EP1333155A1 - Kühlung der Abströmkante einer Hochdruckturbinenlaufschaufel - Google Patents

Kühlung der Abströmkante einer Hochdruckturbinenlaufschaufel Download PDF

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Publication number
EP1333155A1
EP1333155A1 EP03290140A EP03290140A EP1333155A1 EP 1333155 A1 EP1333155 A1 EP 1333155A1 EP 03290140 A EP03290140 A EP 03290140A EP 03290140 A EP03290140 A EP 03290140A EP 1333155 A1 EP1333155 A1 EP 1333155A1
Authority
EP
European Patent Office
Prior art keywords
blade
slot
pressure turbine
dawn
cavity
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.)
Withdrawn
Application number
EP03290140A
Other languages
English (en)
French (fr)
Inventor
Jacques Boury
Maurice Judet
Jacky Tabardin
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 Moteurs SA
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 Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1333155A1 publication Critical patent/EP1333155A1/de
Withdrawn legal-status Critical Current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
    • 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
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F05B2240/801—Platforms for stationary or moving blades cooled platforms
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • the present invention relates to the general field of turbomachine high pressure turbine blades, and more particularly to the vents of the cooling air of the moving blades of a high pressure turbine.
  • a turbomachine comprises a combustion chamber in which air and fuel are mixed before burning.
  • the gases resulting from this combustion flow downstream into the combustion chamber and then feed a high pressure turbine.
  • the high pressure turbine has one or several rows of moving blades circumferentially spaced all around the rotor of the turbine. Mobile blades of the high turbine pressure are thus subjected to the very high temperatures of combustion. These temperatures reach values widely superior to those that can withstand without damage the blades that are in contact with these gases, which has the effect of limiting their lifetime.
  • cooling air which is generally introduced into the dawn by its foot, crosses it in following a path formed by cavities practiced in the dawn before being ejected by slits opening on the surface of dawn on its edge leakage, as in the patent application EP 0 945 594, or on its side intrados, as in US Pat. No. 4,601,638. More specifically, these cooling air vents are usually divided between the foot and the top of this dawn, substantially perpendicular to a longitudinal axis of the dawn.
  • connection zone situated between this slot and the platform supporting the dawn is very poorly cooled, all the more more than, because of the large dimensions of this slot and because the centrifugal force generated by the rotation of the blade, the air evacuated by the slot tends to be diverted to the top of dawn. It results significant thermal gradients in the vicinity of the trailing edge which generate by conduction, at the connection zone, a creek particularly detrimental to the life of dawn.
  • the present invention therefore aims to overcome such a disadvantage by proposing a high-pressure turbine turbine blade presenting a new geometry that does not create a crack.
  • the invention aims also not to degrade the general mechanical strength of the dawn, part subjected to very important mechanical constraints. She aims finally a turbomachine high pressure turbine equipped with such blades mobile with improved thermal behavior.
  • turbomachine pressure comprising at least one cooling consisting of at least one radially extending cavity between a summit and a foot of dawn, of at least one opening air intake at a radial end of the cavity or cavities for supplying the cooling air cooling circuit (s), and of a plurality of slots opening in the cavity or cavities and opening on a side intrados of the dawn between the foot and the top of the dawn, so substantially perpendicular to a longitudinal axis of the dawn, and a zone connection is provided between a slot closest to the foot of the dawn and an upper surface of a platform defining a wall internal flow for a flow of flue gas through the high pressure turbine, characterized in that it also comprises an extra slot for cooling air evacuation practiced in said connection zone in the extension of the edge leak.
