EP2044296A2 - Dispositif de turbine à gaz - Google Patents

Dispositif de turbine à gaz

Info

Publication number
EP2044296A2
EP2044296A2 EP07787838A EP07787838A EP2044296A2 EP 2044296 A2 EP2044296 A2 EP 2044296A2 EP 07787838 A EP07787838 A EP 07787838A EP 07787838 A EP07787838 A EP 07787838A EP 2044296 A2 EP2044296 A2 EP 2044296A2
Authority
EP
European Patent Office
Prior art keywords
collector
combustion gases
diffuser
arrangement
gas turbine
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.)
Granted
Application number
EP07787838A
Other languages
German (de)
English (en)
Other versions
EP2044296B1 (fr
Inventor
Paul Roach
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Publication of EP2044296A2 publication Critical patent/EP2044296A2/fr
Application granted granted Critical
Publication of EP2044296B1 publication Critical patent/EP2044296B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/023—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines the working-fluid being divided into several separate flows ; several separate fluid flows being united in a single flow; the machine or engine having provision for two or more different possible fluid flow paths
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
    • 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
    • F01D9/026—Scrolls for radial machines or engines
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the present invention relates to a gas turbine arrangement.
  • the present invention relates to a gas turbine arrangement
  • a gas turbine arrangement comprising: a passage, annular in cross section, for conveying combustion gases; located in the passage, turbine blading to be driven by the combustion gases; a diffuser, annular in form, for diffusing the combustion gases following their passage through the turbine blading; and a collector for collecting the combustion gases diffused by the diffuser, the collector comprising an annular main part, and, located at a position around the annular main part, a neck exit, in use of the gas turbine arrangement, combustion gases collected by the collector being conveyed around the annular main part of the collector in opposite senses so as to arrive at the neck exit of the collector travelling in opposed directions.
  • Figs 1 to 4 of the accompanying drawings One known such gas turbine arrangement is shown in Figs 1 to 4 of the accompanying drawings .
  • Fig l is a cut away perspective view of the arrangement
  • Fig 2 is a partial longitudinal cross section of the arrangement
  • Fig 3 is a schematic diagram illustrating the passage of combustion gases through the arrangement
  • Fig 4 is a cross section on the line IV-IV in Fig 3.
  • the gas turbine arrangement comprises: a passage 1, annular in cross section, for conveying combustion gases; located in the passage 1, turbine blading 3 to be driven by the combustion gases; a diffuser 5, annular in form, for diffusing the combustion gases following their passage through the turbine blading 3; and a collector 7 for collecting the combustion gases diffused by the diffuser 5, the collector 7 comprising an annular main part 9, and, located at a position around the annular main part 9, a neck exit 11.
  • combustion gases travel along passage 1, drive turbine blading 3, are diffused by diffuser 5, and are collected by collector 7.
  • the combustion gases on leaving the diffuser 5 form within the collector 7 first and second opposite sense vortical flows 13a, 13b, see Fig 4.
  • These vortical flows 13a, 13b are formed by virtue of the combustion gas flow separating off the shroud rim 15 of the diffuser 5, and rolling up, see arrows 17 in Fig 3.
  • the flow is then convected around the annular main part 9 of the collector 7, forming the first and second opposite sense vortical flows 13a, 13b.
  • These flows 13a, 13b meet at the top neck exit 11 of the collector 7 travelling in opposed directions .
