EP2519713B1 - Aube à ventilation intérieure - Google Patents
Aube à ventilation intérieure Download PDFInfo
- Publication number
- EP2519713B1 EP2519713B1 EP10798151.6A EP10798151A EP2519713B1 EP 2519713 B1 EP2519713 B1 EP 2519713B1 EP 10798151 A EP10798151 A EP 10798151A EP 2519713 B1 EP2519713 B1 EP 2519713B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- trailing edge
- cavities
- partition
- closest
- 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
- 238000009423 ventilation Methods 0.000 title description 11
- 238000005192 partition Methods 0.000 claims description 17
- 239000000112 cooling gas Substances 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 9
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 1
- 230000002301 combined effect Effects 0.000 description 1
- 230000010339 dilation Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000750 progressive effect Effects 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
- F05D2260/60—Fluid transfer
- F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
Definitions
- the subject of this invention is an internally ventilated blade.
- the blades of the turbomachines can be equipped with cooling devices by gas ventilation, such as relatively fresh gas withdrawn from the main circulation stream at the compressors; it then circulates to cavities dug inside the blades and comes out through holes that open in particular to the intrados and the trailing edge, where the lower external pressure promotes the flow of gas.
- gas ventilation such as relatively fresh gas withdrawn from the main circulation stream at the compressors; it then circulates to cavities dug inside the blades and comes out through holes that open in particular to the intrados and the trailing edge, where the lower external pressure promotes the flow of gas.
- the object of the invention is to solve this particular problem.
- the invention in its most general form, relates to a blade comprising internal cavities for circulation of cooling gas, the cavities being separated by partitions, one of the partitions, the closest to a trailing edge of the blade, having a greater inclination towards the trailing edge from a height of at least 70% of the blade, counted from a platform at the top of the blade to an outer edge radius (this measure favors refreshing the corner of the blade by better ventilation of the trailing edge, for the reasons that will be given later) characterized in that one of the cavities, delimited towards the trailing edge of the blade by said partition the closer to the trailing edge of the blade, comprises a series of holes leading to a side face of the blade, said holes open into said cavity through orifices arranged on a line parallel to said partition. This improvement also favors the refresh of the dawn corner, this time by a better ventilation of the lateral faces (intrados or extrados).
- the greater inclination is advantageously progressive, giving the partition a rounded overall shape.
- the Figures 1 and 2 have a blade (1), which is joined to a foot (2) housed in a disk not shown and provided with a platform (3).
- the blade (1) is hollow and pierced with multiple cavities (4), separated from each other by partitions (5) extending essentially radially from the root (2) to the apex (11) of the blade ( 1).
- partitions (5) extending essentially radially from the root (2) to the apex (11) of the blade ( 1).
- a cavity (6) closest to the trailing edge (7) of the blade (1), a cavity (8) adjacent to the preceding one, and a partition (9) separating them will be distinguished. which is the partition closest to the trailing edge (7).
- Ventilation gas arrives in the cavities (4) (and (6) and (8)) by their origin (10) in the foot (2) from another region of the machine to which the blade (1 belongs, and rises towards the summit (11) of dawn (1); it leaves the cavities progressively through holes (12) opening on the intrados (13) and / or the extrados (22) of the blade (1), other holes (14) (represented in FIGS. Figures 3 and 4 ) opening at the top (11), and finally by other holes (15), from the single cavity (6), which open at the trailing edge (7).
- the ventilation of the apex (11) of the blade (1) is more difficult since the holes (14) are located at the end of the cavities (4) and the flow of the gas ventilation is lower and has less pressure; another disadvantageous circumstance is that the top (11) is composed of a thin outer edge (16) extending on the extrados side and the intrados side of the blade, thus forming a recessed cavity called "tub" ( 17).
- the ridge (16) limits the flow of hot gas between the blade tip and the housing opposite, and constitutes a wear zone when the blade, under the combined effect of the dilation thermal and centrifugal, extends and touches the housing vis-à-vis.
- the bathtub (17) and the ridge (16) are difficult to cool regions; the situation is especially critical in the upper corner (18) of the blade (1) adjacent to the trailing edge (7), where the cavity (6) is the narrowest.
- the partition (here 9 ') closest to the trailing edge (7) is straight like the others to simplify the manufacture of the blade and is generally completely radial direction.
