade according to the invention is slightly cooled, i.e. executed without meandering structure of the flow channels. she is used for the rear area of a turbine and / or for low cooled turbines / turbine blades used.
  • the turbine blade 1 is of the working fluid 3 - which shown in FIG. 1 only as an excerpt is - flows around in the outflow direction 2, whereby the Work output generated or the turbine driven becomes.
  • the turbine blade 1 is exposed to the cooling fluid 31 also exemplarily and in part in the figure 2 is shown - flows along the flow channels 4,5,6. As a result, the turbine blade 1 is cooled.
  • the Cooling fluid 31 can be (cooled) air, for example.
  • Such a turbine blade 1 has a blade root 10 which into a corresponding groove in the turbine disc (not shown here) inserted and fastened there. Swearing the inflow openings 7, 8, 9 shown with corresponding openings in the turbine disc. Through this the cooling fluid 31 fed to the flow channels 4,5,6.
  • the flow channels 4, 5, 6 run between the inflow openings 7,8,9 on the radially inner blade root 10 and in contrast outlets located further radially outward 11,12,13. They run without reversal points with respect to the radial direction 20, i.e. practically reversible.
  • the cooling fluid 31 thus flows through the radial extent in each flow channel 4, 5, 6 the turbine blade 1 is simply simple.
  • Cooling fluid flow 14 locally practically only radially outside - and not radially inward Radial flow components 15 (see Figure 2). All radial flow components 15 thus point from the center of the Turbine turn away.
  • a turbine blade 1 is also then slightly cooled and thus for the implementation of the invention suitable if their flow channels are practically predominant radially outward radial flow components 15 exhibit.
  • the flow channels 4,5,6 separated by the inner walls 30 are curved in the embodiment shown that the resulting cooling fluid flow 14 in addition to those mentioned Radial flow components 15 local cross flow components 17 has.
  • the resulting cooling fluid flow is shown in FIG. 2 for clarification 14 in the flow channels 4,5 schematically in each a radial flow component 15 and a cross flow component 17 disassembled.
  • the radial flow components 15 all point radially outwards. This is the cooling fluid flow 14 with respect to the radial direction 20 practically inversely.
  • the cross flow components 17 are on each point directed locally in the outflow direction 2. Thereby the cooling fluid 31 of the last trailing edge channel 6 Outflow openings 13 in the trailing edge 18, which are further radial lying inside, fed.
  • Trailing edge channels 5, 6 Two trailing edge channels 5, 6 are shown in the figures. Both trailing edge channels 5, 6 open into the outflow openings 13.23 in the rear edge 18.
  • the radially continuous Trailing edge channel 5 opens into the further radially outside lying outflow openings introduced into the rear edge 18 23 and at the same time into the rubbing edge 16 introduced outflow opening 12. So that the further radial outflow openings 23 on the outside through the cooling fluid 31 acted upon in the radially continuous trailing edge channel 5 the last seen in the outflow direction 2 ends Trailing edge channel 6 at a radial distance 22 radially inside in front of the rubbing edge 16. This leaves the outflow openings 23 through the last trailing edge channel 6 without pressure.
