WO2001000965A1 - Heissgasbeaufschlagbares bauteil, insbesondere turbinenschaufel - Google Patents
Heissgasbeaufschlagbares bauteil, insbesondere turbinenschaufel Download PDFInfo
- Publication number
- WO2001000965A1 WO2001000965A1 PCT/EP2000/005525 EP0005525W WO0100965A1 WO 2001000965 A1 WO2001000965 A1 WO 2001000965A1 EP 0005525 W EP0005525 W EP 0005525W WO 0100965 A1 WO0100965 A1 WO 0100965A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- turbulators
- wall
- inclination
- walls
- turbine blade
- Prior art date
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
-
- 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
Definitions
- Component subject to hot gas in particular turbine blade
- the present invention relates to a component which can be subjected to hot gas, in particular a turbine blade, with at least one channel which can be acted upon by a cooling fluid and is delimited by two first, mutually opposite walls which are used to improve the heat transfer between the component and the cooling fluid or several turbulators are provided, the turbulators of the first wall and the turbulators of the second wall having the same direction of inclination and being inclined at an angle of inclination with respect to a flow direction of the cooling fluid.
- Such a component in the form of a gas turbine blade is known from EP 0 758 932 B1 or US Pat. No. 5,695,321, in particular FIG. 9A.
- the known gas turbine nozzle is hollow and has at least one channel which can be acted upon by a cooling fluid. As a result, the entry temperature of the gas into the gas turbine can be increased, so that the efficiency is improved.
- the channel is delimited by two first opposite walls.
- One or more turbulators are provided on these walls, which improve the heat transfer between the gas turbine blade and the cooling fluid.
- the turbulators of both walls have the same direction of inclination and are inclined by the same angle of inclination with respect to a flow direction of the cooling fluid.
- the channel can be narrowed locally by the turbulators. This occurs in particular when the two opposite walls and thus the turbulators have different lengths. The turbulators of the two walls then face each other at the same height. The canal is narrowed locally at this point. As a rule, the wall is provided with several turbulators this narrowing occurs repeatedly. This does not result in a cooling fluid flow with a substantially constant cross-section which oscillates uniformly from one wall to the other wall. Rather, the cross-section available for the cooling fluid is constantly changed, so that pressure losses occur.
- US 5,413,458 shows a gas turbine guide vane with a platform.
- the platform is provided with a flow chamber in which turbulators are arranged in such a way that cooling fluid flowing through the flow flow is directed to the corners of the platform.
- the object of the present invention is therefore to provide a component which can be subjected to hot gas and in which there is an essentially uniform channel cross section over the entire length of the turbulators without local constrictions.
- this object is achieved in a component of the type mentioned above in that the angle of inclination of the turbulators of the first wall is different from the angle of inclination of the turbulators of the second wall.
- the different angles of inclination of the turbulators of the first and second walls enable the turbulators to be arranged without local constrictions.
- the turbulators are no longer in sections due to the different inclination angles. Rather, the turbulators of one wall can be arranged virtually completely aging with respect to the turbulators of the other wall over their entire length. This results in a uniform cross-section of the channel for the cooling fluid in the direction of the length of the turbulators.
- the cross-sectional changes occurring in the known constructions and the pressure losses associated therewith are substantially reduced.
- the length of the first wall is advantageously greater than the length of the second wall. As a result, different cross-sections can be selected for the component which can be acted upon with gas.
- the two first walls are curved.
- a cross section in the form of an aerofoil profile for the component which can be subjected to hot gas can be selected through the curved walls. This cross section is particularly necessary for use as a turbine blade.
- the angle of inclination of the turbulators of the first wall is greater than the angle of inclination of the turbulators of the second wall.
- the length of the turbulators of the first wall is thereby reduced, while the length of the turbulators of the second wall is increased.
- the angles of inclination are chosen in such a way that the turbulators are arranged on the two walls practically completely alternating with each other. This leads to an essentially uniform cross section of the channel over the entire length of the turbulators.
- Two further walls are advantageously provided to delimit the channel and connect the first two walls to one another.
