EP2384393B1 - Aube refroidie pour turbine a gaz - Google Patents
Aube refroidie pour turbine a gaz Download PDFInfo
- Publication number
- EP2384393B1 EP2384393B1 EP10701389.8A EP10701389A EP2384393B1 EP 2384393 B1 EP2384393 B1 EP 2384393B1 EP 10701389 A EP10701389 A EP 10701389A EP 2384393 B1 EP2384393 B1 EP 2384393B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flow
- pressure
- trailing edge
- cooling
- flow direction
- 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 57
- 230000004888 barrier function Effects 0.000 claims description 23
- 230000000694 effects Effects 0.000 claims description 4
- 238000011144 upstream manufacturing Methods 0.000 claims 1
- 238000003491 array Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000013021 overheating 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
- F01D5/187—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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- 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
- F05D2240/304—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 trailing 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
Definitions
- the present invention relates to the field of gas turbines. It relates to a cooled blade for a gas turbine according to the preamble of claim 1.
- the invention aims to remedy this situation. It is therefore an object of the invention to provide a cooled blade for a gas turbine of the type mentioned, which avoids the disadvantages of previous blades and at the same time characterized by low aerodynamic losses and a significantly reduced consumption of cooling air.
- the object is solved by the entirety of the features of claim 1. It is essential for the inventive solution that the pressure-side wall ends in the flow direction to form a pressure-side lip at a distance from the trailing edge, such that the cooling air exits the interior of the pressure side, that the interior at a distance from the trailing edge by a Variety of parallel to the flow direction oriented ribs is divided into a plurality of parallel cooling channels, which cause a high pressure drop, and in which turbulators are arranged to increase the cooling effect, and that shortly before the exit of the cooling air from the interior in the flow path of the cooling air across distributed to the flow direction, a plurality of flow barriers are provided.
- the invention is characterized in that the linear density of the flow barriers is smaller than the linear density of the ribs.
- the flow barriers each have a teardrop-shaped edge contour, wherein the pointed end points in the flow direction.
- the invention is characterized in that between the cooling channels and the flow barriers in a two-dimensional grid arrangement, a plurality of pins is arranged, which extend transversely to the flow direction between the suction side and pressure side wall through the interior.
- the Figures 1 and 2 show the internal structure of the airfoil 24 of a blade 10 for a gas turbine according to an embodiment of the invention.
- the blade 10 has a (convex) suction side 15 and a (concave) pressure side 16, of which in Fig. 1 only the portions lying near the trailing edge 13 are shown.
- On the suction side 15, the airfoil 24 is delimited by a first wall 11, on the pressure side 16 by a second wall 12.
- the two walls 11, 12 enclose an interior space 14, which is flowed through by cooling air for cooling the airfoil 24.
- the hot gas of the turbine flows on the airfoil 24 in one of the (in Fig. 1 not shown) leading edge to the trailing edge 13 pointing flow direction 25 over.
- the cooling air flows in the same direction through the interior 14 and exits Bech the trailing edge 13 of the blade 10 from.
- the trailing edge 13 is formed by the end of the suction-side wall 11.
- the pressure-side wall 12 terminates at a distance in front of this trailing edge 13, so that the cooling air in the resulting gap on the pressure side 16 exits even before the trailing edge 13 and a film cooling the Trailing edge 13 causes.
- the staggered arrangement of the edges of the two walls 11 and 12 creates a particularly thin cooled trailing edge 13, which significantly reduces the aerodynamic losses at the trailing edge 13.
- the supplied inside the blade 10 cooling air is sent on its way to the trailing edge 13, first by a plurality of parallel, oriented in the flow direction 25 cooling channels 23, which are formed by axial ribs 17 between the two walls 11 and 12.
- cooling channels 23 turbulators 18 are arranged in the form of oblique ribs on the inner sides of the walls 11, 12, through which the heat exchange with the walls 11, 12 is increased.
- pins 19 On the cooling channels 23 follow distributed in a kind of lattice structure arranged pins 19 which, like the axial ribs 17, extend between the two walls 11, 12 and improve the cooling of the wall in this area.
- the cooling air passes through a single row of drop-shaped flow barriers 20 and then exits from the blade 10 between the pressure side lip 21 and the trailing edge 13 on the pressure side 16.
- the cross-sectional shape of these flow barriers 20 is not limited to a drop shape. Other forms of flow may be used on a case by case basis. If the flow in a certain direction or strength to be influenced, the flow barriers 20 are designed accordingly.
