EP1136651A1 - Système de refroidissement pour une aube de turbine à gaz - Google Patents

Système de refroidissement pour une aube de turbine à gaz Download PDF

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Publication number
EP1136651A1
EP1136651A1 EP00106245A EP00106245A EP1136651A1 EP 1136651 A1 EP1136651 A1 EP 1136651A1 EP 00106245 A EP00106245 A EP 00106245A EP 00106245 A EP00106245 A EP 00106245A EP 1136651 A1 EP1136651 A1 EP 1136651A1
Authority
EP
European Patent Office
Prior art keywords
insert
blade
wall
horizontal ribs
cooling fluid
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Withdrawn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
EP00106245A
Other languages
German (de)
English (en)
Inventor
Peter Dipl.-Ing. Tiemann
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 EP00106245A priority Critical patent/EP1136651A1/fr
Priority to JP2001569124A priority patent/JP4637437B2/ja
Priority to EP01919384A priority patent/EP1266127B1/fr
Priority to CNB018067905A priority patent/CN1293285C/zh
Priority to PCT/EP2001/002755 priority patent/WO2001071163A1/fr
Priority to US10/239,234 priority patent/US6769875B2/en
Priority to DE50105062T priority patent/DE50105062D1/de
Publication of EP1136651A1 publication Critical patent/EP1136651A1/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Withdrawn legal-status Critical Current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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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 blade, in particular a turbine blade, with at least one channel bounded by walls is, with in at least one channel with a Cooling fluid loadable insert is inserted.
  • Such a blade is known from US 5,419,039.
  • the cooling fluid emerges from use in these chambers crashes into the walls of the shovel. Subsequently it flows along the walls and passes through outlet openings in specially shaped chambers on the outside of the Walls and from there into the surroundings.
  • With the known Blade is the effect of convection cooling when flowing of the cooling fluid along the walls is small because of the flow length is severely limited. Mixing continues of the cooling fluid in the chambers along the longitudinal axis of the Shovel open so that no targeted cooling is possible.
  • the object of the present invention is therefore a blade to provide an improvement in ease of manufacture the cooling effect is achieved.
  • this task is carried out with a shovel initially mentioned type in that at least one the walls are provided with a number of horizontal ribs, which are arranged between the insert and the wall, and that the insert is provided with openings through which the Enter cooling fluid from the insert between the horizontal fins can.
  • the horizontal ribs guide the coolant along the wall the blade and prevent the coolant from flowing in Direction of the longitudinal axis of the blade. It will be a good one Convection cooling of the wall achieved. Further stiffen the Horizontal ribs the blade so that the wall thickness is reduced can be. The reduction in wall thickness leads to increased cooling efficiency.
  • the manufacture of the shovel can be done with known methods without a complex cross section. Cavity walls are not required. The reject rate is therefore significantly reduced.
  • the insert touches the horizontal ribs.
  • the insert is supported and in the desired Position aligned.
  • the horizontal ribs form cooling fluid flowed through the insert and wall Chambers.
  • a flow of the Cooling fluids reliably in the direction of the longitudinal axis of the blade prevented.
  • the cooling effect along the Longitudinal axis of the blade due to different loading of the chambers with the cooling fluid can be varied in a targeted manner.
  • the openings of the insert at a first end of the chambers and outlet openings for the cooling fluid in the wall at a second end of the chambers are arranged.
  • the cooling fluid therefore flows along the entire length of the chamber along the wall to be cooled, so that the convection cooling is further improved.
  • the horizontal ribs can be substantially perpendicular to that Longitudinal axis of the blade can be arranged.
  • one Angular position are provided. With a vertical arrangement with respect to the longitudinal axis is the length of the horizontal ribs and thus the chambers minimized. The angular position enables an increase in the length of the chambers and thus a further improved convection cooling.
  • the insert is advantageously closed at one end.
  • the Cooling fluid in this case is only from the other end of the Deployed here. An escape of the cooling fluid the end facing away from the feed side is prevented, so that the cooling efficiency is increased. Alternatively, from cooling fluid are supplied to both ends.
  • the turbulators are used to stiffen the wall and go into each other and into the Horizontal ribs over. This will result in a significant increase the rigidity achieved without additional material. At the same thickness of the shovel can again the wall thickness be reduced. At the same time there is a good heat exchange reached between the walls and the cooling fluid. Result it high cooling efficiency and high overall efficiency.
  • the stiffening of the wall does not only arise in the area of one single turbulator. It is rather through the Connection of the turbulators to one another over a large area Stiffener provided.
  • the turbulators are advantageously straight.
  • the use of straight turbulators enables high rigidity with simple production.
  • the turbulators are arranged so that they are together with the horizontal ribs form adjacent recesses in the form of polygons, especially triangles or diamonds.
  • the inside of the Wall is provided with a honeycomb structure.
  • the single ones Polygons or honeycombs each form a closed, high resilient cross-section and support each other. It a significant increase in stiffness can be achieved.
  • the wall thickness of the wall reduced at least in the area between the turbulators. This reduction in wall thickness is made possible by that the turbulators stiffen the wall. By reducing the wall thickness, the cooling efficiency increased again.
  • the turbulators can be advantageous here used as metal feed channels when casting the blade become. The honeycomb structure is therefore easy to manufacture.
  • the blade according to the invention can be used as a guide blade or as Blade of a rotary machine are formed.