- the interior of the component which can be subjected to hot gas is divided by these two further walls into a plurality of, for example three, channels which are connected to one another.
- the cooling fluid flows through the three channels in succession.
- the first channel in which the temperature of the cooling fluid is at its lowest, is advantageously arranged on the flow side of the gas turbine blade.
- the two further walls are arranged at an angle to one another. This angular arrangement enables these further walls to be aligned essentially perpendicular to the first two walls. This alignment leads to an optimization of the leadership of the
- the angular position of the other two walls is also better suited for absorbing loads when used as a gas turbine blade.
- the turbulators are straight. This straight training facilitates the demolding of the component according to the invention and reduces the cost of manufacture.
- Turbulators curved. With curved turbulators, a complete alternation of the turbulators is possible over their entire length. The pressure losses due to cross-sectional changes are minimized as far as possible.
- FIG. 1 shows a longitudinal section through a gas turbine blade along the line I-I in Figure 2;
- FIG. 2 shows a cross section through a gas turbine blade along the line II-II in FIG. 1;
- FIG. 3 shows a view in the direction of arrow III from FIG. 2;
- Figure 4 is a view in the direction of arrow IV of Figure 2;
- Figure 5 is a section along the line V-V in Figure 2; 6 shows a section along the line VI-VI in Figure 2;
- Figure 7 is a view similar to Figure 5 in a gas turbine blade according to the prior art
- Figure 8 is a view similar to Figure 6 in a gas turbine blade according to the prior art
- FIG. 9 is a view similar to FIG. 1 for a gas turbine blade according to the invention.
- FIG. 10 shows a view similar to FIG. 9 for a gas turbine blade according to the prior art.
- a gas turbine blade 10 is shown in longitudinal section and in cross section.
- the inside of the gas turbine blade 10 has a cooling duct 11 which is divided into three individual ducts 12, 13, 14 which run essentially parallel to one another.
- Each of the three channels 12, 13, 14 is delimited by the two outer walls 16, 17 and one or two partition walls 18, 19. To improve the heat transfer between the cooling fluid and the outer walls 16, 17, these are provided with turbulators 20, 21.
- the two outer walls 16, 17 are curved and have a different length.
- the outer wall 16 forms the suction side of the gas turbine blade 10
- the outer wall 17 forms the pressure side.
- the two partition walls 18, 19, which delimit the central channel 13, connect the outer walls 16, 17 to one another. These partitions 18, 19 are arranged at an angle to one another and are essentially perpendicular to the outer walls 16, 17. This achieves an optimization in the routing of the cooling fluid. Due to the angular position of the partition walls 18, 19 perpendicular to the outer walls 16, 17, loads on the gas turbine blade 10 that occur during operation can be better absorbed.
- the turbulators 20, 21 have the same direction of inclination and are inclined by an angle of inclination with respect to a flow direction 22 of the cooling fluid. This is shown for the turbulator 20 with the angle of inclination ⁇ in FIG. 1.
- the direction of flow 22 of the cooling fluid in the individual channels 12, 13, 14 runs essentially parallel to the partition walls 18, 19.
- the turbulators 20 are also longer than the turbulators 21.
- the turbulators 20 have the same angle of inclination with respect to the flow direction 22 of the Cooling fluids on like the turbulators 21 m in a projection parallel to one of the two walls 18, 19.
- the turbulators 20, 21 can be opposed in sections at the same height.
- FIG. 7 and FIG. 8 show a section along the line V-V and VI-VI in FIG. 2 in a gas turbine blade 10 according to the prior art.
- the turbulators 20, 21 of the two outer walls 16, 17 are arranged alternately to one another on the left-hand side of the channel 13 in FIG. 2, which is shown in cross section in FIG.
- the cooling fluid can flow uniformly from one outer wall 16 to the other in this area
- Pendulum outer wall 17 In the area on the right in FIG. 2, which is shown in cross section in FIG. 8, the two turbulators 20, 21 lie opposite one another at the same height. An evenly fluctuating cooling fluid flow is no longer possible. Rather, they form between the turbulators 20, 21
- the invention provides that the turbulators 20, 21 with the same direction of inclination but different inclinations to arrange relative to the direction of flow 22.
