EP3762587B1 - Pale d'aube pour une aube de turbine - Google Patents
Pale d'aube pour une aube de turbine Download PDFInfo
- Publication number
- EP3762587B1 EP3762587B1 EP19723730.8A EP19723730A EP3762587B1 EP 3762587 B1 EP3762587 B1 EP 3762587B1 EP 19723730 A EP19723730 A EP 19723730A EP 3762587 B1 EP3762587 B1 EP 3762587B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- aerofoil
- cooling holes
- height
- series
- blade
- 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.)
- Active
Links
- 238000001816 cooling Methods 0.000 claims description 81
- 239000002826 coolant Substances 0.000 claims description 7
- 230000000694 effects Effects 0.000 description 5
- 238000011835 investigation Methods 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000005057 refrigeration Methods 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
- F01D5/186—Film 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
-
- 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
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
Definitions
- the invention relates to a blade for a turbine blade, comprising a leading edge against which a hot gas can flow, from which a suction side wall and a pressure side wall extend to a trailing edge of the blade, the blade extending in a transverse direction thereto from a root end with a blade height of 0 % to a tip end with an airfoil height of 100%, with at least two rows of cooling holes arranged along the leading edge and having a first distance from one another to be measured perpendicular to the leading edge.
- Such a turbine blade is, for example, from EP 2 154 333 A2 famous.
- the cooling holes arranged in the leading edge serve to produce a cooling protective film over the leading edge during operation of a gas turbine equipped therewith, in order to counteract the incoming flow of hot gas.
- the cooling holes are therefore also referred to as film cooling holes, which are also known in English as “shower head film cooling holes” due to their dense arrangement.
- the airfoil divides the incoming hot gas flow at the leading edge into two partial flows, one of which flows along the suction side of the airfoil and the other part along the pressure side.
- the location of the flow distribution on the blade profile is called the stagnation point, since in the idealized sense no cross flow occurs there.
- film cooling holes are arranged on both sides of the front edge or the previously determined stagnation line, in order to prevent the hot gas flow impinging there from coming into too close contact with the component wall.
- the invention is based on the object of providing an airfoil for a turbine blade which is designed in the best possible way for different operating conditions of a gas turbine, in particular in order to achieve adequate cooling with the longest possible service life of the airfoil when using an acceptable amount of coolant .
- This object is achieved with a blade of the type mentioned at the outset in that the at least two rows of cooling holes are arranged at least partially along the leading edge on a wavy line.
- the wavy line is slightly curved, without changing the sign of its curvature, such that the cooling holes of each of the at least two rows are arranged further downstream at both the root end and the tip end of the airfoil than the cooling holes of the corresponding row at half-height of the airfoil.
- the invention is based on the finding that the actual hot gas flow direction depends on the design of the Airfoil used flow direction can differ on the one hand due to different operating modes of the gas turbine. The deviations can occur due to a change in the load output compared to the nominal load.
- the stagnation point of a blade profile in the area of the leading edge can oscillate due to flow effects which are caused by a guide blade arranged upstream of the moving blade. The oscillation of the stagnation point of a blade profile leads to a locally increased surface temperature of the blade airfoil, which can be counteracted effectively with the invention.
- the invention now proposes providing at least two rows of cooling holes in the area of the leading edge, which are at least partially arranged on a curved wavy line.
- the cooling holes are shifted towards the pressure side or the suction side in relation to the oscillating stagnation point of the relevant blade profile.
- an area is determined for each blade profile in which the stagnation point can occur.
- Each of these areas is defined by two end points, from which an average stagnation point can then be determined.
- the two cooling holes are then positioned in such a way that the best possible cooling is achieved. This allows the cooling effect to be optimized locally.
- the amount of coolant required for cooling can be reduced. The reduced consumption of coolant contributes to the increase in efficiency of the gas turbine during operation.
- each of the at least two rows are located near the root end and near the tip end of the airfoil further downstream than the cooling holes of the corresponding half-airfoil row.
