WO2011080319A1 - Aube a ventilation interieure - Google Patents

Aube a ventilation interieure Download PDF

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Publication number
WO2011080319A1
WO2011080319A1 PCT/EP2010/070933 EP2010070933W WO2011080319A1 WO 2011080319 A1 WO2011080319 A1 WO 2011080319A1 EP 2010070933 W EP2010070933 W EP 2010070933W WO 2011080319 A1 WO2011080319 A1 WO 2011080319A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
trailing edge
cavities
ventilation
closest
Prior art date
Application number
PCT/EP2010/070933
Other languages
English (en)
French (fr)
Inventor
Erwan Daniel Botrel
Jacques Auguste Amédée BOURY
Original Assignee
Snecma
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Snecma filed Critical Snecma
Priority to CA2785377A priority Critical patent/CA2785377C/fr
Priority to JP2012546450A priority patent/JP5661798B2/ja
Priority to EP10798151.6A priority patent/EP2519713B1/fr
Priority to CN201080060268.4A priority patent/CN102713160B/zh
Priority to BR112012015844A priority patent/BR112012015844A2/pt
Priority to US13/519,339 priority patent/US20120282110A1/en
Priority to RU2012132632/06A priority patent/RU2554397C2/ru
Publication of WO2011080319A1 publication Critical patent/WO2011080319A1/fr

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
    • 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 out through holes which 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 out through holes which open in particular to the intrados and the trailing edge, where the lower external pressure promotes the flow of gas.
  • the invention 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
  • the greater inclination is advantageously progressive, giving the partition a rounded overall shape.
  • FIG. 1 and FIG. 2 are general views of the blade according to the invention
  • FIG. 3 is a detail showing an earlier design improved by the invention
  • FIG. 4 is a corresponding detail of a design conforming to
  • FIGS 1 and 2 show a blade (1), which is joined to a foot (2) housed in a disc 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 in a substantially radial direction from the foot (2) to the apex (11) of the blade ( 1).
  • partitions (5) extending in a substantially radial direction from the foot (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 on the extrados (22) of the blade (1), other bores (14) (represented in FIGS. 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 and on 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 dawn and is generally of 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 arrangement of the invention is to provide the partition (9) closest to the trailing edge (7) with an upper end (20) more inclined towards the trailing edge (7) the remainder of the partition (9), and advantageously more and more 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)
PCT/EP2010/070933 2009-12-31 2010-12-30 Aube a ventilation interieure WO2011080319A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
CA2785377A CA2785377C (fr) 2009-12-31 2010-12-30 Aube a ventilation interieure
JP2012546450A JP5661798B2 (ja) 2009-12-31 2010-12-30 内部通気ブレード
EP10798151.6A EP2519713B1 (fr) 2009-12-31 2010-12-30 Aube à ventilation intérieure
CN201080060268.4A CN102713160B (zh) 2009-12-31 2010-12-30 内部通风叶片
BR112012015844A BR112012015844A2 (pt) 2009-12-31 2010-12-30 "pá de ventilação interna"
US13/519,339 US20120282110A1 (en) 2009-12-31 2010-12-30 Inner ventilation blade
RU2012132632/06A RU2554397C2 (ru) 2009-12-31 2010-12-30 Лопатка с внутренним вентилированием

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0959698 2009-12-31
FR0959698A FR2954798B1 (fr) 2009-12-31 2009-12-31 Aube a ventilation interieure

Publications (1)

Publication Number Publication Date
WO2011080319A1 true WO2011080319A1 (fr) 2011-07-07

Family

ID=42133483

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2010/070933 WO2011080319A1 (fr) 2009-12-31 2010-12-30 Aube a ventilation interieure

Country Status (9)

Country Link
US (1) US20120282110A1 (ja)
EP (1) EP2519713B1 (ja)
JP (1) JP5661798B2 (ja)
CN (1) CN102713160B (ja)
BR (1) BR112012015844A2 (ja)
CA (1) CA2785377C (ja)
FR (1) FR2954798B1 (ja)
RU (1) RU2554397C2 (ja)
WO (1) WO2011080319A1 (ja)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2956626B1 (en) * 2013-02-12 2019-11-20 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