  • the trailing edge channels 5, 6 communicate via an opening 24, which in the middle (with respect to the radial direction 20) of the radially continuous trailing edge channel 5 and on the radially outer End of the last trailing edge channel 6 is arranged.
  • the front flow channel 4 seen in the outflow direction 2 expands towards the outside in the radial direction 20 its extension in the outflow direction 2 (i.e. the width).
  • the front flow channel 4 is also curved, that local, resulting cross-flow components 17 are present are.
  • the inner walls 30, the flow channels 4,5,6 separate from each other are over the entire radial extent the turbine blade 1 of practically the same strength.
  • the front flow channel 4 therefore follows in its course Trailing edge channels 5.6 and nestles against them, so that the interior of the turbine blade 1 is practically complete is penetrated by the flow channels 4,5,6.
  • Another new feature of the invention is that the trailing edge channels 5,6 the area of the rear edge 18 of the turbine blade 1 push through practically to a remaining outer wall thickness.
  • This wall thickness - as well as the size of the cast core a cast turbine blade, i.e. the size of the cavities - are down by the technical parameters of the Manufacturing process limited.
  • the rear edge 18 results in a total of the rear edge 18 including homogeneous cooling of the turbine blade 1.
  • the surface pieces 25 are simply hatched. You should one of the same size within each flow channel Mark the area. To clarify the conditions are the areas are not reproduced to scale.
  • the patch 25 is about the cross-sectional deviations 27 in the radial direction 20 bigger.
  • the cross-sectional deviation is 27 preferably less than twenty percent, especially less than ten percent of the inner cross section 25. Also in the radial outer area of the front flow channel 4, where the Turbine blade 1 narrowed, this inner cross section 25 (not shown explicitly) remain the same. To achieve the front flow channel 4 widens for this purpose in the radial direction 20 outwards.
EP00113298A 2000-06-21 2000-06-21 Configuration d'une aube de turbine refroidissable Withdrawn EP1167689A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP00113298A EP1167689A1 (fr) 2000-06-21 2000-06-21 Configuration d'une aube de turbine refroidissable
JP2002504770A JP4683818B2 (ja) 2000-06-21 2001-06-08 冷却材貫流形タービン翼
US10/311,935 US6835046B2 (en) 2000-06-21 2001-06-08 Configuration of a coolable turbine blade
PCT/EP2001/006502 WO2001098634A1 (fr) 2000-06-21 2001-06-08 Configuration d'une aube de turbine pouvant etre refroidie
CNB018113273A CN1283901C (zh) 2000-06-21 2001-06-08 冷却式透平叶片的结构
EP01949387A EP1292760B1 (fr) 2000-06-21 2001-06-08 Configuration d'une aube de turbine pouvant etre refroidie
DE50115690T DE50115690D1 (de) 2000-06-21 2001-06-08 Konfiguration einer kühlbaren turbinenschaufel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00113298A EP1167689A1 (fr) 2000-06-21 2000-06-21 Configuration d'une aube de turbine refroidissable