- the linear density of the flow barriers 20 is less than the linear density of the axial ribs 17. However, this is again not necessarily understand, because depending on the design, the density of the flow barriers 20 may be equal to or greater than the linear density of the axial ribs 17 are selected ,
- a series of film cooling holes 22 is additionally provided in front of the cooling channels 23, exits through the cooling air on the pressure side 16 and forms a cooling film there.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (4)
- Aube refroidie (10) pour une turbine à gaz, comprenant une pale (24) qui s'étend dans la direction d'écoulement (25) entre un bord avant et un bord arrière (13) et qui est limitée, sur le côté d'aspiration (15) et sur le côté de pression (16), par une paroi (11 ou 12), les parois (11, 12) définissant un espace interne (14), dans lequel de l'air de refroidissement s'écoule dans la direction d'écoulement (25) vers le bord arrière (13) et sort vers l'extérieur au niveau du bord arrière, la paroi côté pression (12) se terminant dans la direction d'écoulement (25) en formant une lèvre côté pression (21) à une certaine distance avant le bord arrière (13), de façon à ce que l'air de refroidissement sorte de l'espace interne (14) sur le côté de pression (16), à ce que l'espace interne (14) soit divisée, à une certaine distance avant le bord arrière (13), par une pluralité de nervures (17) orientées parallèlement à la direction d'écoulement (25) en une pluralité canaux de refroidissement (23) parallèles provoquant une chute de pression, dans lesquels sont en outre disposés des turbulateurs (18) afin d'augmenter l'action de refroidissement, et à ce que, peu avant la sortie de l'air de refroidissement de l'espace interne (14), soient disposées, dans le trajet d'écoulement de l'air de refroidissement, réparties transversalement par rapport à la direction d'écoulement, une pluralité de barrières d'écoulement (20), caractérisée en ce que la densité linéaire des barrières d'écoulement (20) est inférieure à la densité linéaire des nervures (17) et en ce que, entre les canaux de refroidissement (23) et les barrières d'écoulement (20), se trouve, dans une disposition de grille bidimensionnelle, une pluralité de broches (19) qui s'étendent à travers l'espace interne (14), transversalement par rapport à la direction d'écoulement (25) entre la paroi côté aspiration et la paroi côté pression.
- Aube refroidie selon la revendication 1, caractérisée en ce que les barrières d'écoulement (20) comprennent une section conforme à l'écoulement ou quasi conforme à l'écoulement.
- Aube refroidie selon les revendications 1 et/ou 2, caractérisée en ce que les barrières d'écoulement (20) présentent chacune un contour de bord en forme de goutte, l'extrémité pointue étant orientée dans la direction d'écoulement (25).
- Aube refroidie selon les revendications 1 à 3, caractérisée en ce que, en tant que turbulateurs (18), dans les canaux de refroidissement (23), sont prévues des nervures obliques sur les côtés interne de la paroi côté aspiration et de la paroi côté pression (11 ou 12).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH00142/09A CH700321A1 (de) | 2009-01-30 | 2009-01-30 | Gekühlte schaufel für eine gasturbine. |
PCT/EP2010/051112 WO2010086419A1 (fr) | 2009-01-30 | 2010-01-29 | Aube refroidie pour turbine à gaz |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2384393A1 EP2384393A1 (fr) | 2011-11-09 |
EP2384393B1 true EP2384393B1 (fr) | 2017-06-28 |
Family
ID=40602892
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10701389.8A Active EP2384393B1 (fr) | 2009-01-30 | 2010-01-29 | Aube refroidie pour turbine a gaz |
Country Status (6)
Country | Link |
---|---|
US (1) | US8721281B2 (fr) |
EP (1) | EP2384393B1 (fr) |
CH (1) | CH700321A1 (fr) |
ES (1) | ES2639735T3 (fr) |
RU (1) | RU2538978C2 (fr) |
WO (1) | WO2010086419A1 (fr) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8439628B2 (en) * | 2010-01-06 | 2013-05-14 | General Electric Company | Heat transfer enhancement in internal cavities of turbine engine airfoils |