  • Figure 1 shows a longitudinal section through a rotary machine in the form of a turbine 10 with a housing 11 and a rotor 12.
  • the housing 11 is with guide vanes 13 and the rotor 12 provided with blades 14.
  • the turbine 10 through which a fluid flows according to arrow direction 15 flows along the guide vanes 13 and blades 14 and the rotor 12 is rotated about an axis 16.
  • the temperature of the fluid is in many applications, especially in the area of the first row of blades (in FIG. 1 shown on the left), relatively high. It is therefore cooling the guide blades 13 and blades 14 are provided.
  • the Flow of the cooling fluid is schematic with the arrows 17, 18 indicated.
  • Figure 2 shows schematically a broken representation of a Guide vane 13.
  • the guide vane 13 has curved outer walls 19, 20 on. The lying between the outer walls 19, 20 The interior is divided into two walls 21 in total divided three channels 22. In each of the channels 22 is one Insert 25 used. The insert is for better illustration of the middle channel 22 not shown.
  • the two outer walls 19, 20 are in each of the channels 22 provided with a number of horizontal ribs 24.
  • the horizontal ribs 24 run along the walls 19, 20 and extend down to the partitions 21. Between the horizontal ribs 24 turbulators 23 are arranged.
  • the stakes 25 touch the horizontal ribs 24.
  • the cooling fluid in particular cooling air, becomes an interior 26 the inserts 25 supplied.
  • the inserts 25 are of a number of openings 27 through which the cooling fluid in the space between the outer walls 19, 20 and the insert 25 exits.
  • the cooling fluid then flows along the outer walls 19, 20 up to outlet openings 28 in the Walls 19, 20. This flow is schematic with the arrow 30 displayed.
  • the openings 27 of the inserts 25 are here spaced from the outlet openings 28 of the outer walls 19, 20 arranged.
  • the outlet openings 28 form in the illustrated Embodiment essentially straight rows 29.
  • the cooling fluid emerging from the inserts 25 initially bounces on the outer walls 19, 20 and there leads to a Impact cooling. Then it flows along the outer walls 19, 20 up to the outlet openings 28, so that convection cooling is achieved. After exiting the outlet openings 28 forms a film of the cooling fluid on the Outside of the outer walls 19, 20, so that also film cooling is made available. There is an essential one improved cooling.
  • the front edge of the guide vane shown on the left in FIG. 2 13 is also provided with direct impingement cooling.
  • the insert 25 has further openings for this impingement cooling 36 on that immediately behind the front edge of the Guide vane 13 are arranged.
  • the cooling medium overflows these openings 36 directly and provides targeted cooling the leading edge of the vane 13 ready.
  • FIGS 3 to 5 show further details of the inside the outer wall 19.
  • the horizontal ribs 24 run essentially perpendicular to a longitudinal axis 31 of the guide vane 13. They are arranged parallel to each other. Between Horizontal ribs 24 are arranged straight turbulators 23, which merge into one another and into the horizontal ribs 24.
  • the front edge 33 of the horizontal ribs 24 goes at the middle Channel 22 in the partition 21 on.
  • Left channel 22 is the leading edge 33 at some distance the foremost outflow openings 28 are arranged.
  • the chambers 32 can be acted upon differently by the cooling fluid become. This is done by varying the number and / or the size of the openings 27 of the insert 25 is reached In this way, individual chambers 32 can be selectively stronger or cooled less than others.
  • the cooling can thus targeted along the longitudinal axis 31 of the guide vane 13 adjusted and adapted to the prevailing conditions become.
  • the turbulators 23 further serve to stiffen the outer wall 19.
  • the straight turbulators 23 are arranged in such a way that they form polygons.
  • Figure 3 are an example Triangles and diamonds in Figure 6 as examples.
  • the stiffening achieved by the turbulators 23 enables a reduction in the wall thickness d of the outer wall 19 in the area between the turbulators 23. Because of this Reducing the wall thickness d further increases the cooling efficiency on.
  • Figure 6 shows a plan view of the inside of the outer wall 19 in a second embodiment.
  • the turbulators 24 With this configuration are the turbulators 24 with respect to the longitudinal axis 31 of the Guide vane 13 inclined. Enlarged due to this inclination the length of the chambers 32 and thus the effect of convection cooling. Even with this configuration are straight Turbulators 23 are provided, four of which are each one Rhombus are summarized. The reduction in wall thickness is indicated schematically in these diamonds with visible edges.
  • the second outer wall 20 is also appropriate Turbulators 23 and horizontal ribs 24 are provided.
  • the horizontal ribs 24 and turbulators 23 can alternatively or additionally provided for a blade 14 become.
  • FIGS. 7 and 8 show two configurations of an insert 25.
  • Such an insert 25 can be used for example in the first row of blades become.
  • an insert 25 according to FIG. 8 can be provided, which is closed at the end 34. The cooling fluid will then fed only through the end 35.
  • This insert will be 25 used in the other rows of blades, in each of which only one end of the vane 13 or the blade 14 via the housing 11 or the rotor 12 with the Cooling fluid can be applied.
EP00106245A 2000-03-22 2000-03-22 Système de refroidissement pour une aube de turbine à gaz Withdrawn EP1136651A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP00106245A EP1136651A1 (fr) 2000-03-22 2000-03-22 Système de refroidissement pour une aube de turbine à gaz
JP2001569124A JP4637437B2 (ja) 2000-03-22 2001-03-12 冷却形タービン翼
EP01919384A EP1266127B1 (fr) 2000-03-22 2001-03-12 Systeme de refroidissement pour aube de turbine
CNB018067905A CN1293285C (zh) 2000-03-22 2001-03-12 涡轮叶片的冷却装置
PCT/EP2001/002755 WO2001071163A1 (fr) 2000-03-22 2001-03-12 Systeme de refroidissement pour aube de turbine
US10/239,234 US6769875B2 (en) 2000-03-22 2001-03-12 Cooling system for a turbine blade
DE50105062T DE50105062D1 (de) 2000-03-22 2001-03-12 Kühlsystem für eine turbinenschaufel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00106245A EP1136651A1 (fr) 2000-03-22 2000-03-22 Système de refroidissement pour une aube de turbine à gaz

