EP1548235A2 - Segment des aubes de guidage refroidi - Google Patents

Segment des aubes de guidage refroidi Download PDF

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Publication number
EP1548235A2
EP1548235A2 EP04257975A EP04257975A EP1548235A2 EP 1548235 A2 EP1548235 A2 EP 1548235A2 EP 04257975 A EP04257975 A EP 04257975A EP 04257975 A EP04257975 A EP 04257975A EP 1548235 A2 EP1548235 A2 EP 1548235A2
Authority
EP
European Patent Office
Prior art keywords
endwall
duct
hole
vane cluster
cross sectional
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Withdrawn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
EP04257975A
Other languages
German (de)
English (en)
Other versions
EP1548235A3 (fr
Inventor
Todd Coons
Edward Pietraszkiewicz
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP1548235A2 publication Critical patent/EP1548235A2/fr
Publication of EP1548235A3 publication Critical patent/EP1548235A3/fr
Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/12—Manufacture by removing material by spark erosion methods
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the invention relates to gas turbine engine components, and more particularly to a cast vane cluster with enhanced cooling.
  • a gas turbine engine includes a compressor for directing a primary fluid stream axially rearward, through a combustor and into a turbine.
  • the turbine extracts power from a primary fluid stream and transmits the power through a shaft to rotate the forward -mounted compressor.
  • a portion of the primary fluid stream is also directed to one or more secondary fluid streams for use in cooling components of the gas turbine engine.
  • Disposed within the turbine section are alternating, annular stages of rotating blades and stationary vanes. The blades and vanes are disposed circumferentially about a central, longitudinal axis of the gas turbine engine.
  • Individual turbine vanes are comprised of an inner platform, an outer platform and an airfoil spanning radially outward from the inner platform to the outer platform.
  • the airfoil contains a forward facing leading edge and a rearward facing trailing edge.
  • the airfoil is staggered on the platforms in relation to the primary fluid stream direction, with the airfoil trailing edges of adj acent vanes forming an overlapping array.
  • the platforms and airfoils of adjacent vanes bound a duct for directing the primary fluid stream rearward.
  • An inlet to the duct is bounded by adjacent airfoil leading edges and inner and outer endwall su rfaces.
  • An outlet to the duct is bounded by adjacent airfoil trailing edges and inner and outer endwall surfaces.
  • the duct area generally converges in the axially rearward direction.
  • Vanes are typically investment cast of high-strength Nickel or Cobalt alloys and may contain multiple airfoils within a single casting. Vane castings with multiple airfoils are referred to as cast vane clusters and have the advantage of reducing the number of inter -platform interfaces in a turbine stage. Inter -platform interfaces are costly to manufacture and are a source of primary fluid stream leakage, which is detrimental to the operating efficiency of the gas turbine engine.
  • one or more hollow passages extend through the interior of the airfoils forming a series of internal airfoil surfaces.
  • the hollow passages direct a secondary fluid stream into the interior of the cast vane cluster.
  • a multitude of cooling holes pass through the airfoil walls and into the hollow passages, allowing the secondary fluid stream to discharge into the primary fluid stream.
  • Each hole comprises an inlet, an outlet and a bore extending from the inlet to the outlet along a central, longitudinal axis.
  • the multitude of cooling holes are drilled from the direction of the airfoil trailing edge and at an acute angle to the cast vane cluster surfaces. The drilling direction and angle are necessary to ensure that the secondary fluid stream is discharged in a substantially rearward direction. This optimizes the cooling effectiveness of the secondary fluid stream and reduces aerodynamic losses in the primary fluid stream.
  • cooling holes are drilled after a vane cluster casting is made.
  • the standard methods used for drilling cooling holes in cast articles are laser and electrodischarge machining (EDM).
  • Laser drilling methods utilize short pulses of a high-energy beam, an example is shown in U.S. Pat. No. 5,037,183.
  • Electrodischarge machining (EDM) drilling methods pass an electrical charge through a gap between an electrode and a surface, an example is shown in U.S. Pat. No. 6,403,910. Both the laser and the EDM drilling methods require a line of sight from the drilling equipment to the hole location, limiting the surfaces that may be drilled.
  • a cast vane cluster with cooling holes drilled into surfaces without a line of sight from the drilling equipment to the hole location.
  • a cast vane cluster with enhanced cooling contains an inner and an outer platform and at least two airfoils for directing a primary fluid stream axially rearward.