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3885609A (en) * 1972-01-18 1975-05-27 Oskar Frei Cooled rotor blade for a gas turbine
US4173120A (en) * 1977-09-09 1979-11-06 International Harvester Company Turbine nozzle and rotor cooling systems
EP0034961A1 (fr) * 1980-02-19 1981-09-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Perfectionnement aux aubes de turbines refroidies
US4416585A (en) * 1980-01-17 1983-11-22 Pratt & Whitney Aircraft Of Canada Limited Blade cooling for gas turbine engine
US4515526A (en) * 1981-12-28 1985-05-07 United Technologies Corporation Coolable airfoil for a rotary machine
US4604031A (en) * 1984-10-04 1986-08-05 Rolls-Royce Limited Hollow fluid cooled turbine blades
DE4443696A1 (de) * 1994-12-08 1996-06-13 Abb Management Ag Gekühlte Turbinenschaufel
FR2833298A1 (fr) 2001-12-10 2003-06-13 Snecma Moteurs Perfectionnements apportes au comportement thermique du bord de fuite d'une aube de turbine haute-pression
FR2834015A1 (fr) 2001-12-20 2003-06-27 Danfoss Maneurop S A Clapet pour compresseur a spirale
US20030156943A1 (en) * 2000-06-21 2003-08-21 Michael Strassberger Configuration of a coolable turbine blade
EP1437483A1 (en) * 2003-01-13 2004-07-14 United Technologies Corporation Trailing edge cooling of a turbine airfoil
US20060013688A1 (en) * 2004-07-15 2006-01-19 Papple Michael L C Internally cooled turbine blade
EP1918522A2 (en) * 2006-10-23 2008-05-07 United Technologies Corporation Turbine component

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US6001A (en) * 1849-01-02 Manufacture of lampblack and colophane
SU444888A1 (ru) * 1973-01-03 1974-09-30 Предприятие П/Я В-2504 Охлаждаема лопатка турбины
SU1228559A1 (ru) * 1981-11-13 1996-10-10 Г.П. Нагога Рабочая лопатка газовой турбины
DE19921644B4 (de) * 1999-05-10 2012-01-05 Alstom Kühlbare Schaufel für eine Gasturbine
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
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
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
US8079814B1 (en) * 2009-04-04 2011-12-20 Florida Turbine Technologies, Inc. Turbine blade with serpentine flow cooling

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3885609A (en) * 1972-01-18 1975-05-27 Oskar Frei Cooled rotor blade for a gas turbine
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
EP0034961A1 (fr) * 1980-02-19 1981-09-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Perfectionnement aux aubes de turbines refroidies
US4515526A (en) * 1981-12-28 1985-05-07 United Technologies Corporation Coolable airfoil for a rotary machine
US4604031A (en) * 1984-10-04 1986-08-05 Rolls-Royce Limited Hollow fluid cooled turbine blades
DE4443696A1 (de) * 1994-12-08 1996-06-13 Abb Management Ag Gekühlte Turbinenschaufel
US20030156943A1 (en) * 2000-06-21 2003-08-21 Michael Strassberger Configuration of a coolable turbine blade
FR2833298A1 (fr) 2001-12-10 2003-06-13 Snecma Moteurs Perfectionnements apportes au comportement thermique du bord de fuite d'une aube de turbine haute-pression
FR2834015A1 (fr) 2001-12-20 2003-06-27 Danfoss Maneurop S A Clapet pour compresseur a spirale
EP1437483A1 (en) * 2003-01-13 2004-07-14 United Technologies Corporation Trailing edge cooling of a turbine airfoil
US20060013688A1 (en) * 2004-07-15 2006-01-19 Papple Michael L C Internally cooled turbine blade
EP1918522A2 (en) * 2006-10-23 2008-05-07 United Technologies Corporation Turbine component

Also Published As

Publication number Publication date
RU2012132632A (ru) 2014-02-10
JP2013516563A (ja) 2013-05-13
EP2519713B1 (fr) 2013-11-06
CA2785377A1 (fr) 2011-07-07
EP2519713A1 (fr) 2012-11-07
RU2554397C2 (ru) 2015-06-27
CN102713160B (zh) 2016-05-18
CN102713160A (zh) 2012-10-03
BR112012015844A2 (pt) 2019-09-24
CA2785377C (fr) 2017-02-21
FR2954798A1 (fr) 2011-07-01
US20120282110A1 (en) 2012-11-08
FR2954798B1 (fr) 2012-03-30
JP5661798B2 (ja) 2015-01-28

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