- the inventors have noted the existence of a low speed recirculation zone (19) in the cavity (6) at the connection between the partition (9 ') and the wall of the bath base (17).
- the low dynamic pressure of the ventilation gas at this point makes it unnecessary to create upper holes to ventilate the top (11), so that the end of the bath (17) is not ventilated at all; and it is found that the holes (15) leading to the trailing edge (7) which are closest to the apex (11), typically the three or four closest ones, receive a flow particularly low due to the low pressure of the gas.
- the specific layout of the invention consists in providing the partition (9) closest to the trailing edge (7) with an upper end (20) more inclined towards the trailing edge (7) than the rest of the partition (9), and advantageously moreover in addition inclined with a rounded shape and an almost regular connection to the wall of the bath base (17).
- the upper part (20) can start at 80%, possibly 70% of the height of the blade (1) counted from the platform (3) to the outer edge, that is to say to the wall bathtub bottom (17).
- the other partitions remain straight.
- the low speed recirculation zone (19) disappears; the ventilation gas is better guided towards the bores (15) close to the top (11), and its pressure is increased, which also increases the flow rate through these bores (15) higher; the holes (12) leading to the intrados (13) (or the extrados) from the second cavity (8) can be moved towards the trailing edge (7), their orifices (21) in the second cavity (8) occupying a line parallel to the upper portion (20); at least one additional crown piercing (14 ') can be provided by widening the second cavity (8) at the top (the first cavity (6) being, in the design shown here as in the previous design, normally devoid of holes (12) and (14) at the top because of the greater difficulties of ventilation).
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Building Environments (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0959698A FR2954798B1 (fr) | 2009-12-31 | 2009-12-31 | Aube a ventilation interieure |
PCT/EP2010/070933 WO2011080319A1 (fr) | 2009-12-31 | 2010-12-30 | Aube a ventilation interieure |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2519713A1 EP2519713A1 (fr) | 2012-11-07 |
EP2519713B1 true EP2519713B1 (fr) | 2013-11-06 |
Family
ID=42133483
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10798151.6A Active EP2519713B1 (fr) | 2009-12-31 | 2010-12-30 | Aube à ventilation intérieure |
Country Status (9)
Country | Link |
---|---|
US (1) | US20120282110A1 (zh) |
EP (1) | EP2519713B1 (zh) |
JP (1) | JP5661798B2 (zh) |
CN (1) | CN102713160B (zh) |
BR (1) | BR112012015844A2 (zh) |
CA (1) | CA2785377C (zh) |
FR (1) | FR2954798B1 (zh) |
RU (1) | RU2554397C2 (zh) |
WO (1) | WO2011080319A1 (zh) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20150361798A1 (en) * | 2013-02-12 | 2015-12-17 | United Technologies Corporation | Fan blade including external cavities |
US9771816B2 (en) * | 2014-05-07 | 2017-09-26 | General Electric Company | Blade cooling circuit feed duct, exhaust duct, and related cooling structure |
JP6353131B1 (ja) | 2017-06-29 | 2018-07-04 | 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 |
Family Cites Families (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6001A (en) * | 1849-01-02 | Manufacture of lampblack and colophane | ||
BE794194A (fr) * | 1972-01-18 | 1973-07-18 | Bbc Sulzer Turbomaschinen | Aube mobile refroidie pour des turbines a gaz |
SU444888A1 (ru) * | 1973-01-03 | 1974-09-30 | Предприятие П/Я В-2504 | Охлаждаема лопатка турбины |
US4173120A (en) * | 1977-09-09 | 1979-11-06 | International Harvester Company | Turbine nozzle and rotor cooling systems |