  • a gas turbine arrangement comprising: a passage, annular in cross section, for conveying combustion gases; located in the passage, turbine blading to be driven by the combustion gases; a diffuser, annular in form, for diffusing the combustion gases following their passage through the turbine blading; and a collector for collecting the combustion gases diffused by the diffuser, the collector comprising an annular main part, and, located at a position around the annular main part, a neck exit, in use of the gas turbine arrangement, combustion gases collected by the collector being conveyed around the annular main part of the collector in opposite senses so as to arrive at the neck exit of the collector travelling in opposed directions, wherein the neck exit of the collector includes a partition device whereby the opposed direction flows at the neck exit are kept substantially separate .
  • the turbine blading rotates about a centre line of the gas turbine arrangement, and the partition device runs parallel to the centre line, and extends radially from the centre line.
  • the diffuser has a mouth whereby combustion gases leave the diffuser and enter the collector
  • the partition device comprises a first portion that extends over the mouth and a second portion that extends to one side of the mouth, and the second portion extends radially inward to a position closer to the centre line than the mouth.
  • the side of the first portion that faces radially inwardly increases in distance from the centre line as the distance from the second portion increases.
  • the partition device comprises a flat plate.
  • the diffuser has a curved shroud rim whereat combustion gases leave the diffuser and enter the collector, the shroud rim has an extension operative to increase pressure recovery in the gas turbine arrangement, and the extension comprises a flat rim extension that is generally planar in form and forms a discontinuity with the curved shroud rim.
  • the diffuser has a curved shroud rim whereat combustion gases leave the diffuser and enter the collector, the shroud rim has an extension operative to increase pressure recovery in the gas turbine arrangement, and the extension comprises a spiral rim extension that continues or extends the curve of the curved shroud rim so as to form a spiral.
  • Fig 1 already referred to, is a cut away perspective view of a known gas turbine arrangement
  • Fig 2 also already referred to, is a partial longitudinal cross section of the arrangement of Fig 1;
  • Fig 3 also already referred to, is a schematic diagram illustrating the passage of combustion gases through the arrangement of Fig 1;
  • Fig 4 also already referred to, is a cross section on the line IV-IV in Fig 3;
  • Fig 5 is a cut away perspective view of a gas turbine arrangement in accordance with the present invention.
  • Fig 6 is a partial longitudinal cross section of the arrangement of Fig 5;
  • Fig 7 is a schematic diagram illustrating the passage of combustion gases through the arrangement of Fig 5;
  • Fig 8 is a cross section on the line VIII-VIII in Fig 7;
  • Fig 9 illustrates in greater detail the form and location of a splitter plate of the arrangement of Fig 5;
  • Fig 10 illustrates alternative splitter plates to the splitter plate of Fig 9;
  • Fig 11 illustrates possible extensions to a shroud rim of the arrangement of Fig 5;
  • Figs 12, 13 and 14 illustrate respectively combustion gas flow in three gas turbine arrangements;
  • Figs 15, 16 and 17 are plan views corresponding respectively to Figs 12, 13 and 14;
  • Figs 18, 19 and 20 are side views corresponding respectively to Figs 12, 13 and 14;
  • Figs 21 and 22 are perspective views corresponding respectively to Figs 13 and 14;
  • Fig 23 illustrates an alternative form of partition device to the flat plates of earlier Figs.
  • the arrangement of Figs 5 to 8 is the same as that of Figs 1 to 4 with the exception that the neck exit 11 of the collector 7 includes a partition device in the form of a splitter plate 19 whereby the opposed direction vortical flows 13a, 13b at the neck exit 11 are kept substantially separate, i.e. the splitter plate 19 isolates the vortical flows 13a, 13b one from the other.
  • the splitter plate 19 runs parallel to the centre line A of the gas turbine arrangement, and extends radially from the centre line A. Preventing meeting of the vortical flows 13a, 13b, reduces entropy production in the flow of combustion gases through the gas turbine arrangement, consequently improving the efficiency of the arrangement.
  • the splitter plate 19 has the advantage that it is simple in design, and can be retrofitted to current gas turbine arrangement collectors .
  • Fig 9 illustrates the precise shape and location of the splitter plate 19 in the arrangement of Figs 5 to 8.