  • this additional slot has a shape taken in the group of the following forms: oblong, rectangular, triangular or inverted T and it is obtained directly from foundry.
  • this extra slot may have a section output different from that of its feed channel.
  • a longitudinal lower end of the additional slot is arranged just above said surface top of the platform.
  • FIG. 1 represents in perspective a moving blade 10, for example of a high pressure turbine of a turbomachine according to the present invention.
  • This blade of longitudinal axis X-X is fixed on a rotor disc (not shown) of the high pressure turbine by via a fitting 12 generally fir-shaped. It typically comprises a foot 14A, a vertex 14B, a wall 16A, an extrados wall 16B, leading edge 18 and an edge of 20.
  • the fitting 12 is connected to the foot 14A of the dawn level a platform 22 defining an internal wall for the vein flow of combustion gases through the high turbine pressure.
  • the blade 10 has at least one circuit of internal cooling composed for example of at least one cavity 24 extending radially between the foot 14A and the vertex 14B of the blade.
  • This cavity is supplied with cooling air to one of its radial ends through an air inlet opening (not shown).
  • This air intake opening is generally provided at the level of the fitting 12 of the dawn.
  • the slots 26 for exhausting the cooling air are typically distributed between the foot 14A and the summit 14B of the dawn, substantially perpendicular to the longitudinal axis X-X of the blade. More particularly, the slot 28 closest to the foot 14A of the dawn 10 is formed just above a connection zone 30 between the foot 14A of the dawn and an upper surface 22A of the platform 22 on the side of the flow of flue gas.
  • FIG. 2 and Figures 2A through 2C illustrate more precisely the geometry of the trailing edge 20 of the dawn at this level connection area with the slot 28 closest to the foot 14A of dawn 10.
  • a slot is provided additional opening in the cavity 24 and opening into said area connection in the extension of the trailing edge 20.
  • This slot additional 32 provides convective cooling of this part of the connection area and, by conduction, of the slot the closer to the foot of dawn and part of the platform located in the extension of the trailing edge.
  • Cooling air evacuated by this additional slot covers indeed the whole surface of the connection area at the trailing edge and lowers the local temperature of about 10%, without changing the aerodynamic performance provided by the vents of the side intrados.
  • the extra slot can have different shapes determined according to the criteria of thermal design and mechanics desired.
  • the feed channel and the orifice output can be of different sections.
  • Figure 2 illustrates a additional slot having a feed channel and an orifice elongate output, advantageously oblong (a section rectangular is also possible).
  • the output section is always oblong but the internal feed channel is substantially triangular, ie flared on both sides of this hole outlets, so as to ensure better cooling of the connection while having a perfectly calibrated output flow. according to the thermal stresses and the mechanical forces undergone by the dawn, this Variable angle flare can be asymmetrical and therefore point that to only one side, as shown in Figure 2B.
  • This slot is advantageously obtained directly from foundry at the same time as the dawn itself (and not machined next) and it crosses the dawn to the cavity 24 while remaining constantly just above the level of the upper surface of the platform (this is mean that its lower longitudinal end 32A or 34A is above of this upper surface 22A). So, it's this additional slot that suffers the effects of the metal casting pressure and not the most 28 slot close to the foot of the dawn, as in the prior art, and any risk of weakening of the blade due to machining is rejected.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03290140A 2002-01-23 2003-01-21 Kühlung der Abströmkante einer Hochdruckturbinenlaufschaufel Withdrawn EP1333155A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0200802 2002-01-23
FR0200802A FR2835015B1 (fr) 2002-01-23 2002-01-23 Aube mobile de turbine haute pression munie d'un bord de fuite au comportement thermique ameliore