- the wavy line then extends between these points without one Changing the sign of its curvature so that it is only slightly curved.
- this variant represents a more favorable cooling configuration, especially for guide vanes, since with these vanes the stagnation point shift occurs more at the ends of the airfoil than in its center and also towards the suction side.
- the maximum displacement of the relevant cooling holes near the ends of the airfoil is then only a few millimeters, in particular 2 mm, towards the suction side, compared to the position of the cooling holes of the same row at half the airfoil height, ie at 50% of the airfoil height.
- the first distance between the at least two rows of cooling holes varies along the leading edge, so that the first distance is different for some blade heights.
- the local cooling capacity of the turbine blade in the area of the leading edge can be adapted locally to the individual temperature load.
- a blade profile can be determined by examining a cross section, which profile is known to have the shape of a curved drop.
- Each blade profile therefore has a nose radius in the area of the leading edge, with the blade profiles having a first distance between the at least two rows at the level of cooling holes, the size of which is in the range between 0.4 times and 0.7 times the associated nose radius located.
- the effectiveness of the cooling depends on the distance between the cooling holes of different rows and the curvature of the leading edge, the so-called nose radius, as well as the length of the camberline, the number of blades and the turning of the blade profile. It was then found that a particularly efficient cooling of the leading edge region can be achieved if the first distance between the cooling holes of different rows that are at the same blade height lies within the claimed interval.
- the first distance is smallest at half the height of the airfoil and increases towards the two ends.
- the increase is particularly moderate.
- each cooling hole preferably has a throttle cross section that adjusts the coolant flow, the throttle cross sections of some cooling holes being of different sizes.
- the throttle cross sections of the cooling holes in the region of half the blade height are particularly preferably larger than the throttle cross section of the cooling holes in the region further away from half the blade height.
- This configuration is based on the finding that at half the blade height and in the regions immediately adjacent thereto, there is a somewhat greater cooling requirement than in those regions of the leading edge which are further away from half the blade height.
- the configuration in which the at least two rows of cooling holes are arranged on both sides of a central stagnation point line of the incoming hot gas flow is particularly preferred.
- the hot gas flow is divided into a part flowing to the pressure side and a part flowing to the suction side, which is diverted to both sides, so that the component wall underneath is particularly efficiently protected from the high temperatures of the hot gas due to the arrangement of the cooling holes on both sides.
- a further but shortened row of essentially evenly spaced cooling holes is provided on the pressure side in addition to the at least two rows, with the length of the further row between 50% and 60% of the airfoil height and the further row of cooling holes is arranged substantially centrally between the two ends of the airfoil.
- the further row is arranged essentially centrally as long as it is divided by half the airfoil height into two parts, the shorter part of which is not shorter than 1/3 of the length of the further row.
- the length of the further row of cooling holes is recorded in the same direction as the airfoil height.
- the airfoil is preferably part of a turbine blade, in particular a turbine guide blade of a stationary gas turbine.
- FIG 1 a turbine rotor blade 10 is shown in a perspective view.
- the turbine blade 10 successively comprises an essentially fir-tree-shaped blade root 12, which is adjoined by a hot-gas platform 14 as the end wall.
- an airfoil 16 On its surface facing the hot gas S, an airfoil 16 according to a first example is arranged.
- the airfoil 16 is known to include a leading edge 18 and a trailing edge 20 between which a suction sidewall 17 and a pressure sidewall 19 extend. In a direction transverse thereto, the airfoil 16 extends from a root end 21 at 0% airfoil height to a tip end 23 at 100% airfoil height.
- Two rows R 1 , R 2 of cooling holes 22 are arranged along the leading edge 18 .
- the two rows R 1 , R 2 run along a wavy line with a plurality of wave troughs and wave crests and are simultaneously arranged on both sides of a central stagnation point line 24
- a second example is in figure 2 shown.
- a region is straight, followed by a bulbous section.
- the two rows R 1 , R 2 of cooling holes 22 are arranged in the first, radially inner area in such a way that they are arranged parallel to the leading edge 18 on both sides thereof.
