EP1266127B1 - Kühlsystem für eine turbinenschaufel - Google Patents
Kühlsystem für eine turbinenschaufel Download PDFInfo
- Publication number
- EP1266127B1 EP1266127B1 EP01919384A EP01919384A EP1266127B1 EP 1266127 B1 EP1266127 B1 EP 1266127B1 EP 01919384 A EP01919384 A EP 01919384A EP 01919384 A EP01919384 A EP 01919384A EP 1266127 B1 EP1266127 B1 EP 1266127B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- insert
- 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.)
- Expired - Lifetime
Links
Images
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, wherein in at least one channel with a Cooling fluid acted upon insert is inserted.
- Such a blade is known from US 5,419,039. Between the insert and the walls of the blade become chambers formed in the direction of a longitudinal axis of the blade run. The cooling fluid exits the insert into these chambers and bounces on 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 to the surroundings. In the known Vane is the effect of convection cooling while flowing the cooling fluid along the walls only slightly, since the flow length is very limited. Next, a mixture occurs the cooling fluid in the chambers along the longitudinal axis of the Shovel on, so that no targeted cooling is possible. See EP-A-0 541 207 for details.
- Another blade is from the same applicant W098 / 25009 known.
- This document describes a blade with partially hollow Walls through which a cooling fluid flows. by virtue of the reduction of the wall thickness in the area of the hollow chambers a high cooling efficiency is achieved.
- Shovels with such hollow walls require Shovels with such hollow walls a complicated casting with high reject rates and are therefore very expensive.
- Object of the present invention is therefore a blade to provide an improvement in ease of manufacture the cooling effect achieved.
- the horizontal ribs direct the coolant along the wall the vane and prevent a flow of coolant in Direction of the longitudinal axis of the blade. It will be a good one Convection cooling of the wall reached. Further stiffen the Horizontal ribs the blade, so that the wall thickness decreases can be. The reduction in wall thickness leads to an increased cooling efficiency.
- the manufacture of the shovel can be done with known methods without complex cross-section. Hollow 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, the insert and the wall flowed through by the cooling fluid Chambers.
- the chambers Through the chambers is a stream of Cooling fluid in the direction of the longitudinal axis of the blade reliably prevented.
- the cooling effect along the Longitudinal axis of the blade by a different application the chambers are selectively varied with the cooling fluid.
- 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 Whole length of the chamber along the wall to be cooled, so that the convection cooling is further improved.
- the horizontal ribs may be substantially perpendicular to the Be arranged longitudinal axis of the blade.
- a Angular position can be provided. In a vertical arrangement with respect to the longitudinal axis, the length of the horizontal ribs and thus minimizes the chambers. The angular position allows an increase in the length of the chambers and thus a further improved convection cooling.
- the insert is closed at one end.
- the Cooling fluid is in this case only from the other end of the es supplied. A leakage of the cooling fluid through the end facing away from the feed side is prevented, so that the cooling efficiency is increased.
- from both ends are supplied with cooling fluid.
- the turbulators serve to stiffen the wall and go into each other and into the Horizontal ribs over. This will be a significant increase the rigidity achieved without additional material. at the same strength of the blade, the wall thickness can again be reduced. At the same time, a good heat exchange reached between the walls and the cooling fluid. It revealed thus a high cooling efficiency and a high overall efficiency.
- the stiffening of the wall is not just in the area of one single turbulator. It is rather by the Connecting the turbulators together a large area Stiffening provided.
- the turbulators are straight.
- the Use of straight turbulators allows high rigidity with simple production.
- the turbulators arranged so that they 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 strong cross-section and support each other. It a substantial increase in rigidity can be achieved.
- the wall thickness of the wall reduced at least in the area between the turbulators. This reduction in wall thickness is thereby made possible that the turbulators effect a stiffening of the wall. By reducing the wall thickness becomes the cooling efficiency increased again.
- the turbulators can be advantageous here used in casting the blade as metal feed channels become. The honeycomb structure is therefore easy to produce.
- the blade according to the invention can be used as a vane or as Blade of a rotary machine can be formed.
- FIG. 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 provided with guide vanes 13 and the rotor 12 provided with blades 14.
- the turbine 10 flows through a fluid according to arrow 15, the on the guide vanes 13 and blades 14 flows along and the rotor 12 is rotated about an axis 16.
- the temperature of the fluid is in many applications, in particular in the area of the first blade row (in FIG. 1) shown on the left), relatively high. It is therefore a cooling the guide vanes 13 and blades 14 are provided.
- the Flow of the cooling fluid is schematically indicated by the arrows 17, 18th indicated.