  • a duct is bounded by inner, an outer endwall surfaces, and adjacent airfoil fluid directing surfaces.
  • the duct boundar y contains at least one cooling hole for directing a secondary fluid stream to enhance cooling and extend the life of the cast vane cluster.
  • FIG. 1 A gas turbine engine 10 with a central, longitudinal axis 12 is shown in FIG. 1.
  • the gas turbine engine contains a compressor section 14, a combustor section 16 and a turbine section 18.
  • a primary fluid stream 20 is directed axially rearward from the compressor section 14, through the combustor section 16 and into the turbine section 18.
  • Within the compressor section 14, a portion of the primary fluid stream 20 is directed to one or more secondary fluid streams 22, which bypass the combustor section 16, for use in cooling components within the gas turbine engine 10.
  • the turbine section 18 typically comprises multiple, alternating stages of rotating blades 24 and stationary vanes 26. Multiple vanes may be cast as a single piece, which is typically called a cast vane cluster 32 (shown in FIG. 2).
  • a cast vane cluster 32 comprises an inner platform 34, an outer platform 36 and at least two airfoils 38 spanning radially outward from the inner platform 34 to the outer platform 36.
  • the inner platform 34 has an inner endwall surface 40 facing the airfoils and one or more inboard cavities 42 (shown in FIGS. 7 and 8) opposite the airfoils.
  • the outer platform 36 has an outer endwall surface 44 facing the airfoils and one or more outboard cavities 46 opposite the airfoils.
  • each of the airfoils 38 are comprised of a concave fluid directing surface 48, a convex fluid directing surface 50, a forward facing leading edge 52 and a rearward facing trailing edge 54.
  • the platform endwall surfaces 40, 44 and airfoil fluid directing surfaces 48, 50 delineate a duct 56, as shown in FIG. 2, for directing the primary fluid stream 20 rearward.
  • One or more hollow passages 58 extend through the interior of the airfoils 38, connecting the inboard 42 and outboard cavities 46, (shown in FIG. 8).
  • a multitude of cooling holes 62 may be drilled using conventional laser or electrodischarge machining EDM drilling methods.
  • a typical cooling hole 62 is comprised of an inlet cross sectional area 65, an outlet cross sectional area 66 and a bore 67.
  • the bore 67 extends through an airfoil wall 94, from the inlet cross sectional area 65 to the outlet cross sectional area 66, along a central, longitudinal axis 68.
  • this example shows a cooling hole 62 with circular inlet and outlet cross sectional areas 65, 66, it is to be understood that any shape may be used.
  • a cooling hole 62 may pass through an inner platform 34 or an outer platform 36 as well as an airfoil wall 94.
  • FIGS. 6,7 and 8 shows an exemplary embodiment cast vane cluster including one or more cooling holes 62 located in an obstructed area 64 (shown in FIG 3) of duct 56 (shown in FIG. 2).
  • Duct 56 extends axially across portions of the platform endwall surfaces 40, 44, and radially across portions of the airfoil fluid directing surfaces 48, 50.
  • One or more cooling holes 62, located in portions of the duct 56 may not be visible when viewed from an external location. Additionally, one or more cooling holes 62, may only have an outlet cross sectional area 66 visible when viewed along a longitudinal axis 68 from an external location.
  • An exemplary cast vane cluster, with enhanced cooling as described above, may be made using one or more of the hole- drilling guides and methods described below.
  • FIG. 4 shows an embodiment of a hole -drilling guide 70 for guiding a flexible, hole-drilling instrument 72 to a surface without a line of sight from the hole drilling equipment to a required hole location.
  • the hole -drilling guide 70 comprises a body 74, one or more inlet apertures 76, one or more exit apertures 78 and a hollow, nonlinear raceway 80 connecting each corresponding inlet 76 and exit 78 apertures. Shown in this example are three raceways; however, any number may be used.
  • An inlet aperture 76 may contain a conical, bell -shaped or a similar shaped entrance 82 to simplify insertion of the flexible, hole-drilling instrument 72.
  • the raceways 80 are a similar cross sectional shape as the flexible, hole-drilling instrument 72 and are slightly larger in sectional area.
  • the clearance required between the flexible, hole -drilling instrument 72 and the nonlinear raceway 80 depends on the material of the hole-drilling guide 70 and the degree of curvature of the nonlinear raceway 80. In this example, a radial clearance of approximately 0.004 inch (0.1 mm)is used.
  • Each of the exit apertures 78 penetrates a substantially conforming face 84 of the hole-drilling guide 70.
  • the pos ition of an exit aperture 78 in relation to an obstructed surface of an article is controlled by the substantially conforming faces 84, and by other locating features such as rolls, pins, tabs, balls, bumps 86.
