EP2384393A1 - Gekühlte schaufel für eine gasturbine - Google Patents
Gekühlte schaufel für eine gasturbineInfo
- Publication number
- EP2384393A1 EP2384393A1 EP10701389A EP10701389A EP2384393A1 EP 2384393 A1 EP2384393 A1 EP 2384393A1 EP 10701389 A EP10701389 A EP 10701389A EP 10701389 A EP10701389 A EP 10701389A EP 2384393 A1 EP2384393 A1 EP 2384393A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flow
- trailing edge
- cooling air
- interior
- cooling
- 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.)
- Granted
Links
- 238000001816 cooling Methods 0.000 claims abstract description 69
- 230000004888 barrier function Effects 0.000 claims abstract description 28
- 230000000694 effects Effects 0.000 claims abstract description 6
- 238000000034 method Methods 0.000 claims description 3
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 230000000903 blocking effect Effects 0.000 claims description 2
- 238000000265 homogenisation Methods 0.000 claims 1
- 238000011144 upstream manufacturing Methods 0.000 abstract 1
- 238000003491 array Methods 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
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
- Cooling air mass flow is controlled by a throttle device at the trailing edge.
- this type of cooling has the disadvantage that comparatively thick trailing edges are required, resulting in considerable aerodynamic losses.
- 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.
- An embodiment of 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.
- a further embodiment of 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 cooled blade is also operated so that in the interior of such a blade axial ribs act, which produce an increase in the surface area for a heat transfer between the walls and the cooling air flow. Furthermore, there are advantages if in the cooling channels (23) rib-shaped turbulators are ornotch or Fix, which increase the heat transfer coefficient in the associated region of action.
- FIG. 1 shows the detail of a cross section through a blade according to an embodiment of the invention.
- 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 in the vicinity of the trailing edge 13 are shown.
- the airfoil 24 is bounded by a first wall 1 1, on the pressure side 16 by a second wall 12.
- the two walls 1 1, 12 surround an interior 14 which is flowed through to cool the airfoil 24 of cooling air.
- the hot gas of the turbine flows past the airfoil 24 in a flow direction 25 pointing from the leading edge (not shown in FIG. 1) to the trailing edge 13.
- 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 1 1.
- 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 1 1 and 12 creates a particularly thin cooled trailing edge 13, which significantly reduces the aerodynamic losses at the trailing edge 13.
- the inside of the blade 10 supplied cooling air is on its way to
- Trailing edge 13 initially passed through a plurality of parallel, oriented in the flow direction 25 cooling channels 23, which are formed by axial ribs 17 between the two walls 1 1 and 12.
- cooling channels 23 1 12 turbulators 18 are arranged in the form of oblique ribs on the inner sides of the walls, through which the heat exchange with the walls 1 1, 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, between the two walls 1 1, 12 extend 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.
- the axial ribs 17 allow a cooling arrangement for a relatively wide aerodynamic profile.
- the cooling channels 23 between the axial Ribs 17 have a sufficiently small cross-sectional area to achieve high flow velocities even for large spaces between the suction side and the pressure side.
- the rib-shaped turbulators 18 in the cooling channels 23 additionally increase the heat transfer coefficient.
- the pin arrays 19 are used in an area where the space between the suction side and the pressure side is already lower. • Drop-shaped flow barriers 20 are inserted to the lateral
- a series of film cooling holes 22 on the pressure side 16 allows a reduction in the temperature in the rear part of the pressure side 16th
Abstract
Description
Claims
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 (de) | 2009-01-30 | 2010-01-29 | Gekühlte schaufel für eine gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2384393A1 true EP2384393A1 (de) | 2011-11-09 |
EP2384393B1 EP2384393B1 (de) | 2017-06-28 |
Family
ID=40602892
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10701389.8A Active EP2384393B1 (de) | 2009-01-30 | 2010-01-29 | Gekühlte schaufel für eine gasturbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US8721281B2 (de) |
EP (1) | EP2384393B1 (de) |
CH (1) | CH700321A1 (de) |
ES (1) | ES2639735T3 (de) |
RU (1) | RU2538978C2 (de) |
WO (1) | WO2010086419A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
Families Citing this family (12)
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 (de) * | 2010-09-03 | 2012-03-07 | Siemens Aktiengesellschaft | Turbinenschaufel für eine Gasturbine |
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 (de) | 2012-07-02 | 2016-09-21 | General Electric Technology GmbH | Gekühlte Schaufel für eine Gasturbine |
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 |
EP3370945B1 (de) * | 2015-11-03 | 2019-11-13 | Discma AG | Formkopf mit integrierter dichtung/reckdorn und verschiedenen dichtungsgeometrien |
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 |
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 |
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 |
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 |
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 ES ES10701389.8T patent/ES2639735T3/es active Active
- 2010-01-29 EP EP10701389.8A patent/EP2384393B1/de active Active
- 2010-01-29 WO PCT/EP2010/051112 patent/WO2010086419A1/de active Application Filing
- 2010-01-29 RU RU2011135948/06A patent/RU2538978C2/ru not_active IP Right Cessation
-
2011
- 2011-07-28 US US13/193,548 patent/US8721281B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2010086419A1 * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
Also Published As
Publication number | Publication date |
---|---|
RU2011135948A (ru) | 2013-03-10 |
CH700321A1 (de) | 2010-07-30 |
US20120020787A1 (en) | 2012-01-26 |
EP2384393B1 (de) | 2017-06-28 |
RU2538978C2 (ru) | 2015-01-10 |
ES2639735T3 (es) | 2017-10-30 |
WO2010086419A1 (de) | 2010-08-05 |
US8721281B2 (en) | 2014-05-13 |
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