  • the diffuser 5 has a mouth 35 whereby combustion gases leave the diffuser 5 and enter the collector 7.
  • the splitter plate 19 comprises a first portion 37 that extends over the mouth 35 and a second portion 39 that extends to one side of the mouth 35. It can be seen from Fig 9 that the second portion 39 extends radially inward to a position 41 closer to the centre line A than the mouth 35. It can also be seen from Fig 9 that the side 43 of the first portion 37 that faces radially inwardly progressively increases in distance from the centre line A as the distance from the second portion 39 increases.
  • Fig 10 illustrates the precise shape of three alternative splitter plates 21, 23, 25.
  • Plate 21 is the same as plate 19 except that the side 45 of plate 21 corresponding to side 43 of plate 19 remains at a constant distance from the centre line A.
  • Plate 23 may be derived from plate 21 by removing that portion of plate 21 which is radially nearer to the centre line A than side 45 of plate 21.
  • Plate 25 may be derived from plate 23 by removing a further radially inner portion of plate 23. It is to be noted that in the case of both plates 23, 25, the sides 47 of the plates 23, 25 that face radially inwardly remain at a constant distance from the centre line A. It is also to be noted that the sides 47 are radially further from the centre line A than the mouth 35 of the diffuser 5.
  • Fig 11 illustrates two possible extensions 29, 31 to the shroud rim 15 of the diffuser 5 of the arrangement of Figs 5 to 8.
  • the extensions 29, 31 operate to increase the pressure recovery in the gas turbine arrangement, over and above that obtained using a splitter plate alone.
  • the extensions 29, 31 diffuse the combustion gas flow in a more controlled manner, weakening the vortices formed in the collector 7.
  • Extension 29 comprises a flat rim extension, and is generally planar in form, and forms a discontinuity with the shroud rim 15.
  • Extension 31 comprises a spiral rim extension, and continues or extends the curve of the shroud rim 15 so as to form a spiral.
  • Fig 12 illustrates combustion gas flow in the diffuser 5 and collector 7 of the known gas turbine arrangement of Figs 1 to 4. It is to be noted that strong vortices occur in the annular main part 9 of the collector 7, and mixing of the vortical flows 13a, 13b occurs in the neck exit 11 of the collector 7.
  • Fig 13 illustrates combustion gas flow in the diffuser 5 and collector 7 of a gas turbine arrangement including a splitter plate 19 only, i.e. not including an extension 29, 31 to the shroud rim 15 as shown in Fig 11. It is to be noted that strong vortices still occur in the annular main part 9 of the collector 7, but no mixing of the vortical flows 13a, 13b occurs in the neck exit 11 of the collector 7.
  • Fig 14 illustrates combustion gas flow in the diffuser 5 and collector 7 of a gas turbine arrangement including a splitter plate 19 and a flat rim extension 29. It is to be noted that only weak vortices occur in the annular main part 9 of the collector 7, and, in addition, no mixing of the vortical flows 13a, 13b occurs in the neck exit 11 of the collector 7.
  • Figs 15, 16 and 17 are views taken from above in Figs 12, 13 and 14 respectively.
  • Splitter plate 19 is to be noted in Figs 16 and 17.
  • Flat rim extension 29 is to be noted in Fig 17.
  • Figs 18, 19 and 20 are views taken from the left side in Figs 12, 13 and 14 respectively.
  • Splitter plate 19 is to be noted in Figs 19 and 20.
  • Flat rim extension 29 is to be noted in Fig 20.
  • Figs 21 and 22 are perspective views corresponding respectively to Figs 13 and 14.
  • Splitter plate 19 is to be noted in Figs 21 and 22.
  • Flat rim extension 29 is to be noted in Fig 22.
  • Fig 23 shows an example of an alternative partition device 33, comprising an upper flat plate part 51 and a lower substantially triangular cross section part 53 having concave sides. It is to be noted that the cross section shown in Fig 23 corresponds to second portion 39 in Fig 9, and that the first portion 37 in Fig 9 remains as it is, i.e. a flat plate.
  • the upper and lower parts 51, 53 of the partition device 33 meet at a height corresponding to the height of the obtuse angle 55 in Fig 9.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Separating Particles In Gases By Inertia (AREA)