Publications (1)

Publication Number Publication Date
EP1136651A1 true EP1136651A1 (fr) 2001-09-26

Family

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP00106245A Withdrawn EP1136651A1 (fr) 2000-03-22 2000-03-22 Système de refroidissement pour une aube de turbine à gaz
EP01919384A Expired - Lifetime EP1266127B1 (fr) 2000-03-22 2001-03-12 Systeme de refroidissement pour aube de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP01919384A Expired - Lifetime EP1266127B1 (fr) 2000-03-22 2001-03-12 Systeme de refroidissement pour aube de turbine

Country Status (6)

Country Link
US (1) US6769875B2 (fr)
EP (2) EP1136651A1 (fr)
JP (1) JP4637437B2 (fr)
CN (1) CN1293285C (fr)
DE (1) DE50105062D1 (fr)
WO (1) WO2001071163A1 (fr)

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EP1840330A2 (fr) 2006-03-24 2007-10-03 United Technologies Corporation Agencement de turbulateurs pour passages d' écoulement
US7300251B2 (en) 2003-11-21 2007-11-27 Mitsubishi Heavy Industries, Ltd. Turbine cooling vane of gas turbine engine
EP2107214A1 (fr) * 2008-03-31 2009-10-07 United Technologies Corporation Refroidissement de surface portante chambrée
EP2890880A4 (fr) * 2012-08-30 2015-12-02 United Technologies Corp Circuit de refroidissement de profil aérodynamique de moteur à turbine à gaz
EP3002412A1 (fr) * 2014-10-03 2016-04-06 Rolls-Royce plc Refroidissement interne de composants d'une turbine à gaz
US10494939B2 (en) 2014-02-13 2019-12-03 United Technologies Corporation Air shredder insert
EP3647544A1 (fr) * 2018-11-01 2020-05-06 United Technologies Corporation Profil d'aube statorique refroidie d'une turbine à gaz
EP3663524A1 (fr) * 2018-12-05 2020-06-10 United Technologies Corporation Schéma de refroidissement à flux axial avec nervure structurale pour un moteur à turbine à gaz
US10822963B2 (en) 2018-12-05 2020-11-03 Raytheon Technologies Corporation Axial flow cooling scheme with castable structural rib for a gas turbine engine

