EP2158404A1 - Cône d'entrée d'un rotor de turbomachine - Google Patents

Cône d'entrée d'un rotor de turbomachine

Info

Publication number
EP2158404A1
EP2158404A1 EP08760534A EP08760534A EP2158404A1 EP 2158404 A1 EP2158404 A1 EP 2158404A1 EP 08760534 A EP08760534 A EP 08760534A EP 08760534 A EP08760534 A EP 08760534A EP 2158404 A1 EP2158404 A1 EP 2158404A1
Authority
EP
European Patent Office
Prior art keywords
turbomachine
impeller
nose
rotor
wall
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Withdrawn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
EP08760534A
Other languages
German (de)
English (en)
Inventor
Thomas MÖNK
Axel Spanel
Wolfgang Zacharias
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
Priority to EP08760534A priority Critical patent/EP2158404A1/fr
Publication of EP2158404A1 publication Critical patent/EP2158404A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • 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
    • F01D25/04—Antivibration arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a nose hood for a
  • a turbomachine is, for example, a conventional turbocompressor 101 as shown in FIGS. 8 and 9.
  • the turbocompressor 101 has a housing 102 and a turbocompressor rotor 103 surrounded by the housing 102.
  • the turbo compressor rotor 103 has a shaft 104 which is supported on a bearing 105 on the housing 102. Further, the turbo compressor rotor 103 has an impeller
  • the impeller 106 is a radial compressor impeller whose inflow in the axial direction of the shaft 104 and its outflow in the radial direction of the shaft 104 extends.
  • the inflow is guided in an inlet channel 107 of the turbocompressor 101 running in the axial direction of the shaft 104, so that the inflow into the shaft 106 in the axial direction of the shaft 104 hits the impeller 106.
  • a plurality of adjustable guide vanes 108 is arranged in the inlet passage 107, wherein the adjustable guide vanes 108 are combined to form a blade ring.
  • the hub portion is the
  • Leitschaufel 108 provided with a nose hood 110 which is fixed to the impeller 106 and thus rotates with the impeller 106 with.
  • the nose cap 110 is aerodynamically shaped and serves to minimize the interference of the hub portion of the impeller 106 in the inflow.
  • a stationary nose cap 111 may be provided in the area of the nose Hub region of the impeller 106 may be provided.
  • the nose cap 111 is held in position by a strut 109 fixed to the inlet passage 107.
  • the nose cap 111 is also aerodynamically shaped so as not to disturb the inflow to the impeller 106 as possible.
  • the strut 109 is aerodynamically shaped to minimize the interference of the strut 109 to the inflow as small as possible.
  • the strut 109 is disposed upstream of the adjustable vane 108, and the stationary nose dome 111 is formed longer than the rotating nose dome 110 in the axial direction of the shaft 104.
  • the nose cap 111 is spaced from the impeller 106 so that the impeller 106 does not contact the stationary nose cap 111 and thus can not grind and damage it.
  • the rotor dynamics of the turbocompressor rotor 103 i.
  • the dynamic vibration behavior of the turbocompressor rotor 103 during operation of the turbocompressor 101 depends essentially on the geometry and structural design of the turbocompressor rotor 103 and the dynamic properties inherent in the bearing 105, in particular the rigidity and damping of the bearing 105.
  • the bearing 105 is formed by a Kippsegmentgleitlager, which according to its design, construction and its operation has the appropriate stiffness and the corresponding damping.
  • Operating speed of the turbocompressor 103 passes usually at least one critical speed.
  • the radial oscillation amplitude of the turbocompressor rotor 103 must always be within design limits. These limits can be met if the rotor dynamics of the turbo compressor rotor 103 is set accordingly, in particular by the geometry and the structural design of the turbocompressor rotor 103 and the rigidity and the damping of the bearing 105.
  • the object of the invention is to provide a nose hood for a turbomachine rotor and a turbomachine with the turbomachine rotor having the nose hood, wherein the turbomachine has a balanced rotor dynamic behavior and thus is safe to operate.
  • the nose hood according to the invention for a turbomachine rotor which has an impeller arranged to fly to a bearing point of the turbomachine rotor, can be connected axially to guide an axial supply and / or outflow of the impeller and has a coupling device with which the impeller and the nose hood are radially connected are mechanically coupled, so that the vibration behavior of the turbomachine rotor can be influenced.
  • the turbomachine according to the invention has a turbomachine rotor, which has an impeller which is arranged to fly over the bearing point of the rotor, and the nose hood, wherein the impeller and the nose hood are radially coupled by means of the coupling device, so that the
  • Vibration behavior of the turbomachine rotor can be influenced.
  • the nose hood engages with the coupling device on the
  • Impeller which is cantilevered with respect to the bearing. Due to the flying bearing of the impeller is based on the bearing for the coupling device before a favorable lever arm for influencing the rotor dynamic behavior of the turbomachine rotor before. As a result, the rotor dynamic behavior of the turbomachine rotor can be influenced effectively and favorably by the nose hood.
  • the vibration of the turbomachine rotor is damped in operation by means of the coupling device, so that the maximum oscillation amplitude during operation of the turbomachine rotor is low.
  • the amplitude of vibration of the turbomachine rotor may be so great that operation of the turbomachinery with these gases results in damage to the turbomachine.
  • the oscillation amplitude of the turbomachine rotor is low, so that the turbomachine according to the invention can also be operated with these gases with high density and high reliability.
  • the provision of the nose hood according to the invention in the turbomachine according to the invention implements new machine concepts possible, especially in high gas density applications such as carbon dioxide compressed to a high pressure.