EP2426317A1 (fr) * | 2010-09-03 | 2012-03-07 | Siemens Aktiengesellschaft | Aube de turbine pour une turbine à gaz |
US9249675B2 (en) * | 2011-08-30 | 2016-02-02 | General Electric Company | Pin-fin array |
US8840371B2 (en) * | 2011-10-07 | 2014-09-23 | General Electric Company | Methods and systems for use in regulating a temperature of components |
EP2682565B8 (fr) * | 2012-07-02 | 2016-09-21 | General Electric Technology GmbH | Pale refroidie pour une turbine à gaz |
GB201311333D0 (en) | 2013-06-26 | 2013-08-14 | Rolls Royce Plc | Component for use in releasing a flow of material into an environment subject to periodic fluctuations in pressure |
US10479014B2 (en) * | 2015-11-03 | 2019-11-19 | Discma Ag | Forming head with integrated seal pin/stretch rod and various sealing geometries |
JP6671149B2 (ja) * | 2015-11-05 | 2020-03-25 | 三菱日立パワーシステムズ株式会社 | タービン翼及びガスタービン、タービン翼の中間加工品、タービン翼の製造方法 |
RU171631U1 (ru) * | 2016-09-14 | 2017-06-07 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Охлаждаемая лопатка турбины |
RU2684355C1 (ru) * | 2018-07-05 | 2019-04-08 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Ротор турбины низкого давления (ТНД) газотурбинного двигателя (варианты), узел соединения вала ротора с диском ТНД, тракт воздушного охлаждения ротора ТНД и аппарат подачи воздуха на охлаждение лопаток ротора ТНД |
RU2691867C1 (ru) * | 2018-07-05 | 2019-06-18 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Способ охлаждения лопатки ротора турбины низкого давления (ТНД) газотурбинного двигателя и лопатка ротора ТНД, охлаждаемая этим способом |
CN109139128A (zh) * | 2018-10-22 | 2019-01-04 | 中国船舶重工集团公司第七0三研究所 | 一种船用燃气轮机高压涡轮导叶冷却结构 |
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 |
CN114607469A (zh) * | 2022-03-16 | 2022-06-10 | 中国联合重型燃气轮机技术有限公司 | 燃气轮机的叶片及燃气轮机 |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4303374A (en) * | 1978-12-15 | 1981-12-01 | General Electric Company | Film cooled airfoil body |
US5288207A (en) * | 1992-11-24 | 1994-02-22 | United Technologies Corporation | Internally cooled turbine airfoil |
RU2083851C1 (ru) * | 1993-02-03 | 1997-07-10 | Московский авиационный технологический институт им.К.Э.Циалковского | Охлаждаемая лопатка газовой турбины |
DE19963349A1 (de) | 1999-12-27 | 2001-06-28 | Abb Alstom Power Ch Ag | Schaufel für Gasturbinen mit Drosselquerschnitt an Hinterkante |
US6599092B1 (en) * | 2002-01-04 | 2003-07-29 | General Electric Company | Methods and apparatus for cooling gas turbine nozzles |
US6602047B1 (en) * | 2002-02-28 | 2003-08-05 | General Electric Company | Methods and apparatus for cooling gas turbine nozzles |
GB2411698A (en) * | 2004-03-03 | 2005-09-07 | Rolls Royce Plc | Coolant flow control in gas turbine engine |
US7121787B2 (en) * | 2004-04-29 | 2006-10-17 | General Electric Company | Turbine nozzle trailing edge cooling configuration |
RU2267616C1 (ru) * | 2004-05-21 | 2006-01-10 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Охлаждаемая лопатка турбины |
US7575414B2 (en) * | 2005-04-01 | 2009-08-18 | General Electric Company | Turbine nozzle with trailing edge convection and film cooling |
US7438527B2 (en) * | 2005-04-22 | 2008-10-21 | United Technologies Corporation | Airfoil trailing edge cooling |
-
2009
- 2009-01-30 CH CH00142/09A patent/CH700321A1/de not_active Application Discontinuation
-
2010
- 2010-01-29 EP EP10701389.8A patent/EP2384393B1/fr active Active
- 2010-01-29 WO PCT/EP2010/051112 patent/WO2010086419A1/fr active Application Filing
- 2010-01-29 RU RU2011135948/06A patent/RU2538978C2/ru not_active IP Right Cessation
- 2010-01-29 ES ES10701389.8T patent/ES2639735T3/es active Active
-
2011
- 2011-07-28 US US13/193,548 patent/US8721281B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
CH700321A1 (de) | 2010-07-30 |
ES2639735T3 (es) | 2017-10-30 |
EP2384393A1 (fr) | 2011-11-09 |
US8721281B2 (en) | 2014-05-13 |
RU2538978C2 (ru) | 2015-01-10 |
RU2011135948A (ru) | 2013-03-10 |
US20120020787A1 (en) | 2012-01-26 |
WO2010086419A1 (fr) | 2010-08-05 |
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