- This first range B 1 extends between 0% and about 40% airfoil height.
- a second area B 2 is provided radially on the outside. This ends at an airfoil height of about 75%.
- the cooling holes 22 of both rows R 1 , R 2 move further towards the pressure side with increasing height until they have reached the maximum displacement away from the leading edge 18 at about 75% airfoil height.
- the cooling holes 22 of the two rows R 1 , R 2 shift back again in the direction of the front edge 18 .
- cooling holes 22 are shown only schematically as circles, with their throttle cross sections being shown schematically by circles of different sizes.
- the cooling holes 22 can be film cooling holes that have a diffuser-like opening. Its diffuser can even be designed with a profile.
- a distance A between the cooling holes 22 to be measured transversely on the surface of the airfoil 16 can also be of different sizes at different airfoil heights.
- FIG. 12 also shows, as a blade profile 28, the cross section through the airfoil 16 of the first example according to FIG figure 1 .
- the blade profile center line is provided with reference number 30 .
- the foremost arranged point of the blade profile center line 30 defines the leading edge 18.
- the stagnation point 25 can be slightly shifted away from the leading edge 18 towards the pressure side 19 or towards the suction side 17.
- the (middle) stagnation points 25 of each blade profile section which can be determined at any blade height, together form the stagnation point line 24.
- the nose radius is denoted by R.
- FIG 4 An embodiment of the invention is in figure 4 shown. It shows a perspective view of a turbine blade configured as a guide blade, with the blade root 12 comprising two hook-shaped rails for fastening the blade to a blade carrier (not shown in any more detail).
- a platform 14 is provided at both the root end 21 and the tip end 23 of the airfoil to limit the flow path.
- the airfoil 16 extends along its airfoil height.
- the at least two rows R 1 , R 2 of cooling holes 18 are also arranged analogously: starting with the cooling holes at half the height of the airfoil, within each row R 1 , R 2 the cooling holes arranged with decreasing spacing towards the platforms 14 are arranged further on the suction side .
- the stagnation point line 24 is slightly curved without changing the sign of its curvature.
- a further but shortened row of substantially evenly spaced cooling holes 18 is provided on the pressure side next to the two rows R 1 , R 2 .
- This further row R 3 is according to this embodiment in the middle between the two platforms 14 and the two ends 21, 23 and extends over a length of only 55% of the blade height. It is therefore shorter than the two rows R 1 , R 2 .
- the invention relates to an airfoil 16 for a turbine blade 10, comprising a leading edge 18 against which a hot gas S can flow, from which a suction sidewall 17 and a pressure sidewall 19 extend to a trailing edge 20 of the airfoil 16, the airfoil 16 being in a transverse direction thereto extending from a root end 21 with an airfoil height of 0% to a tip end 23 with an airfoil height of 100%, with two rows R 1 , R 2 of cooling holes 22 arranged along the leading edge, the mutually perpendicular to the leading edge 18 to be detected have first distance A.
- the two rows R 1 , R 2 of cooling holes 22 be arranged at least partially along the leading edge 18 on a wavy line.
- the wavy line 24 is slightly curved without changing the sign of its curvature such that the cooling holes 18 of each of the at least two rows (Ri, R2) are arranged further on the suction side than the cooling holes at both the root end 21 and the tip end 23 of the airfoil 18 of the corresponding row (Ri, R2) at half blade height.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (9)
- Corps (16) creux d'une aube de turbine, comprenant un bord avant sur lequel peut passer un gaz (S) chaud et duquel s'étend une paroi (17) d'extrados et une paroi (19) d'intrados vers un bord (20) arrière du corps (16) de l'aube, le corps (16) de l'aube s'étendant dans une direction perpendiculaire à cela d'une extrémité du côté de l'emplanture en ayant une hauteur de corps d'aube de 0% à une extrémité (23) du côté de la pointe en ayant une hauteur de corps d'aube de 100%,comprenant au moins deux rangées (R1, R2) de trous (22) de refroidissement, qui sont disposées le long du bord (18) avant et qui ont entre elles une première distance (A), à prendre perpendiculairement au bord (18) avant, les au moins deux rangées (R1, R2) de trous (22) de refroidissement étant disposées au moins en partie sur une ligne ondulée le long du bord (18) avant,caractérisé en ce quela ligne (24) ondulée est, sans modification du signe de sa courbure, incurvée légèrement de manière à ce que les trous (22) de refroidissement de chacune des au moins deux rangées (R1, R2) soient disposés à la fois, à l'extrémité (21) du côté de l'emplanture et à l'extrémité (23) du côté de la pointe du corps de l'autre, davantage du côté de l'extrados que les trous (22) de refroidissement des rangées (R1, R2) correspondantes à mi-hauteur du corps de l'aube.