  • the nose cap thus provides an additional
  • Design element with which the damping of the vibration system can be favorably influenced.
  • the impeller has an externally accessible shaft bore having a cylindrical inner wall and the coupling means has a protrusion with a cylindrical outer wall insertable into the shaft bore forming a cylindrical annular gap between the outer wall of the protrusion and the inner wall of the shaft bore, and has a loading device, with which the annular gap for damping the vibration of the turbomachine rotor can be acted upon with pressurizing gas.
  • an annular, cylindrical gas cushion between the projection of the nose hood and the impeller is achieved with a flow of Beaufschlagungsgases through the annular gap.
  • the gas cushion has a damping characteristic with which the vibration of the turbomachine rotor can be damped.
  • the flow of the admission gas can be predetermined, so that the damping property of the gas cushion is adjustable.
  • the annular gap is provided, so that in spite of the damping coupling between the impeller and the nose hood, the impeller is not in contact with the nose hood. Therefore, the impeller and the nose hood are mechanically coupled without contact, so that mechanical wear in the coupling device on the impeller and the nose hood is prevented.
  • the loading device prefferable for feeding the pressurizing gas into the annular gap, the pressurizing gas being able to flow into the annular gap through the outer wall of the protrusion.
  • the supply gas is guided to the annular gap in the interior of the nose hood, so that an additional space outside the nose hood need not be provided for the supply of the annular gap with the pressurizing gas.
  • the loading device is designed to save space within the nose hood.
  • the coupling device has at least one labyrinth seal with labyrinth tips, which are attached to the outer wall of the projection and / or the inner wall of the impeller.
  • the apply gas flows through the labyrinth seal within the annular gap, i. around the labyrinth peaks, a multiplicity of vortices form at the labyrinth peaks, which increase the flow resistance of the admission gas in the annular gap.
  • the damping effect of the gas cushion which is formed with the pressurizing gas within the annular gap, improved.
  • the coupling device has a multiplicity of the labyrinth seals, between which in each case the admission gas for supplying the labyrinth seals can be fed into the annular gap.
  • the labyrinth seals can be individually designed individually so that an admission profile adapted to the rotor dynamics of the turbomachinery rotor can be generated within the annular gap.
  • the individual labyrinth seals in the axial direction of the turbomachine rotor and in the radial direction may be formed differently, so that the individual seals have different damping and stiffness properties.
  • the coupling means comprise a honeycomb honeycomb seal, which are attached to the outer wall of the projection and / or the inner wall of the impeller.
  • the coupling device has a plurality of the honeycomb seals, between each of which the pressurizing gas for supplying the honeycomb seal can be fed into the annular gap.
  • the individual honeycomb seals can be designed differently, so that the individual honeycomb seals have different damping and stiffness properties.
  • the nose cap is fixed stationary relative to the impeller.
  • the turbomachine is a radial compressor, which preferably has an inlet channel for the impeller and at least one strut with which the nose hood is suspended in the inlet channel.
  • the strut is stationarily stably positioned relative to the impeller, whereby forces from the impeller via the Coupling device can be transferred to the nose cap on the strut to the inlet channel.
  • the engagement of the projection of the nose cap in the impeller is safe and accurate, so that the damping effect of the coupling device is effective.
  • the strut is aerodynamically shaped.
  • the strut in the inlet channel has a low aerodynamic resistance, whereby the flow in the
  • the turbomachine has a high efficiency.
  • the strut is formed as a guide vane.
  • the strut is fixed in the inlet channel, it is stationary.
  • the strut is the guide vane, so that by means of the strut, the inlet flow in the direction of the impeller can be correspondingly advantageously deflected.
  • the inflow to the impeller is advantageously aerodynamically manipulatable.
  • the loading device can be supplied with the application gas through the strut.
  • the admission gas is guided from outside the inlet channel through the strut into the interior of the nose hood.
  • Inside the nosecap is that
  • Channel system provided by the supply gas is guided to the outer wall of the projection, wherein from the outer wall of the projection of the impingement gas flows into the annular gap.
  • the pressurizing gas is a process gas of the turbomachine.
  • the admission gas mixes with the process gas of the turbomachine. Since the apply gas has the same composition as the process gas, contamination of the process gas by the process takes place
  • the apply gas may be tapped from the turbomachine and a separate source of the apply gas need not be provided.
  • the turbomachine has at least one adjustable guide vane, which is arranged between the strut and the impeller.
  • the guide vane can advantageously be positively manipulated the inflow to the impeller, so that the impeller has a high efficiency.
  • Fig. 1 is a sectional view of the invention
  • FIG. 2 detail X from FIG. 1, FIG.
  • Fig. 4 shows a first embodiment of
  • Fig. 5 shows a second embodiment of
  • Fig. 6 shows a third embodiment of
  • Coupling device, 7 shows a fourth embodiment of the coupling device
  • Fig. 8 shows a first example of a conventional turbocompressor
  • FIG 9 shows a second example of a conventional turbocompressor.
  • a turbocompressor 1 has a housing 2 and a housing
  • Turbo compressor rotor 3 which is surrounded by the housing 2.
  • the turbocompressor rotor 3 has a shaft 4, which is supported on a bearing 5 on the housing 2. Furthermore, the turbocompressor rotor 3 has an impeller 6, which is fastened to the shaft 4.
