US20120282110A1 - Inner ventilation blade - Google Patents

Inner ventilation blade Download PDF

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Publication number
US20120282110A1
US20120282110A1 US13/519,339 US201013519339A US2012282110A1 US 20120282110 A1 US20120282110 A1 US 20120282110A1 US 201013519339 A US201013519339 A US 201013519339A US 2012282110 A1 US2012282110 A1 US 2012282110A1
Authority
US
United States
Prior art keywords
blade
trailing edge
piercings
closest
apex
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.)
Abandoned
Application number
US13/519,339
Other languages
English (en)
Inventor
Erwan Daniel Botrel
Jacques Auguste Amedee Boury
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SAS filed Critical SNECMA SAS
Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOTREL, ERWAN DANIEL, BOURY, JACQUES AUGUSTE AMEDEE
Publication of US20120282110A1 publication Critical patent/US20120282110A1/en
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SNECMA
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Assignors: SNECMA
Abandoned legal-status Critical Current

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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 greater inclination is advantageously gradual, giving the partition a general rounded shape.
  • FIG. 3 is a detail showing a prior design which is improved by the invention
  • FIG. 4 is a corresponding detail of a design in accordance with the invention.
  • Ventilation gas arrives in the cavities ( 4 ) (and ( 6 ) and ( 8 )) through their origins ( 10 ) in the root ( 2 ) from another region of the machine to which the blade ( 1 ) belongs, and rises to the apex ( 11 ) of the blade ( 1 ); it leaves the cavities gradually through piercings ( 12 ) emerging in the intrados ( 13 ) and/or in the extrados ( 22 ) of the blade ( 1 ), whilst other piercings ( 14 ) (represented in FIGS. 3 and 4 ) emerge in the apex ( 11 ), and finally by other piercings ( 15 ), exiting solely from cavity ( 6 ), which emerge in the trailing edge ( 7 ).
  • Ventilation of the apex ( 11 ) of the blade ( 1 ) is more difficult since the piercings ( 14 ) are located at the end of the cavities ( 4 ) and since the ventilation gas flow rate is lower and is of lower pressure; another unfavourable circumstance results from the fact that the apex ( 11 ) consists of a thin external ridge ( 16 ), extending on the extrados side and on the intrados side of the blade, thus forming a hollow cavity referred to as a “basin” ( 17 ).
  • Ridge ( 16 ) enables the hot gas outflows between the apex of the blade and the casing opposite it to be limited, and is a zone which is subjected to wear and tear zone when the blade, under the combined effect of the thermal expansion and the centrifugal force, extends and touches the casing opposite it.
  • the basin ( 17 ) and the ridge ( 16 ) are regions which are difficult to cool; 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 narrowest.
  • the partition (in this case 9 ′) closest to the trailing edge ( 7 ) is rectilinear, as are the others, to simplify blade manufacture, and it is generally completely radial in direction.
  • the inventors observed the existence of a low-speed recirculation zone ( 19 ) in the cavity ( 6 ) at the point where the partition ( 9 ′) and wall at the base of the basin ( 17 ) connect.
  • the low dynamic pressure of the ventilation gas in this location makes the creation of upper piercings to ventilate the apex ( 11 ) futile, such that the edge of the basin ( 17 ) is not ventilated at all; and it is observed that the piercings ( 15 ) leading to the trailing edge ( 7 ) closest to the apex ( 11 ), typically the three or four closest such piercings, are subjected to a particularly low flow rate due to the low pressure of the gas.
  • the modification specific to the invention which can be seen in FIG. 4 , consists in giving the partition ( 9 ) closest to the trailing edge ( 7 ) an upper end ( 20 ) which is more inclined towards the trailing edge ( 7 ) than the remainder of the partition ( 9 ), and which is advantageously increasingly inclined, with a rounded shape, and an almost regular connection, to the wall at the base of the basin ( 17 ).
  • the upper portion ( 20 ) can start at 80%, or possibly 70%, of the height of the blade ( 1 ) measured from the platform ( 3 ) as far as the outer edge, i.e. the wall at the base of the basin ( 17 ).
  • the other partitions remain rectilinear.
  • the low-speed recirculation zone ( 19 ) disappears; the guiding of the ventilation gas to the piercings ( 15 ) close to the apex ( 11 ) is improved, and its pressure is increased, which also increases the flow rate through these upper piercings ( 15 ); the piercings ( 12 ) leading to the intrados ( 13 ) (or to the extrados) from the second cavity ( 8 ) can be moved towards the trailing edge ( 7 ), with their apertures ( 21 ) in the second cavity ( 8 ) occupying a line parallel to the upper portion ( 20 ); at least one additional apex piercing ( 14 ′) can be included due to the fact that the second cavity ( 8 ) is widened at the apex (where the first cavity ( 6 ), in the design represented here and also in the prior design, normally has no piercings ( 12 ) and ( 14 ) at the apex due to greater ventilation difficulties).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Building Environments (AREA)
US13/519,339 2009-12-31 2010-12-30 Inner ventilation blade Abandoned US20120282110A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0959698A FR2954798B1 (fr) 2009-12-31 2009-12-31 Aube a ventilation interieure
FR0959698 2009-12-31
PCT/EP2010/070933 WO2011080319A1 (fr) 2009-12-31 2010-12-30 Aube a ventilation interieure