  • a clamping lug 88 allows the hole-drilling guide 70 to be rigidly secured to the article, once positioned.
  • FIG. 5 shows an alternate embodiment of a hole-drilling guide 70.
  • the hole- drilling guide 70 comprises a body 74 and faces 84, which substantially conform to an internal cavity or passage of an article.
  • a clamping lug 88 allows the hole- drilling guide 70 to be rigidly secured to the article, once positioned, and contains one or more inlet apertures 76.
  • One or more exit apertures 78 penetrate the substantially corresponding surfaces 84 and are connected to the inlet apertures 76 by one or more nonlinear raceways 80. Shown in this example are three nonlinear raceways; however, any number may be used.
  • the flexible, hole-drilling instrument 72 is an EDM electrode.
  • the EDM electrode is formed of a flexible, electrically conductive wire with a diameter of between approximately 0.009 - 0.016 inches (0.23 -0.41 mm).
  • a flexible, electrically conductive foil strip of a comparable dimension may be used.
  • the body 74 of the hole -drilling guide 70 is preferably made of an electrically insulating material using solid freeform fabrication, casting, molding, machining or any other suitable technique. Alternately, the body 74 may be formed of an electrically conductive material and the nonlinear raceways 80 may be coated with an electrically insulating material.
  • a hole-drilling guide 70 is used to guide an EDM electrode 72 to a portion of an obstructed surface area 64 (shown in FIG. 3) of a cast vane cluster 32.
  • the obstructed surface area is located on an airfoil convex fluid directing surface 50.
  • a cast vane cluster 32 is loaded in a single or multiple axis EDM station using a conventional tooling fixture 90.
  • an AMCHEM model HSD6-11, high-speed EDM station was used.
  • a hole- drilling guide 70 is placed into a duct 56 (shown in FIG.
  • the hole- drilling guide 70 is rigidly secured by a clamp 92 contacting a clamping lug 88.
  • An EDM electrode 72 is inserted into an inlet aperture 76 and advanced along a nonlinear raceway 80, until the electrode contacts the airfoil convex fluid directing surface 50. Once loaded into the raceway 80, the EDM electrode 72 is secured to the EDM station and plunged through an airfoil wall 94 into a hollow passage 58, forming a hole 62. Upon completion of the hole 62, the EDM electrode 72 is retracted and the process is repeated as required.
  • a hole-drilling guide 70 is used to guide an EDM electrode 72 to a portion of an obstructed surface area 64 (shown in FIG. 3) of a cast vane cluster 32.
  • the obstructed surface area is located on an inner endwall surface 40.
  • a cast vane cluster 32 is loaded in a single or multiple axis EDM station using a conventional tooling fixture 90.
  • an AMCHEM model HSD6- 11, high-speed EDM station or equivalent may be used.
  • a hole-drilling guide 70 is placed into a duct 56 (shown in FIG.
  • the hole -drilling guide 70 is rigidly secured by a clamp 92 contacting a clamping lug 88.
  • An EDM electrode 72 is inserted into an inlet aperture 76 and advanced along a nonlinear raceway 80, until the electrode contacts the inner endwall surface 40. Once loaded into the raceway 80, the EDM electrode 72 is secured to the EDM station and plunged through an inner platform 34 into an inner cavity 42 of the vane cluster 32, forming a hole 62. Upon completion of the hole 62, the EDM electrode 72 is retracted and the process is repeated as required.
  • a hole-drilling guide 70 guides an EDM electrode 72 to a portion of an obstructed surface area 64 (shown in FIG. 3) of a cast vane cluster 32.
  • the obstructed surface area is located on an airfoil concave fluid directing surface 48, and is accessed via a hollow passage 58.
  • a cast vane cluster 32 is loaded in a single or multiple axis EDM station using a conventional tooling fixture 90.
  • an AMCHEM model HSD6 -11, high-speed EDM station or equivalent may be used.
  • a hole -drilling guide 70 is inserted into the hollow passage 58 of the vane cluster 32 and accurately positioned in relation to the hollow passage 58 by conforming surfaces 84 and locating features 86.
  • the hole -drilling guide 70 is rigidly secured by a clamp 92 contacting a clamping lug 88.
  • An EDM electrode 72 is inserted into an inlet aperture 76 and advanced along a nonlinear raceway 80, until the electrode contacts the surface of the hollow passage 58. Once loaded into the raceway 80, the EDM electrode 72 is secured to the EDM station and plunged through the airfoil wall 94, forming a hole 62 (not shown. Upon completion of the hole 62, the EDM electrode 72 is retracted and the process is repeated as required.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP04257975A 2003-12-22 2004-12-20 Segment des aubes de guidage refroidi Withdrawn EP1548235A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10/743,516 US20050135923A1 (en) 2003-12-22 2003-12-22 Cooled vane cluster
US743516 2003-12-22