  • the impeller 6 is arranged to be cantilevered relative to the bearing 5.
  • the impeller 6 has a shaft bore 7, in which the shaft 4 engages, wherein the shaft 4, the shaft bore 7 does not completely penetrate.
  • the shaft bore 7 is bounded by its inner wall 8, on which the shaft 4 rests firmly.
  • the turbocompressor 1 has an inlet channel 9, through which the inflow is guided to the impeller 6.
  • the impeller 6 is a Radialver Whyrrad with axial
  • a strut 10 is fixed to which a nose hood 11 is fixed, which is centered in the
  • Inlet channel 9 is arranged.
  • the nose hood 11 has a projection 12 which engages in the shaft bore 7 from the inlet channel 9 ago.
  • the projection 12 has an outer wall 13, which is located in the shaft bore 7. Due to the fact that the strut 10 holds the nose cap 11 centrally in the inlet channel 9, the outer wall 13 of the projection 12 is arranged concentrically with the inner wall 8 of the shaft bore 7. As a result, between the inner wall 8 of the Shaft bore 7 and the outer wall 13 of the projection 12, an annular gap 14 is formed.
  • a labyrinth seal 15 is provided which has two axially successive labyrinths 16, 16 a.
  • the labyrinths 16, 16 a are mounted on the outer wall 13 of the projection 12 and are arranged at a distance from the inner wall 8 of the shaft bore 7.
  • a channel system 17 is provided with which the annular gap 14 with a
  • the channel system has a channel system entrance 18 into which the admission gas flows into the channel system 17 and a channel system exit 19, which is located on the outer wall 13 of the projection 12.
  • the channel system outlet 19 is located inter alia between the two labyrinths 16, so that between the two labyrinths 16, the pressurizing gas flows into the annular gap 14.
  • the housing 2 has a feed nozzle 20 and a feed line 21, via which the admission gas is guided to the strut 10.
  • the strut 10 is hollow and is connected with its cavity to the channel system inlet 18 on the nose hood 11 gas-conducting, so that of the
  • the admission gas flowing through the channel system 17 splits into the stream (a) through the channel system exit 19 via the labyrinth 16 into the space immediately in front of the impeller 6 and into the stream (b) via the labyrinth 16a into the space between the projection 12 of FIG Shaft 4, from where it is also discharged through an end opening 19 a in the space immediately in front of the impeller 6. While the pressurizing gas flowing through the channel system outlets 19 flows along the labyrinths 16, 16a through the annular gap 14, it forms a gas cushion.
  • Turbo compressor rotor 3 Due to the rotor dynamic behavior of the turbocompressor rotor 3, this experiences a bending vibration, which leads to a dynamic radial movement of the impeller 6.
  • the nose hood 11 is held stable and stationary by means of the strut 10 in the inlet channel 9.
  • a radial relative movement between the outer wall 13 of the projection 12 and the inner wall 18 of the shaft bore 7 forms, whereby the annular gap 14 changes its shape dynamically.
  • the dynamic radial movement of the impeller 6 is restricted so that the rotor-dynamic behavior of the turbocompressor rotor 3 is improved.
  • the turbocompressor rotor 3 and thus the impeller 6 rotate. Since the nasal hood 11 is stationary, a shear flow in the gas cushion is formed in the annular gap 14. As a result, the gas cushion has a high damping effect.
  • the turbocompressor 1 further comprises an adjustable stator 22, which is arranged in the axial direction of the turbo compressor rotor 3 between the impeller 6 and the strut 10.
  • the adjustable stator 22 By means of the adjustable stator 22, the inflow can be manipulated to the impeller 6, in particular be subjected to a twist, so that the impeller 6 has a high thermodynamic efficiency.
  • Fig. 4 is a first embodiment of
  • Coupling device shown schematically, wherein the labyrinth 16 applied to the projection 12 of the nose hood 11 is stored stationary. Arranged in the annular gap 14 opposite the labyrinth 16, the inner wall 8 of the shaft bore 6, which is moved relative to the labyrinth 16, is located.
  • Fig. 5 is a second embodiment of
  • Coupling device shown schematically, wherein the labyrinth 16 is attached to the inner wall 8 of the shaft bore 7, so that the labyrinth 16 rotates relative to the outer wall 13 of the projection 12.
  • a third embodiment of the coupling device is shown, which is comparable to the first embodiment of FIG. 4, but with the difference that instead of the labyrinth 16 a honeycomb seal 23 is provided with a honeycomb 24.
  • the fourth embodiment of the coupling device shown in FIG. 7 is comparable to the second embodiment shown in FIG. 5, wherein, instead of the labyrinth 16, the honeycomb seal 23 with the honeycomb 24 is provided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un cône d'entrée d'un rotor de turbomachine qui présente une roue mobile disposée de manière volante par rapport à un point de support du rotor de turbomachine. Le cône d'entrée peut être raccordé axialement à la roue mobile pour guider un écoulement d'afflux et ou de sortie axial de la roue mobile et présente un dispositif d'accouplement avec lequel la roue mobile et le cône d'entrée peuvent être accouplés radialement de manière mécanique, de sorte que le comportement d'oscillation du rotor de turbomachine puisse être influencé. La turbomachine avec le rotor de turbomachine présente le cône d'entrée, et la roue mobile et le cône d'entrée sont accouplés radialement au moyen du dispositif d'accouplement de sorte que l'oscillation du rotor de turbomachine soit amortie.
EP08760534A 2007-06-27 2008-06-05 Cône d'entrée d'un rotor de turbomachine Withdrawn EP2158404A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08760534A EP2158404A1 (fr) 2007-06-27 2008-06-05 Cône d'entrée d'un rotor de turbomachine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP07012621A EP2009290A1 (fr) 2007-06-27 2007-06-27 Capot nasal pour l'arbre d'une turbomachine
EP08760534A EP2158404A1 (fr) 2007-06-27 2008-06-05 Cône d'entrée d'un rotor de turbomachine
PCT/EP2008/056955 WO2009000618A1 (fr) 2007-06-27 2008-06-05 Cône d'entrée d'un rotor de turbomachine