- Corps d'aube suivant la revendication 1,
dans lequel la première distance (A) entre les au moins deux rangées (R1, R2) varie le long du bord (18) avant. - Corps d'aube suivant l'une des revendications précédentes, dans lequel, pour chaque hauteur du corps de l'aube, un profil (28) d'aube peut être déterminé, lequel profil (28) d'aube a, dans la partie du bord (18) avant, un rayon (R) de bec, dans lequel les profils de l'aube ont, au niveau des trous (22) de refroidissement, une première distance (A) entre les au moins deux rangées (R1, R2), dont la dimension est dans la plage comprise entre 0,4 fois et 0,7 fois le rayon du bec associé.
- Corps d'aube suivant l'une des revendications précédentes, dans lequel la première distance (A) est la plus petite à mi-hauteur du corps de l'aube et augmente vers les deux extrémités.
- Corps d'aube suivant l'une des revendications précédentes, dans lequel chaque trou de refroidissement a une surface transversale d'étranglement réglant le débit de fluide de refroidissement, les sections transversales d'étranglement de certains trous (22) de refroidissement ayant des dimensions différentes.
- Corps d'aube suivant l'une des revendications précédentes, dans lequel les sections transversales d'étranglement des trous (22) de refroidissement sont plus grandes dans la partie de la mi-hauteur du corps de l'aube que la section transversale d'étranglement des trous (22) de refroidissement dans la partie plus loin de la mi-hauteur du corps de l'aube.
- Corps d'aube suivant l'une des revendications précédentes, dans lequel les au moins deux rangées (R1, R2) de trous (22) de refroidissement sont disposées des deux côtés d'une ligne (24) de points d'arrêt du courant de gaz chaud arrivant.
- Corps d'aube suivant l'une des revendications précédentes, dans lequel il est prévu, outre les au moins deux rangées (R1, R2), au voisinage de l'intrados, une autre rangée (R3) de trous (22) de refroidissement, une longueur de l'autre rangée (R3) représentant entre 50% et 60% de la hauteur du corps de l'aube et l'autre rangée (R3) étant disposée sensiblement au milieu entre les deux extrémités (21, 23) du corps (16) de l'aube.