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EP3158169A1 (fr) * 2014-06-17 2017-04-26 Siemens Energy, Inc. Système de refroidissement d'un profil de turbine comprenant un système de refroidissement par impact d'un bord d'attaque et d'un système d'impact d'un quasi-paroi
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US10767487B2 (en) * 2016-11-17 2020-09-08 Raytheon Technologies Corporation Airfoil with panel having flow guide
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US10450873B2 (en) * 2017-07-31 2019-10-22 Rolls-Royce Corporation Airfoil edge cooling channels
EP3460190A1 (fr) * 2017-09-21 2019-03-27 Siemens Aktiengesellschaft Structures d'amélioration de transfert de chaleur sur des nervures en ligne d'une cavité de surface portante d'une turbine à gaz
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US11396819B2 (en) * 2019-04-18 2022-07-26 Raytheon Technologies Corporation Components for gas turbine engines
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US7300251B2 (en) 2003-11-21 2007-11-27 Mitsubishi Heavy Industries, Ltd. Turbine cooling vane of gas turbine engine
EP1840330A3 (fr) * 2006-03-24 2008-07-23 United Technologies Corporation Agencement de turbulateurs pour passages d' écoulement
US7513745B2 (en) 2006-03-24 2009-04-07 United Technologies Corporation Advanced turbulator arrangements for microcircuits
US8210812B2 (en) 2006-03-24 2012-07-03 United Technologies Corporation Advanced turbulator arrangements for microcircuits
EP1840330A2 (fr) 2006-03-24 2007-10-03 United Technologies Corporation Agencement de turbulateurs pour passages d' écoulement
EP2107214A1 (fr) * 2008-03-31 2009-10-07 United Technologies Corporation Refroidissement de surface portante chambrée
US8393867B2 (en) 2008-03-31 2013-03-12 United Technologies Corporation Chambered airfoil cooling
EP2890880A4 (fr) * 2012-08-30 2015-12-02 United Technologies Corp Circuit de refroidissement de profil aérodynamique de moteur à turbine à gaz
US9759072B2 (en) 2012-08-30 2017-09-12 United Technologies Corporation Gas turbine engine airfoil cooling circuit arrangement
US11377965B2 (en) 2012-08-30 2022-07-05 Raytheon Technologies Corporation Gas turbine engine airfoil cooling circuit arrangement
US10494939B2 (en) 2014-02-13 2019-12-03 United Technologies Corporation Air shredder insert
EP3002412A1 (fr) * 2014-10-03 2016-04-06 Rolls-Royce plc Refroidissement interne de composants d'une turbine à gaz
US9797261B2 (en) 2014-10-03 2017-10-24 Rolls-Royce Plc Internal cooling of engine components
EP3647544A1 (fr) * 2018-11-01 2020-05-06 United Technologies Corporation Profil d'aube statorique refroidie d'une turbine à gaz
US10787913B2 (en) 2018-11-01 2020-09-29 United Technologies Corporation Airfoil cooling circuit
EP3663524A1 (fr) * 2018-12-05 2020-06-10 United Technologies Corporation Schéma de refroidissement à flux axial avec nervure structurale pour un moteur à turbine à gaz
US10822963B2 (en) 2018-12-05 2020-11-03 Raytheon Technologies Corporation Axial flow cooling scheme with castable structural rib for a gas turbine engine

Also Published As

Publication number Publication date
JP2003528246A (ja) 2003-09-24
CN1293285C (zh) 2007-01-03
JP4637437B2 (ja) 2011-02-23
EP1266127B1 (fr) 2005-01-12
EP1266127A1 (fr) 2002-12-18
US20030049127A1 (en) 2003-03-13
CN1418284A (zh) 2003-05-14
US6769875B2 (en) 2004-08-03
WO2001071163A1 (fr) 2001-09-27
DE50105062D1 (de) 2005-02-17

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