Abstract

L'invention concerne un dispositif de turbine à gaz comprenant : un passage annulaire en coupe, destiné à transporter des gaz de combustion situés dans ce passage, des aubes de turbine entraînées par les gaz de combustion, un diffuseur de forme annulaire destiné à diffuser les gaz de combustion après leur passage à travers les aubes de la turbine et, un collecteur destiné à recueillir les gaz de combustion diffusés par le diffuseur, ce collecteur comprenant une partie principale annulaire située à une position autour de la partie principale annulaire, une sortie rétrécie utilisée dans le dispositif de turbine à gaz, des gaz de combustion recueillis par le collecteur étant transportés autour de la partie principale annulaire du collecteur dans le sens opposé de façon à arriver au niveau de la sortie rétrécie du collecteur en sens opposé, la sortie rétrécie du collecteur comprenant un dispositif de partition, les flux de direction opposée au niveau de la sortie rétrécie étant conservés sensiblement séparés.
EP07787838A 2006-07-25 2007-07-24 Dispositif de turbine à gaz Expired - Fee Related EP2044296B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0614687A GB2440343B (en) 2006-07-25 2006-07-25 A gas turbine arrangement
PCT/EP2007/057595 WO2008012294A2 (fr) 2006-07-25 2007-07-24 Dispositif de turbine à gaz

Publications (2)

Publication Number Publication Date
EP2044296A2 true EP2044296A2 (fr) 2009-04-08
EP2044296B1 EP2044296B1 (fr) 2010-06-23

Family

ID=36998632

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07787838A Expired - Fee Related EP2044296B1 (fr) 2006-07-25 2007-07-24 Dispositif de turbine à gaz

Country Status (8)

Country Link
US (1) US20090246010A1 (fr)
EP (1) EP2044296B1 (fr)
CN (1) CN101495715B (fr)
DE (1) DE602007007334D1 (fr)
ES (1) ES2346159T3 (fr)
GB (1) GB2440343B (fr)
RU (1) RU2441987C2 (fr)
WO (1) WO2008012294A2 (fr)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1992789A1 (fr) * 2007-05-18 2008-11-19 ABB Turbo Systems AG Carter de turbine à gas d'échappement comprenant un élément de support
GB0800451D0 (en) 2008-01-11 2008-02-20 Cummins Turbo Tech Ltd A turbomachine system and turbine therefor
US8109720B2 (en) * 2009-03-31 2012-02-07 General Electric Company Exhaust plenum for a turbine engine
US20110088379A1 (en) * 2009-10-15 2011-04-21 General Electric Company Exhaust gas diffuser
US8398359B2 (en) * 2010-02-17 2013-03-19 General Electric Company Exhaust diffuser
US8276390B2 (en) * 2010-04-15 2012-10-02 General Electric Company Method and system for providing a splitter to improve the recovery of compressor discharge casing
US8757969B2 (en) * 2010-09-15 2014-06-24 General Electric Company Turbine exhaust plenum
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
CN102434225B (zh) * 2011-10-18 2014-12-03 中国南方航空工业(集团)有限公司 增压叶轮轴的密封结构
US20140026999A1 (en) * 2012-07-25 2014-01-30 Solar Turbines Incorporated Exhaust diffuser for a gas turbine engine having curved and offset struts
US20140047813A1 (en) * 2012-08-17 2014-02-20 Solar Turbines Incorporated Exhaust collector with radial and circumferential flow breaks
US20140119910A1 (en) * 2012-10-29 2014-05-01 General Electric Company Turbine exhaust hood and related method
DE102013001231B4 (de) * 2013-01-25 2014-10-09 Voith Patent Gmbh Abgasführung einer Abgasnutzturbine für ein Turbocompound-System und Turbocompound-System
US9644496B2 (en) 2013-03-13 2017-05-09 General Electric Company Radial diffuser exhaust system
FR3009026B1 (fr) * 2013-07-24 2018-01-05 Safran Aircraft Engines Corps central d'echappement pour une turbomachine
US9476324B2 (en) 2013-09-19 2016-10-25 Solar Turbines Incorporated Exhaust collector with curved side panel
US20150240667A1 (en) * 2014-02-26 2015-08-27 General Electric Company Exhaust plenum for radial diffuser
EP3129608A1 (fr) * 2014-04-10 2017-02-15 Siemens Aktiengesellschaft Système d'échappement de turbine à gaz
FR3030633B1 (fr) * 2014-12-22 2019-04-12 Airbus Helicopters Tuyere d'echappement d'un turbomoteur dont la sortie est perpendiculaire a l'axe de rotation du turbomoteur
BR112017021584B1 (pt) * 2015-04-24 2023-01-17 Nuovo Pignone Tecnologie Srl Motor de turbina a gás
DE102017124467A1 (de) * 2017-10-19 2019-04-25 Abb Turbo Systems Ag Diffusoranordnung einer Abgasturbine
WO2019194797A1 (fr) * 2018-04-04 2019-10-10 Siemens Aktiengesellschaft Collecteur de gaz d'échappement pour une turbine