- Figure 2 shows schematically a broken-away view of a Guide vane 13.
- the vane 13 has curved outer walls 19, 20 on.
- the lying between the outer walls 19, 20 Interior is divided into two partitions 21 in total divided into three channels 22.
- In each of the channels 22 is a Insert 25 used.
- the middle channel 22 is not drawn.
- the two outer walls 19, 20 are in each of the channels 22 with a number of horizontal ribs 24 provided.
- the horizontal ribs 24 extend along the walls 19, 20 and extend down to the dividing walls 21. Between the horizontal ribs 24 turbulators 23 are arranged.
- the inserts 25 touch the horizontal ribs 24th
- the cooling fluid in particular cooling air, is an interior space 26 the inserts 25 supplied.
- the inserts 25 are with a number provided by openings 27 through which the cooling fluid in the space between the outer walls 19, 20 and the insert 25 leaves. Subsequently, the cooling fluid flows along the outer walls 19, 20 to exit openings 28 in the Walls 19, 20. This flow is schematic with the arrow 30 is 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 29th
- cooling fluid bounces first on the outer walls 19, 20 and leads there to a Impingement cooling. Then it flows along the outer walls 19, 20 up to the outlet openings 28, so that a convection cooling is reached. After emerging from the outlet openings 28, a film of the cooling fluid forms at the Outside of the outer walls 19, 20, so that also a film cooling is made available. It results in a significant improved cooling.
- the front edge of the vane shown on the left in Figure 2 13 is additionally provided with a direct impingement cooling.
- the insert 25 has further openings for this impingement cooling 36 on, just behind the front edge of the Guide vane 13 'are arranged.
- the cooling medium overflows these openings 36 directly from and provides a targeted cooling the leading edge of the vane 13 ready.
- the associated insert 25 is provided with a further opening 37. Through this opening 37 cooling fluid passes directly into a narrow Gap 38 between the outer walls 19, 20 and causes there a film cooling.
- Figures 3 to 5 show details of the inside the outer wall 19.
- the horizontal ribs 24 are substantially perpendicular to a longitudinal axis 31 of the vane 13. They are arranged parallel to each other. Between Horizontal ribs 24 are arranged just turbulators 23, which merge into one another and into the horizontal ribs 24.
- the leading edge 33 of the horizontal ribs 24 goes in the middle Channel 22 in the partition 21 via.
- left channel 22 is the leading edge 33 at some distance the foremost discharge openings 28 are arranged.
- Each two horizontal ribs 24 limit together with the Outer wall 19 and the insert 25, a chamber 32.
- the cooling fluid enters through the openings 27 of the insert 25 in this chamber 32 on. Then it flows according to arrow 30 to the Outlet openings 28.
- the openings 27 are in this case on the one end of the chamber 32 and the outlet openings 28 on the arranged at the other end. This will change the route that the Cooling fluid sweeps while flowing along the outer wall 19, maximized. This results in a maximum convection cooling.
- the effect of convection cooling is provided by the turbulators 23 still reinforced, since these heat exchange between the outer wall 19 and the cooling fluid improve.
- the chambers 32 can be differently charged with the cooling fluid become. This will be about a variation of the number and / or the size of the openings 27 of the insert 25 In this way, individual chambers 32 targeted stronger or weaker than others are cooled. The cooling can thus targeted along the longitudinal axis 31 of the 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 this case, that they form polygons. In Figure 3 are as an example Triangles and shown in Figure 6 as examples diamonds.
- the stiffening achieved by the turbulators 23 allows a reduction of 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 at.
- FIG. 6 shows a plan view of the inside of the outer wall 19 in second embodiment.
- the turbulators 24 with respect to the longitudinal axis 31 'of Guide vane 13 inclined. Increased due to this inclination the length of the chambers 32 and thus the effect of convection cooling.
- straight Turbulators 23 are provided, each of which four to one Rhombus are summarized. The reduction of the wall thickness is schematically indicated in these diamonds with visible edges.
- the horizontal ribs 24 and turbulators 23 may alternatively or additionally provided with a blade 14 become.
- FIG. 7 and 8 show two embodiments of an insert 25.
- the Cooling fluid supplied from both ends 34, 35 of the insert and exits through the openings 27.
- Such an insert 25 can for example be used 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 is then fed only via the end 35.