Publications (2)

Publication Number Publication Date
EP1548235A2 true EP1548235A2 (fr) 2005-06-29
EP1548235A3 EP1548235A3 (fr) 2008-11-19

Family

ID=34552829

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04257975A Withdrawn EP1548235A3 (fr) 2003-12-22 2004-12-20 Segment des aubes de guidage refroidi

Country Status (9)

Country Link
US (1) US20050135923A1 (fr)
EP (1) EP1548235A3 (fr)
JP (1) JP2005180447A (fr)
KR (1) KR20050063678A (fr)
CN (1) CN1637235A (fr)
AU (1) AU2004240240A1 (fr)
CA (1) CA2489964A1 (fr)
NO (1) NO20045594L (fr)
RU (1) RU2004136896A (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1916388A2 (fr) * 2006-10-18 2008-04-30 United Technologies Corporation Vanne dotée d'un transfert de chaleur amélioré
EP1849965A3 (fr) * 2006-04-26 2011-05-18 United Technologies Corporation Refroidissement de plateforme à ailettes
EP2436884A1 (fr) * 2010-09-29 2012-04-04 Siemens Aktiengesellschaft Agencement de turbine et moteur à turbine à gaz

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE479017T1 (de) * 2005-09-06 2010-09-15 Volvo Aero Corp Verfahren zur herstellung einer motorwandstruktur
US8191504B2 (en) * 2006-11-27 2012-06-05 United Technologies Corporation Coating apparatus and methods
US7862291B2 (en) * 2007-02-08 2011-01-04 United Technologies Corporation Gas turbine engine component cooling scheme
FR2978197B1 (fr) * 2011-07-22 2015-12-25 Snecma Distributeur de turbine de turbomachine et turbine comportant un tel distributeur
US10408079B2 (en) 2015-02-18 2019-09-10 Siemens Aktiengesellschaft Forming cooling passages in thermal barrier coated, combustion turbine superalloy components
CN105171158B (zh) * 2015-10-10 2017-11-14 贵阳中航动力精密铸造有限公司 一种涡轮导向叶片锥形气膜孔加工工艺
US10436042B2 (en) 2015-12-01 2019-10-08 United Technologies Corporation Thermal barrier coatings and methods
US10641102B2 (en) * 2017-09-01 2020-05-05 United Technologies Corporation Turbine vane cluster including enhanced vane cooling
US11125164B2 (en) * 2019-07-31 2021-09-21 Raytheon Technologies Corporation Baffle with two datum features
CN112091336B (zh) * 2020-09-21 2022-02-25 中国航发沈阳黎明航空发动机有限责任公司 一种整铸成联叶片电火花加工干涉气膜孔精确定位方法