- FIGS. 3 and 4 which each show views in the direction of the partition walls 18, 19.
- the turbulators 20, 21 have the same inclination direction on both outer walls 16, 17, namely running from bottom left to top right.
- the outer wall 17 m is not shown in FIGS. 3 and 4.
- the partition 18 appears undistorted in width. Due to the viewing direction, the partition 19 is correspondingly distorted and therefore shown wider.
- the turbulators 20 extend from the dividing wall 18 to the dividing wall 19 along the first wall 16. In the view according to FIG. 3, they are therefore partially covered by the dividing wall 19 in the right area.
- the turbulators 21 extend along the outer wall 17 between the partition walls 18, 19. Due to the different lengths of the outer walls 16, 17 and the angular position of the partition walls 18, 19, the turbulators 20, 21 have a different length.
- the angle of inclination ⁇ of the turbulators of the first outer wall 16 is chosen to be larger than the angle of inclination ⁇ of the turbulators 21 of the second outer wall
- FIG. 4 shows a view in the direction of view of the partition 19. Accordingly, the partition 19 appears undistorted, while the partition 18 appears wider due to the direction of view.
- the angle difference ⁇ between the turbulators 20, 21 due to the different inclination angles ⁇ , ß is clearly recognizable.
- Figures 3 and 4 show the position of the turbulators 20, 21 from different angles. Because of these different viewing angles, there are different angles of inclination and angle differences in FIGS. 3 and 4, which are correspondingly designated as ⁇ ⁇ 2 , ⁇ i, ⁇ 2 and ⁇ i, ⁇ 2 .
- the type and size of the distortion depend on the individual case.
- the turbulators 20, 21 Due to the different inclination angles ⁇ , ⁇ , but the same direction of inclination of the turbulators 20, 21, the turbulators alternate almost completely. As shown in FIGS. 3 and 4, the turbulators 20, 21 do not lie opposite one another at any point. The cooling fluid can therefore swing freely from one outer wall 16 to the other outer wall 17. This applies both near the partition 18 and near the partition 19.
- FIGS. 5 and 6 show the conditions near the dividing walls 18, 19 in accordance with the section lines V-V and VI-VI in FIG. 2. It clearly shows that the
- State-of-the-art constriction 23 no longer exists in the gas turbine blade 10 according to the invention. This is achieved by the different inclination angles ⁇ , ⁇ of the turbulators 20, 21 with the same direction of inclination.
- straight turbulators 20, 21 are used, as shown in FIGS. 3 and 4, the gas turbine blade 10 can be manufactured economically.
- a complete alternation of the turbulators 20, 21 is only possible with straight turbulators with parallel partition walls 18 and 19.
- the distance between the turbulators 20, 21 near the partition 18 is different from the distance near the partition 19.
- curved turbulators 20, 21 complete alternating in the middle can be achieved. This is shown in particular in FIG. 9.
- curved turbulators 20, 21 it is also possible to achieve a uniform reduction along the entire length of the turbulators 20, 21. Stand d between the turbulators 20, 21 achieve. This results in an optimal oscillation of the cooling fluid flow between the two outer walls 16, 17.
- FIG. 10 For comparison, the mutual position of the turbulators 20, 21 in a gas turbine blade 10 according to the prior art is shown in FIG. 10 if the partition walls 18, 19 are not are parallel and the removal of the partitions 18 is carried out. It clearly shows that the turbulators 20, 21 are located opposite one another near the partition 19. The constriction 23 shown in FIG. 8 is thereby formed.
- FIGS. 9 and 10 show a schematic projection of the channel 13 into the plane along the section line I-I in FIG. 2.
- the arrangement of the turbulators 20, 21 according to the invention results in the uniform course shown in FIG.
- the apparently different inclination angles of the turbulators 20, 21 in FIG. 10 and the apparently identical inclination angles in FIG. 9 are due to the distortion caused by the projection. Because of this distortion, the turbulators 20, 21 appear to be the same length both in FIG. 9 and in FIG. 10 despite their actually different lengths.