- This insert will be 25 used in the other rows of blades, in each case only one end of the vane 13 or the blade 14th via the housing 11 and the rotor 12 with the Cooling fluid can be applied.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- FIG 1
- einen Längsschnitt durch eine Rotationsmaschine;
- FIG 2
- eine perspektivische, aufgebrochene Darstellung einer Schaufel;
- FIG 3
- eine Draufsicht auf die Innenseite einer Wand der Schaufel;
- FIG 4
- einen Schnitt längs der Linie IV-IV in Figur 3;
- FIG 5
- einen Schnitt längs der Linie V-V in Figur 3;
- FIG 6
- eine Ansicht ähnlich Figur 3 in zweiter Ausgestaltung;
- FIG 7
- eine schematische Darstellung eines Einsatzes in erster Ausgestaltung; und
- FIG 8
- eine Ansicht ähnlich Figur 7 in zweiter Ausgestaltung.
Claims (8)
- Turbinenschaufel (13; 14), mit mindestens einem Kanal (22), der von Wänden (19, 20, 21) begrenzt ist, wobei mindestens eine Wand (19; 20) eine Anzahl von Horizontalrippen (24) und Austrittsöffnungen (28) aufweist, wobei in mindestens einem Kanal (22) ein mit einem Kühlfluid beaufschlagbarer, mit Öffnungen (27) versehener Einsatz (25) eingefügt ist, der durch die Horizontalrippen (24) von den Wänden (19; 20) beabstandet ist, und diese berührt, wobei das Kühlfluid durch die Öffnungen (27) aus dem Einsatz (25) in eine von diesem durchströmbare Kammer (32) eintreten kann, die aus den Horizontalrippen (24), dem Einsatz (25) und der Wand (19; 20) gebildet wird,
dadurch gekennzeichnet, dass die Öffnungen (27) des Einsatzes (25) an einem ersten Ende der Kammern (32) und die Austrittsöffnungen (28) für das Kühlfluid in der Wand (19; 20) an einem zweiten Ende der Kammern (32) angeordnet sind, und dass zwischen den Horizontalrippen (24) Turbulatoren (23) zur Verbesserung des Wärmeaustausches zwischen der Wand (19; 20) und dem Kühlfluid vorgesehen sind. - Schaufel nach Anspruch 1,
dadurch gekennzeichnet, dass die Horizontalrippen (24) im wesentlichen senkrecht zu einer Längsachse (25) der Schaufel (13; 14) angeordnet sind. - Schaufel nach einem der Ansprüche 1 bis 2,
dadurch gekennzeichnet, dass der Einsatz (25) an einem Ende (34) verschlossen ist. - Schaufel nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass die Turbulatoren (23) zur Versteifung der Wand (19; 20) dienen und ineinander und in die Horizontalrippen (24) übergehen. - Schaufel nach einem der Ansprüche 1 bis 4,
dadurch gekennzeichnet, dass die Turbulatoren (23) im wesentlichen gerade ausgebildet sind. - Schaufel nach Anspruch 4 oder 5,
dadurch gekennzeichnet, dass Turbulatoren (23) derart angeordnet sind, dass sie zusammen mit den Horizontalrippen (24) nebeneinanderliegende Ausnehmungen in Form von Vielecken, insbesondere Dreiecken oder Rauten, bilden. - Schaufel nach Anspruch 5 oder 6,
dadurch gekennzeichnet, dass die Wandstärke (d) der Wand (19; 20) zumindest im Bereich zwischen den Turbulatoren (23) verringert ist. - Schaufel nach einem der Ansprüche 1 bis 7,
dadurch gekennzeichnet, dass die Schaufel als Leitschaufel (13) oder als Laufschaufel (14) einer Rotationsmaschine (10) ausgebildet ist.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP01919384A EP1266127B1 (de) | 2000-03-22 | 2001-03-12 | Kühlsystem für eine turbinenschaufel |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00106245A EP1136651A1 (de) | 2000-03-22 | 2000-03-22 | Kühlsystem für eine Turbinenschaufel |
EP00106245 | 2000-03-22 | ||
PCT/EP2001/002755 WO2001071163A1 (de) | 2000-03-22 | 2001-03-12 | Kühlsystem für eine turbinenschaufel |
EP01919384A EP1266127B1 (de) | 2000-03-22 | 2001-03-12 | Kühlsystem für eine turbinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1266127A1 EP1266127A1 (de) | 2002-12-18 |
EP1266127B1 true EP1266127B1 (de) | 2005-01-12 |
Family
ID=8168201