Publications (1)

Publication Number Publication Date
EP1167689A1 true EP1167689A1 (fr) 2002-01-02

Family

ID=8169046

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00113298A Withdrawn EP1167689A1 (fr) 2000-06-21 2000-06-21 Configuration d'une aube de turbine refroidissable
EP01949387A Expired - Lifetime EP1292760B1 (fr) 2000-06-21 2001-06-08 Configuration d'une aube de turbine pouvant etre refroidie

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP01949387A Expired - Lifetime EP1292760B1 (fr) 2000-06-21 2001-06-08 Configuration d'une aube de turbine pouvant etre refroidie

Country Status (6)

Country Link
US (1) US6835046B2 (fr)
EP (2) EP1167689A1 (fr)
JP (1) JP4683818B2 (fr)
CN (1) CN1283901C (fr)
DE (1) DE50115690D1 (fr)
WO (1) WO2001098634A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101586477B (zh) * 2008-05-23 2011-04-13 中国科学院工程热物理研究所 一种具有射流冲击作用的扰流挡板强化传热装置

Families Citing this family (15)

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US6955525B2 (en) 2003-08-08 2005-10-18 Siemens Westinghouse Power Corporation Cooling system for an outer wall of a turbine blade
US7210906B2 (en) * 2004-08-10 2007-05-01 Pratt & Whitney Canada Corp. Internally cooled gas turbine airfoil and method
RU2425982C2 (ru) * 2005-04-14 2011-08-10 Альстом Текнолоджи Лтд Лопатка газовой турбины
US7442007B2 (en) * 2005-06-02 2008-10-28 Pratt & Whitney Canada Corp. Angled blade firtree retaining system
CN100368128C (zh) * 2006-04-03 2008-02-13 潘毅 透平动叶片铆钉头的加工方法
US20080085193A1 (en) * 2006-10-05 2008-04-10 Siemens Power Generation, Inc. Turbine airfoil cooling system with enhanced tip corner cooling channel
US7857587B2 (en) * 2006-11-30 2010-12-28 General Electric Company Turbine blades and turbine blade cooling systems and methods
US8246306B2 (en) * 2008-04-03 2012-08-21 General Electric Company Airfoil for nozzle and a method of forming the machined contoured passage therein
US8671696B2 (en) * 2009-07-10 2014-03-18 Leonard M. Andersen Method and apparatus for increasing thrust or other useful energy output of a device with a rotating element
FR2954798B1 (fr) * 2009-12-31 2012-03-30 Snecma Aube a ventilation interieure
US9376933B2 (en) * 2011-04-29 2016-06-28 Leonard M. Andersen Apparatus for distributing fluid into a gas turbine
US9932837B2 (en) 2013-03-11 2018-04-03 United Technologies Corporation Low pressure loss cooled blade
US9927123B2 (en) * 2013-10-24 2018-03-27 United Technologies Corporation Fluid transport system having divided transport tube
EP3059394B1 (fr) * 2015-02-18 2019-10-30 Ansaldo Energia Switzerland AG Aube de turbine et ensemble d'aubes de turbine
FR3096074B1 (fr) * 2019-05-17 2021-06-11 Safran Aircraft Engines Aube de turbomachine à bord de fuite ayant un refroidissement amélioré

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641440A (en) * 1947-11-18 1953-06-09 Chrysler Corp Turbine blade with cooling means and carrier therefor
US2687278A (en) * 1948-05-26 1954-08-24 Chrysler Corp Article with passages
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US3885609A (en) * 1972-01-18 1975-05-27 Oskar Frei Cooled rotor blade for a gas turbine
EP0034961A1 (fr) * 1980-02-19 1981-09-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Perfectionnement aux aubes de turbines refroidies
US5462405A (en) * 1992-11-24 1995-10-31 United Technologies Corporation Coolable airfoil structure

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US4073599A (en) * 1976-08-26 1978-02-14 Westinghouse Electric Corporation Hollow turbine blade tip closure
US4180373A (en) * 1977-12-28 1979-12-25 United Technologies Corporation Turbine blade
GB2152150A (en) * 1983-12-27 1985-07-31 Gen Electric Anti-icing inlet guide vane
US5931638A (en) * 1997-08-07 1999-08-03 United Technologies Corporation Turbomachinery airfoil with optimized heat transfer
JP4315599B2 (ja) * 1998-08-31 2009-08-19 シーメンス アクチエンゲゼルシヤフト タービン翼

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641440A (en) * 1947-11-18 1953-06-09 Chrysler Corp Turbine blade with cooling means and carrier therefor
US2687278A (en) * 1948-05-26 1954-08-24 Chrysler Corp Article with passages
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US3885609A (en) * 1972-01-18 1975-05-27 Oskar Frei Cooled rotor blade for a gas turbine
EP0034961A1 (fr) * 1980-02-19 1981-09-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Perfectionnement aux aubes de turbines refroidies
US5462405A (en) * 1992-11-24 1995-10-31 United Technologies Corporation Coolable airfoil structure

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101586477B (zh) * 2008-05-23 2011-04-13 中国科学院工程热物理研究所 一种具有射流冲击作用的扰流挡板强化传热装置

Also Published As

Publication number Publication date
US6835046B2 (en) 2004-12-28
CN1283901C (zh) 2006-11-08
US20030156943A1 (en) 2003-08-21
JP2004501311A (ja) 2004-01-15
EP1292760B1 (fr) 2010-11-03
JP4683818B2 (ja) 2011-05-18
DE50115690D1 (de) 2010-12-16
WO2001098634A1 (fr) 2001-12-27
EP1292760A1 (fr) 2003-03-19
CN1436275A (zh) 2003-08-13

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