Publications (1)

Publication Number Publication Date
EP1333155A1 true EP1333155A1 (de) 2003-08-06

Family

ID=8871382

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03290140A Withdrawn EP1333155A1 (de) 2002-01-23 2003-01-21 Kühlung der Abströmkante einer Hochdruckturbinenlaufschaufel

Country Status (7)

Country Link
US (1) US20030138322A1 (de)
EP (1) EP1333155A1 (de)
JP (1) JP2003214108A (de)
CN (1) CN1436919A (de)
CA (1) CA2418241A1 (de)
FR (1) FR2835015B1 (de)
RU (1) RU2003101665A (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2868867A1 (de) * 2013-10-29 2015-05-06 Siemens Aktiengesellschaft Turbinenschaufel
EP3249162B1 (de) * 2016-05-24 2021-08-18 General Electric Company Laufschaufel und zugehöriges gasturbinensystem

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE50306044D1 (de) * 2003-09-05 2007-02-01 Siemens Ag Schaufel einer Turbine
FR2864990B1 (fr) * 2004-01-14 2008-02-22 Snecma Moteurs Perfectionnements apportes aux fentes d'evacuation de l'air de refroidissement d'aubes de turbine haute-pression
US7097424B2 (en) * 2004-02-03 2006-08-29 United Technologies Corporation Micro-circuit platform
US7246999B2 (en) * 2004-10-06 2007-07-24 General Electric Company Stepped outlet turbine airfoil
FR2877034B1 (fr) * 2004-10-27 2009-04-03 Snecma Moteurs Sa Aube de rotor d'une turbine a gaz
GB2444483B (en) * 2006-12-09 2010-07-14 Rolls Royce Plc A core for use in a casting mould
CH699601A1 (de) * 2008-09-30 2010-03-31 Alstom Technology Ltd Schaufel für eine gasturbine.
CN101767286B (zh) * 2008-12-30 2013-06-05 沈阳黎明航空发动机(集团)有限责任公司 一种高压涡轮工作叶片精整、机加定位工艺方法
US8632297B2 (en) 2010-09-29 2014-01-21 General Electric Company Turbine airfoil and method for cooling a turbine airfoil
US8585350B1 (en) * 2011-01-13 2013-11-19 George Liang Turbine vane with trailing edge extension
JP2012189026A (ja) * 2011-03-11 2012-10-04 Ihi Corp タービン翼
US9045987B2 (en) * 2012-06-15 2015-06-02 United Technologies Corporation Cooling for a turbine airfoil trailing edge
US10107107B2 (en) 2012-06-28 2018-10-23 United Technologies Corporation Gas turbine engine component with discharge slot having oval geometry
JP6245740B2 (ja) * 2013-11-20 2017-12-13 三菱日立パワーシステムズ株式会社 ガスタービン翼
US20160090843A1 (en) * 2014-09-30 2016-03-31 General Electric Company Turbine components with stepped apertures
FR3099523B1 (fr) * 2019-08-01 2021-10-29 Safran Aircraft Engines Aube munie d’un circuit de refroidissement
US20230151737A1 (en) * 2021-11-18 2023-05-18 Raytheon Technologies Corporation Airfoil with axial cooling slot having diverging ramp

Citations (2)

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Publication number Priority date Publication date Assignee Title
US4601638A (en) * 1984-12-21 1986-07-22 United Technologies Corporation Airfoil trailing edge cooling arrangement
EP1128024A2 (de) * 2000-02-23 2001-08-29 Mitsubishi Heavy Industries, Ltd. Rotorblatt für Gasturbinen

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US4738588A (en) * 1985-12-23 1988-04-19 Field Robert E Film cooling passages with step diffuser
EP0954679B1 (de) * 1996-06-28 2003-01-22 United Technologies Corporation Kühlbare schaufelstruktur für eine gasturbine
JP3316418B2 (ja) * 1997-06-12 2002-08-19 三菱重工業株式会社 ガスタービン冷却動翼
US5975851A (en) * 1997-12-17 1999-11-02 United Technologies Corporation Turbine blade with trailing edge root section cooling
US6062817A (en) * 1998-11-06 2000-05-16 General Electric Company Apparatus and methods for cooling slot step elimination
US6609891B2 (en) * 2001-08-30 2003-08-26 General Electric Company Turbine airfoil for gas turbine engine

Patent Citations (2)

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Publication number Priority date Publication date Assignee Title
US4601638A (en) * 1984-12-21 1986-07-22 United Technologies Corporation Airfoil trailing edge cooling arrangement
EP1128024A2 (de) * 2000-02-23 2001-08-29 Mitsubishi Heavy Industries, Ltd. Rotorblatt für Gasturbinen

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2868867A1 (de) * 2013-10-29 2015-05-06 Siemens Aktiengesellschaft Turbinenschaufel
WO2015063021A1 (de) * 2013-10-29 2015-05-07 Siemens Aktiengesellschaft Turbinenschaufel mit einer mittigen ausblasung an der hinterkante
US10487669B2 (en) 2013-10-29 2019-11-26 Siemens Aktiengesellschaft Turbine blade with a central blowout at the trailing edge
EP3249162B1 (de) * 2016-05-24 2021-08-18 General Electric Company Laufschaufel und zugehöriges gasturbinensystem

Also Published As

Publication number Publication date
RU2003101665A (ru) 2004-11-10
CN1436919A (zh) 2003-08-20
US20030138322A1 (en) 2003-07-24
FR2835015A1 (fr) 2003-07-25
JP2003214108A (ja) 2003-07-30
FR2835015B1 (fr) 2005-02-18
CA2418241A1 (fr) 2003-07-23

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