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191402848A (en) * 1914-02-03 1914-12-24 Karl Baumann Improvements in Steam Turbines.
US2840342A (en) * 1953-03-17 1958-06-24 David H Silvern Turbine exhaust
US2796732A (en) * 1953-05-12 1957-06-25 Napier & Son Ltd Gas producing apparatus of the gas turbine type
GB786088A (en) * 1955-03-30 1957-11-13 Napier & Son Ltd Exhaust duct assemblies for aircraft propulsion units of the combustion turbine type
US3120374A (en) * 1962-08-03 1964-02-04 Gen Electric Exhaust scroll for turbomachine
US3802187A (en) * 1972-06-01 1974-04-09 Avco Corp Exhaust system for rear drive engine
US3995432A (en) * 1975-07-28 1976-12-07 United Technologies Corporation Collector
JPS5464204A (en) * 1977-10-31 1979-05-23 Hitachi Ltd Low pressure casing of turbine
SU857516A1 (ru) * 1978-11-27 1981-08-23 Харьковский Ордена Ленина Политехнический Институт Им. В.И.Ленина Выхлопной патрубок осевой турбины
JPS5672206A (en) * 1979-11-14 1981-06-16 Nissan Motor Co Ltd Diffuser with collector
AT383396B (de) * 1984-08-17 1987-06-25 Proizv Ob Turbostroenia Niederdruckzylinder einer dampfturbine
US5188510A (en) * 1990-11-21 1993-02-23 Thomas R. Norris Method and apparatus for enhancing gas turbo machinery flow
US5174120A (en) * 1991-03-08 1992-12-29 Westinghouse Electric Corp. Turbine exhaust arrangement for improved efficiency
US5257906A (en) * 1992-06-30 1993-11-02 Westinghouse Electric Corp. Exhaust system for a turbomachine
US6419448B1 (en) * 2000-03-20 2002-07-16 Jerzy A. Owczarek Flow by-pass system for use in steam turbine exhaust hoods
US20050042087A1 (en) * 2003-05-28 2005-02-24 Hamer Andrew J. Method and apparatus for reducing total pressure loss in a turbine engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2008012294A3 *

Also Published As

Publication number Publication date
GB0614687D0 (en) 2006-08-30
CN101495715A (zh) 2009-07-29
DE602007007334D1 (de) 2010-08-05
RU2441987C2 (ru) 2012-02-10
US20090246010A1 (en) 2009-10-01
WO2008012294A3 (fr) 2008-03-13
GB2440343B (en) 2008-08-13
CN101495715B (zh) 2012-06-20
RU2009106437A (ru) 2010-08-27
WO2008012294A2 (fr) 2008-01-31
ES2346159T3 (es) 2010-10-11
GB2440343A (en) 2008-01-30
EP2044296B1 (fr) 2010-06-23

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