US4416585A (en) * | 1980-01-17 | 1983-11-22 | Pratt & Whitney Aircraft Of Canada Limited | Blade cooling for gas turbine engine |
FR2476207A1 (fr) * | 1980-02-19 | 1981-08-21 | Snecma | Perfectionnement aux aubes de turbines refroidies |
SU1228559A1 (ru) * | 1981-11-13 | 1996-10-10 | Г.П. Нагога | Рабочая лопатка газовой турбины |
US4515526A (en) * | 1981-12-28 | 1985-05-07 | United Technologies Corporation | Coolable airfoil for a rotary machine |
GB2165315B (en) * | 1984-10-04 | 1987-12-31 | Rolls Royce | Improvements in or relating to hollow fluid cooled turbine blades |
DE4443696A1 (de) * | 1994-12-08 | 1996-06-13 | Abb Management Ag | Gekühlte Turbinenschaufel |
DE19921644B4 (de) * | 1999-05-10 | 2012-01-05 | Alstom | Kühlbare Schaufel für eine Gasturbine |
EP1167689A1 (de) * | 2000-06-21 | 2002-01-02 | Siemens Aktiengesellschaft | Konfiguration einer kühlbaren Turbinenschaufel |
US6471479B2 (en) * | 2001-02-23 | 2002-10-29 | General Electric Company | Turbine airfoil with single aft flowing three pass serpentine cooling circuit |
US6554575B2 (en) * | 2001-09-27 | 2003-04-29 | General Electric Company | Ramped tip shelf blade |
FR2833298B1 (fr) | 2001-12-10 | 2004-08-06 | Snecma Moteurs | Perfectionnements apportes au comportement thermique du bord de fuite d'une aube de turbine haute-pression |
FR2834015B1 (fr) | 2001-12-20 | 2004-08-13 | Danfoss Maneurop S A | Clapet pour compresseur a spirale |
US6942449B2 (en) * | 2003-01-13 | 2005-09-13 | United Technologies Corporation | Trailing edge cooling |
US7014424B2 (en) * | 2003-04-08 | 2006-03-21 | United Technologies Corporation | Turbine element |
US7008179B2 (en) * | 2003-12-16 | 2006-03-07 | General Electric Co. | Turbine blade frequency tuned pin bank |
RU2263791C1 (ru) * | 2004-03-19 | 2005-11-10 | Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "САЛЮТ" (ФГУП "ММПП "САЛЮТ") | Охлаждаемая рабочая лопатка турбины |
US7198468B2 (en) * | 2004-07-15 | 2007-04-03 | Pratt & Whitney Canada Corp. | Internally cooled turbine blade |
US7431562B2 (en) * | 2005-12-21 | 2008-10-07 | General Electric Company | Method and apparatus for cooling gas turbine rotor blades |
EP1895096A1 (de) * | 2006-09-04 | 2008-03-05 | Siemens Aktiengesellschaft | Gekühlte Turbinenlaufschaufel |
US7607891B2 (en) * | 2006-10-23 | 2009-10-27 | United Technologies Corporation | Turbine component with tip flagged pedestal cooling |
US8079814B1 (en) * | 2009-04-04 | 2011-12-20 | Florida Turbine Technologies, Inc. | Turbine blade with serpentine flow cooling |
-
2009
- 2009-12-31 FR FR0959698A patent/FR2954798B1/fr not_active Expired - Fee Related
-
2010
- 2010-12-30 BR BR112012015844A patent/BR112012015844A2/pt not_active IP Right Cessation
- 2010-12-30 EP EP10798151.6A patent/EP2519713B1/fr active Active
- 2010-12-30 WO PCT/EP2010/070933 patent/WO2011080319A1/fr active Application Filing
- 2010-12-30 CN CN201080060268.4A patent/CN102713160B/zh active Active
- 2010-12-30 US US13/519,339 patent/US20120282110A1/en not_active Abandoned
- 2010-12-30 RU RU2012132632/06A patent/RU2554397C2/ru active
- 2010-12-30 JP JP2012546450A patent/JP5661798B2/ja active Active
- 2010-12-30 CA CA2785377A patent/CA2785377C/fr active Active
Also Published As
Publication number | Publication date |
---|---|
US20120282110A1 (en) | 2012-11-08 |
JP2013516563A (ja) | 2013-05-13 |
JP5661798B2 (ja) | 2015-01-28 |
CA2785377A1 (fr) | 2011-07-07 |
CN102713160A (zh) | 2012-10-03 |
RU2012132632A (ru) | 2014-02-10 |
BR112012015844A2 (pt) | 2019-09-24 |
FR2954798B1 (fr) | 2012-03-30 |
CA2785377C (fr) | 2017-02-21 |
WO2011080319A1 (fr) | 2011-07-07 |
CN102713160B (zh) | 2016-05-18 |
EP2519713A1 (fr) | 2012-11-07 |
FR2954798A1 (fr) | 2011-07-01 |
RU2554397C2 (ru) | 2015-06-27 |
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