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00106245A Withdrawn EP1136651A1 (de) | 2000-03-22 | 2000-03-22 | Kühlsystem für eine Turbinenschaufel |
EP01919384A Expired - Lifetime EP1266127B1 (de) | 2000-03-22 | 2001-03-12 | Kühlsystem für eine turbinenschaufel |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00106245A Withdrawn EP1136651A1 (de) | 2000-03-22 | 2000-03-22 | Kühlsystem für eine Turbinenschaufel |
Country Status (6)
Country | Link |
---|---|
US (1) | US6769875B2 (de) |
EP (2) | EP1136651A1 (de) |
JP (1) | JP4637437B2 (de) |
CN (1) | CN1293285C (de) |
DE (1) | DE50105062D1 (de) |
WO (1) | WO2001071163A1 (de) |
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DE102020106135B4 (de) * | 2020-03-06 | 2023-08-17 | Doosan Enerbility Co., Ltd. | Strömungsmaschinenkomponente für eine gasturbine, strömungsmaschinenanordnung und gasturbine mit derselben |
CN114109515B (zh) * | 2021-11-12 | 2024-01-30 | 中国航发沈阳发动机研究所 | 一种涡轮叶片吸力面冷却结构 |
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US429677A (en) | 1890-06-10 | Whip-socket and rein-holder | ||
US3574481A (en) * | 1968-05-09 | 1971-04-13 | James A Pyne Jr | Variable area cooled airfoil construction for gas turbines |
BE755567A (fr) * | 1969-12-01 | 1971-02-15 | Gen Electric | Structure d'aube fixe, pour moteur a turbines a gaz et arrangement de reglage de temperature associe |
US4118146A (en) * | 1976-08-11 | 1978-10-03 | United Technologies Corporation | Coolable wall |
US4296779A (en) * | 1979-10-09 | 1981-10-27 | Smick Ronald H | Turbulator with ganged strips |
JPS60182304A (ja) * | 1984-02-29 | 1985-09-17 | Toshiba Corp | ガスタ−ビンの冷却翼 |
US5232343A (en) * | 1984-05-24 | 1993-08-03 | General Electric Company | Turbine blade |
JPS61187501A (ja) * | 1985-02-15 | 1986-08-21 | Hitachi Ltd | 流体冷却構造 |
US5405242A (en) | 1990-07-09 | 1995-04-11 | United Technologies Corporation | Cooled vane |
JPH04259603A (ja) * | 1991-02-14 | 1992-09-16 | Toshiba Corp | タービン静翼 |
EP0541207A1 (de) * | 1991-11-04 | 1993-05-12 | General Electric Company | Prallgekühltes Schaufelblatt mit einem die Blatthälften verbundendem Einsatz |
US5695321A (en) * | 1991-12-17 | 1997-12-09 | General Electric Company | Turbine blade having variable configuration turbulators |
US5468125A (en) * | 1994-12-20 | 1995-11-21 | Alliedsignal Inc. | Turbine blade with improved heat transfer surface |
DE19634238A1 (de) * | 1996-08-23 | 1998-02-26 | Asea Brown Boveri | Kühlbare Schaufel |
DE59706345D1 (de) | 1996-12-02 | 2002-03-21 | Siemens Ag | Turbinenschaufel sowie verwendung in einer gasturbinenanlage |
EP0905353B1 (de) * | 1997-09-30 | 2003-01-15 | ALSTOM (Switzerland) Ltd | Prallanordnung für ein konvektives Kühl- oder Heizverfahren |
SE512384C2 (sv) * | 1998-05-25 | 2000-03-06 | Abb Ab | Komponent för en gasturbin |
-
2000
- 2000-03-22 EP EP00106245A patent/EP1136651A1/de not_active Withdrawn
-
2001
- 2001-03-12 CN CNB018067905A patent/CN1293285C/zh not_active Expired - Fee Related
- 2001-03-12 JP JP2001569124A patent/JP4637437B2/ja not_active Expired - Fee Related
- 2001-03-12 WO PCT/EP2001/002755 patent/WO2001071163A1/de active IP Right Grant
- 2001-03-12 US US10/239,234 patent/US6769875B2/en not_active Expired - Lifetime
- 2001-03-12 EP EP01919384A patent/EP1266127B1/de not_active Expired - Lifetime
- 2001-03-12 DE DE50105062T patent/DE50105062D1/de not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
US20030049127A1 (en) | 2003-03-13 |
DE50105062D1 (de) | 2005-02-17 |
EP1136651A1 (de) | 2001-09-26 |
WO2001071163A1 (de) | 2001-09-27 |
CN1418284A (zh) | 2003-05-14 |
JP2003528246A (ja) | 2003-09-24 |
JP4637437B2 (ja) | 2011-02-23 |
US6769875B2 (en) | 2004-08-03 |
EP1266127A1 (de) | 2002-12-18 |
CN1293285C (zh) | 2007-01-03 |
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