- the invention enables a uniform cross section of the channel 11 over the entire length of the turbulators 20, 21.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00942078A EP1192333B1 (de) | 1999-06-28 | 2000-06-15 | Heissgasbeaufschlagbares bauteil, insbesondere turbinenschaufel |
US10/030,236 US6641362B1 (en) | 1999-06-28 | 2000-06-15 | Component that can be subjected to hot gas, especially in a turbine blade |
DE50002464T DE50002464D1 (de) | 1999-06-28 | 2000-06-15 | Heissgasbeaufschlagbares bauteil, insbesondere turbinenschaufel |
JP2001506354A JP4489336B2 (ja) | 1999-06-28 | 2000-06-15 | 高温ガスを受ける構造部品 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP99112370 | 1999-06-28 | ||
EP99112370.4 | 1999-06-28 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2001000965A1 true WO2001000965A1 (de) | 2001-01-04 |
Family
ID=8238439
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2000/005525 WO2001000965A1 (de) | 1999-06-28 | 2000-06-15 | Heissgasbeaufschlagbares bauteil, insbesondere turbinenschaufel |
Country Status (5)
Country | Link |
---|---|
US (1) | US6641362B1 (de) |
EP (1) | EP1192333B1 (de) |
JP (1) | JP4489336B2 (de) |
DE (1) | DE50002464D1 (de) |
WO (1) | WO2001000965A1 (de) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1944469A2 (de) * | 2007-01-03 | 2008-07-16 | United Technologies Corporation | Turbinenblatt-Nockenstreifenausrichtung |
WO2013076109A1 (de) | 2011-11-21 | 2013-05-30 | Siemens Aktiengesellschaft | Kühlbares heissgasbauteil für eine gasturbine |
EP2146055B2 (de) † | 2008-07-17 | 2022-01-19 | Ansaldo Energia S.P.A. | Dichtungselement für Gasturbinen, Gasturbine mit besagtem Dichtungselement und Verfahren zum Kühlen besagten Dichtungselements |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7513745B2 (en) * | 2006-03-24 | 2009-04-07 | United Technologies Corporation | Advanced turbulator arrangements for microcircuits |
US7641445B1 (en) | 2006-12-01 | 2010-01-05 | Florida Turbine Technologies, Inc. | Large tapered rotor blade with near wall cooling |
US7955053B1 (en) | 2007-09-21 | 2011-06-07 | Florida Turbine Technologies, Inc. | Turbine blade with serpentine cooling circuit |
US8376706B2 (en) * | 2007-09-28 | 2013-02-19 | General Electric Company | Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method |
US8042268B2 (en) * | 2008-03-21 | 2011-10-25 | Siemens Energy, Inc. | Method of producing a turbine component with multiple interconnected layers of cooling channels |
US20090324841A1 (en) * | 2008-05-09 | 2009-12-31 | Siemens Power Generation, Inc. | Method of restoring near-wall cooled turbine components |
EP2954168B1 (de) * | 2013-02-05 | 2019-07-03 | United Technologies Corporation | Gasturbinenmotorkomponente mit gekrümmtem turbulator |
WO2015073092A2 (en) * | 2013-09-05 | 2015-05-21 | United Technologies Corporation | Gas turbine engine airfoil turbulator for airfoil creep resistance |
CN106481366B (zh) * | 2015-08-28 | 2019-03-26 | 中国航发商用航空发动机有限责任公司 | 冷却叶片和燃气涡轮 |
US11085304B2 (en) | 2018-06-07 | 2021-08-10 | Raytheon Technologies Corporation | Variably skewed trip strips in internally cooled components |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4627480A (en) * | 1983-11-07 | 1986-12-09 | General Electric Company | Angled turbulence promoter |
US5413458A (en) | 1994-03-29 | 1995-05-09 | United Technologies Corporation | Turbine vane with a platform cavity having a double feed for cooling fluid |