Publications (1)

Publication Number Publication Date
US20120282110A1 true US20120282110A1 (en) 2012-11-08

Family

ID=42133483

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/519,339 Abandoned US20120282110A1 (en) 2009-12-31 2010-12-30 Inner ventilation blade

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)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150361798A1 (en) * 2013-02-12 2015-12-17 United Technologies Corporation Fan blade including external cavities
US11414998B2 (en) 2017-06-29 2022-08-16 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9771816B2 (en) * 2014-05-07 2017-09-26 General Electric Company Blade cooling circuit feed duct, exhaust duct, and related cooling structure

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6347923B1 (en) * 1999-05-10 2002-02-19 Alstom (Switzerland) Ltd Coolable blade for a gas turbine
US6471479B2 (en) * 2001-02-23 2002-10-29 General Electric Company Turbine airfoil with single aft flowing three pass serpentine cooling circuit
US6835046B2 (en) * 2000-06-21 2004-12-28 Siemens Aktiengesellschaft Configuration of a coolable turbine blade
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
US8079814B1 (en) * 2009-04-04 2011-12-20 Florida Turbine Technologies, Inc. Turbine blade with serpentine flow cooling

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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
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
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

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6347923B1 (en) * 1999-05-10 2002-02-19 Alstom (Switzerland) Ltd Coolable blade for a gas turbine
US6835046B2 (en) * 2000-06-21 2004-12-28 Siemens Aktiengesellschaft Configuration of a coolable turbine blade
US6471479B2 (en) * 2001-02-23 2002-10-29 General Electric Company Turbine airfoil with single aft flowing three pass serpentine cooling circuit
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
US8079814B1 (en) * 2009-04-04 2011-12-20 Florida Turbine Technologies, Inc. Turbine blade with serpentine flow cooling

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150361798A1 (en) * 2013-02-12 2015-12-17 United Technologies Corporation Fan blade including external cavities
US11414998B2 (en) 2017-06-29 2022-08-16 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine

Also Published As

Publication number Publication date
EP2519713B1 (fr) 2013-11-06
CN102713160A (zh) 2012-10-03
FR2954798A1 (fr) 2011-07-01
CN102713160B (zh) 2016-05-18
RU2012132632A (ru) 2014-02-10
CA2785377C (fr) 2017-02-21
BR112012015844A2 (pt) 2019-09-24
EP2519713A1 (fr) 2012-11-07
JP5661798B2 (ja) 2015-01-28
RU2554397C2 (ru) 2015-06-27
WO2011080319A1 (fr) 2011-07-07
FR2954798B1 (fr) 2012-03-30
CA2785377A1 (fr) 2011-07-07
JP2013516563A (ja) 2013-05-13

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Legal Events

Date Code Title Description
AS Assignment

Owner name: SNECMA, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BOTREL, ERWAN DANIEL;BOURY, JACQUES AUGUSTE AMEDEE;REEL/FRAME:028469/0499

Effective date: 20120618

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION

AS Assignment

Owner name: SAFRAN AIRCRAFT ENGINES, FRANCE

Free format text: CHANGE OF NAME;ASSIGNOR:SNECMA;REEL/FRAME:046479/0807

Effective date: 20160803

AS Assignment

Owner name: SAFRAN AIRCRAFT ENGINES, FRANCE

Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME;ASSIGNOR:SNECMA;REEL/FRAME:046939/0336

Effective date: 20160803