- Aube (10) d'une turbine à gaz fixe,
comprenant un corps (16) d'aube suivant l'une des revendications précédentes, conformée de préférence en aube directrice de turbine.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP18170731.6A EP3564483A1 (fr) | 2018-05-04 | 2018-05-04 | Pale d'aube pour une aube de turbine |
PCT/EP2019/061354 WO2019211427A1 (fr) | 2018-05-04 | 2019-05-03 | Pale d'aube pour une aube de turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3762587A1 EP3762587A1 (fr) | 2021-01-13 |
EP3762587B1 true EP3762587B1 (fr) | 2022-04-13 |
Family
ID=62116325
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18170731.6A Withdrawn EP3564483A1 (fr) | 2018-05-04 | 2018-05-04 | Pale d'aube pour une aube de turbine |
EP19723730.8A Active EP3762587B1 (fr) | 2018-05-04 | 2019-05-03 | Pale d'aube pour une aube de turbine |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18170731.6A Withdrawn EP3564483A1 (fr) | 2018-05-04 | 2018-05-04 | Pale d'aube pour une aube de turbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US11326458B2 (fr) |
EP (2) | EP3564483A1 (fr) |
JP (1) | JP7124122B2 (fr) |
KR (1) | KR102505046B1 (fr) |
CN (1) | CN112074652B (fr) |
WO (1) | WO2019211427A1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3564483A1 (fr) * | 2018-05-04 | 2019-11-06 | Siemens Aktiengesellschaft | Pale d'aube pour une aube de turbine |
JP7224928B2 (ja) * | 2019-01-17 | 2023-02-20 | 三菱重工業株式会社 | タービン動翼及びガスタービン |
KR102507408B1 (ko) | 2022-11-11 | 2023-03-08 | 터보파워텍(주) | 3d프린팅에 의한 가스터빈 블레이드의 에어포일 수리 공정 |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6869268B2 (en) * | 2002-09-05 | 2005-03-22 | Siemens Westinghouse Power Corporation | Combustion turbine with airfoil having enhanced leading edge diffusion holes and related methods |
US7217094B2 (en) | 2004-10-18 | 2007-05-15 | United Technologies Corporation | Airfoil with large fillet and micro-circuit cooling |
EP1898051B8 (fr) * | 2006-08-25 | 2017-08-02 | Ansaldo Energia IP UK Limited | Aube de turbine à gaz avec refroidissement du bord d'attaque |
US8105030B2 (en) * | 2008-08-14 | 2012-01-31 | United Technologies Corporation | Cooled airfoils and gas turbine engine systems involving such airfoils |
CN104508247B (zh) * | 2012-08-06 | 2017-05-31 | 通用电气公司 | 涡轮翼型及其制成方法 |
WO2014137686A1 (fr) * | 2013-03-04 | 2014-09-12 | United Technologies Corporation | Refroidissement de turbine à gaz à profil aérodynamique haute portance dans une zone de stagnation |
US10329923B2 (en) * | 2014-03-10 | 2019-06-25 | United Technologies Corporation | Gas turbine engine airfoil leading edge cooling |
US9976423B2 (en) * | 2014-12-23 | 2018-05-22 | United Technologies Corporation | Airfoil showerhead pattern apparatus and system |
US10240462B2 (en) | 2016-01-29 | 2019-03-26 | General Electric Company | End wall contour for an axial flow turbine stage |
US11286787B2 (en) | 2016-09-15 | 2022-03-29 | Raytheon Technologies Corporation | Gas turbine engine airfoil with showerhead cooling holes near leading edge |
EP3564483A1 (fr) * | 2018-05-04 | 2019-11-06 | Siemens Aktiengesellschaft | Pale d'aube pour une aube de turbine |
-
2018
- 2018-05-04 EP EP18170731.6A patent/EP3564483A1/fr not_active Withdrawn
-
2019
- 2019-05-03 WO PCT/EP2019/061354 patent/WO2019211427A1/fr unknown
- 2019-05-03 CN CN201980030091.4A patent/CN112074652B/zh active Active
- 2019-05-03 US US17/048,582 patent/US11326458B2/en active Active
- 2019-05-03 KR KR1020207034682A patent/KR102505046B1/ko active IP Right Grant
- 2019-05-03 JP JP2020561773A patent/JP7124122B2/ja active Active
- 2019-05-03 EP EP19723730.8A patent/EP3762587B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
KR102505046B1 (ko) | 2023-03-06 |
CN112074652B (zh) | 2023-05-02 |
US20210156263A1 (en) | 2021-05-27 |
KR20210002709A (ko) | 2021-01-08 |
EP3564483A1 (fr) | 2019-11-06 |
EP3762587A1 (fr) | 2021-01-13 |
JP2021522444A (ja) | 2021-08-30 |
WO2019211427A1 (fr) | 2019-11-07 |
JP7124122B2 (ja) | 2022-08-23 |
CN112074652A (zh) | 2020-12-11 |
US11326458B2 (en) | 2022-05-10 |
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