US5695321A (en) | 1991-12-17 | 1997-12-09 | General Electric Company | Turbine blade having variable configuration turbulators |
EP0825332A1 (de) * | 1996-08-23 | 1998-02-25 | Asea Brown Boveri AG | Kühlbare Schaufel |
EP0758932B1 (de) | 1994-04-19 | 1998-06-24 | United Technologies Corporation | Gekühlte gasturbinenschaufel |
EP0852285A1 (de) * | 1997-01-03 | 1998-07-08 | General Electric Company | Wirbelelementkonstruktion für Kühlkanäle eines Gasturbinenrotorschaufelblattes |
EP0892150A1 (de) * | 1997-07-14 | 1999-01-20 | Abb Research Ltd. | Kühlsystem für den Hinterkantenbereich einer hohlen Gasturbinenschaufel |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5695322A (en) * | 1991-12-17 | 1997-12-09 | General Electric Company | Turbine blade having restart turbulators |
US5681144A (en) * | 1991-12-17 | 1997-10-28 | General Electric Company | Turbine blade having offset turbulators |
US5700132A (en) * | 1991-12-17 | 1997-12-23 | General Electric Company | Turbine blade having opposing wall turbulators |
-
2000
- 2000-06-15 EP EP00942078A patent/EP1192333B1/de not_active Expired - Lifetime
- 2000-06-15 US US10/030,236 patent/US6641362B1/en not_active Expired - Lifetime
- 2000-06-15 WO PCT/EP2000/005525 patent/WO2001000965A1/de active IP Right Grant
- 2000-06-15 DE DE50002464T patent/DE50002464D1/de not_active Expired - Lifetime
- 2000-06-15 JP JP2001506354A patent/JP4489336B2/ja not_active Expired - Fee Related
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4627480A (en) * | 1983-11-07 | 1986-12-09 | General Electric Company | Angled turbulence promoter |
US5695321A (en) | 1991-12-17 | 1997-12-09 | General Electric Company | Turbine blade having variable configuration turbulators |
US5413458A (en) | 1994-03-29 | 1995-05-09 | United Technologies Corporation | Turbine vane with a platform cavity having a double feed for cooling fluid |
EP0758932B1 (de) | 1994-04-19 | 1998-06-24 | United Technologies Corporation | Gekühlte gasturbinenschaufel |
EP0825332A1 (de) * | 1996-08-23 | 1998-02-25 | Asea Brown Boveri AG | Kühlbare Schaufel |
EP0852285A1 (de) * | 1997-01-03 | 1998-07-08 | General Electric Company | Wirbelelementkonstruktion für Kühlkanäle eines Gasturbinenrotorschaufelblattes |
EP0892150A1 (de) * | 1997-07-14 | 1999-01-20 | Abb Research Ltd. | Kühlsystem für den Hinterkantenbereich einer hohlen Gasturbinenschaufel |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1944469A2 (de) * | 2007-01-03 | 2008-07-16 | United Technologies Corporation | Turbinenblatt-Nockenstreifenausrichtung |
EP1944469A3 (de) * | 2007-01-03 | 2013-11-13 | United Technologies Corporation | Turbinenblatt-Nockenstreifenausrichtung |
EP2146055B2 (de) † | 2008-07-17 | 2022-01-19 | Ansaldo Energia S.P.A. | Dichtungselement für Gasturbinen, Gasturbine mit besagtem Dichtungselement und Verfahren zum Kühlen besagten Dichtungselements |
WO2013076109A1 (de) | 2011-11-21 | 2013-05-30 | Siemens Aktiengesellschaft | Kühlbares heissgasbauteil für eine gasturbine |
EP2602439A1 (de) | 2011-11-21 | 2013-06-12 | Siemens Aktiengesellschaft | Kühlbares Heißgasbauteil für eine Gasturbine |
Also Published As
Publication number | Publication date |
---|---|
DE50002464D1 (de) | 2003-07-10 |
JP4489336B2 (ja) | 2010-06-23 |
EP1192333B1 (de) | 2003-06-04 |
US6641362B1 (en) | 2003-11-04 |
JP2003503620A (ja) | 2003-01-28 |
EP1192333A1 (de) | 2002-04-03 |
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