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US3529903A (en) * 1968-11-29 1970-09-22 Westinghouse Electric Corp Nozzle blade structure
JPS59180006A (ja) * 1983-03-30 1984-10-12 Hitachi Ltd ガスタ−ビン静翼セグメント
US4693667A (en) * 1980-04-29 1987-09-15 Teledyne Industries, Inc. Turbine inlet nozzle with cooling means
US5813832A (en) * 1996-12-05 1998-09-29 General Electric Company Turbine engine vane segment
WO2001012382A1 (fr) * 1999-08-12 2001-02-22 Chromalloy Gas Turbine Corporation Procede de remplacement d'un profil de roue de turbine
EP1176284A2 (fr) * 2000-07-27 2002-01-30 General Electric Company Aubes de guidage avec col dépourvu de brasure
EP1262634A2 (fr) * 2001-05-29 2002-12-04 General Electric Company Tuyère intégrale et virole
US20030002979A1 (en) * 2001-06-28 2003-01-02 Koschier Angelo Von Hybrid turbine nozzle

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US5637239A (en) * 1995-03-31 1997-06-10 United Technologies Corporation Curved electrode and method for electrical discharge machining curved cooling holes
GB2313414B (en) * 1996-05-24 2000-05-17 Rolls Royce Plc Gas turbine engine blade tip clearance control
US6416278B1 (en) * 2000-11-16 2002-07-09 General Electric Company Turbine nozzle segment and method of repairing same
DE10059997B4 (de) * 2000-12-02 2014-09-11 Alstom Technology Ltd. Kühlbare Schaufel für eine Gasturbinenkomponente
US6382908B1 (en) * 2001-01-18 2002-05-07 General Electric Company Nozzle fillet backside cooling

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3529903A (en) * 1968-11-29 1970-09-22 Westinghouse Electric Corp Nozzle blade structure
US4693667A (en) * 1980-04-29 1987-09-15 Teledyne Industries, Inc. Turbine inlet nozzle with cooling means
JPS59180006A (ja) * 1983-03-30 1984-10-12 Hitachi Ltd ガスタ−ビン静翼セグメント
US5813832A (en) * 1996-12-05 1998-09-29 General Electric Company Turbine engine vane segment
WO2001012382A1 (fr) * 1999-08-12 2001-02-22 Chromalloy Gas Turbine Corporation Procede de remplacement d'un profil de roue de turbine
EP1176284A2 (fr) * 2000-07-27 2002-01-30 General Electric Company Aubes de guidage avec col dépourvu de brasure
EP1262634A2 (fr) * 2001-05-29 2002-12-04 General Electric Company Tuyère intégrale et virole
US20030002979A1 (en) * 2001-06-28 2003-01-02 Koschier Angelo Von Hybrid turbine nozzle

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1849965A3 (fr) * 2006-04-26 2011-05-18 United Technologies Corporation Refroidissement de plateforme à ailettes
EP1916388A2 (fr) * 2006-10-18 2008-04-30 United Technologies Corporation Vanne dotée d'un transfert de chaleur amélioré
EP1916388A3 (fr) * 2006-10-18 2013-10-30 United Technologies Corporation Vanne dotée d'un transfert de chaleur amélioré
EP2436884A1 (fr) * 2010-09-29 2012-04-04 Siemens Aktiengesellschaft Agencement de turbine et moteur à turbine à gaz
WO2012041728A1 (fr) * 2010-09-29 2012-04-05 Siemens Aktiengesellschaft Agencement de turbine et moteur à turbine à gaz
US9238969B2 (en) 2010-09-29 2016-01-19 Siemens Aktiengesellschaft Turbine assembly and gas turbine engine
RU2576754C2 (ru) * 2010-09-29 2016-03-10 Сименс Акциенгезелльшафт Турбинная система и газотурбинный двигатель

Also Published As

Publication number Publication date
CN1637235A (zh) 2005-07-13
NO20045594L (no) 2005-06-23
JP2005180447A (ja) 2005-07-07
RU2004136896A (ru) 2006-05-27
EP1548235A3 (fr) 2008-11-19
KR20050063678A (ko) 2005-06-28
CA2489964A1 (fr) 2005-06-22
US20050135923A1 (en) 2005-06-23
AU2004240240A1 (en) 2005-07-07

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