Publications (1)

Publication Number Publication Date
EP2158404A1 true EP2158404A1 (fr) 2010-03-03

Family

ID=38794252

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07012621A Withdrawn EP2009290A1 (fr) 2007-06-27 2007-06-27 Capot nasal pour l'arbre d'une turbomachine
EP08760534A Withdrawn EP2158404A1 (fr) 2007-06-27 2008-06-05 Cône d'entrée d'un rotor de turbomachine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07012621A Withdrawn EP2009290A1 (fr) 2007-06-27 2007-06-27 Capot nasal pour l'arbre d'une turbomachine

Country Status (4)

Country Link
US (1) US8545174B2 (fr)
EP (2) EP2009290A1 (fr)
CN (1) CN101688542B (fr)
WO (1) WO2009000618A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102767533B (zh) * 2012-08-10 2014-09-17 三一能源重工有限公司 一种油封密封结构及压缩机
DE102017223791A1 (de) 2017-12-27 2019-06-27 Siemens Aktiengesellschaft Wellendichtungsanordnung einer Turbomaschine, Turbomaschine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2784551A (en) * 1951-06-01 1957-03-12 Orin M Raphael Vortical flow gas turbine with centrifugal fuel injection
US3756741A (en) * 1971-12-17 1973-09-04 Jacuzzi Bros Inc Jet propulsion pump assembly
US4325673A (en) * 1980-03-10 1982-04-20 General Motors Corporation Variable vane seal
DE3628687A1 (de) * 1986-08-23 1988-02-25 Daimler Benz Ag Lagerung der auf einem wellenende einer rotorwelle nebeneinander angeordneten laufraeder von verdichter und turbine im turbinengehaeuse
US4997340A (en) * 1989-09-25 1991-03-05 Carrier Corporation Balance piston and seal arrangement
JPH10306948A (ja) * 1997-05-08 1998-11-17 Tochigi Fuji Ind Co Ltd 冷却装置
SE510979C2 (sv) * 1997-10-23 1999-07-19 Carl Fredriksson Anordning vid turbomaskin
CN2806843Y (zh) * 2005-07-22 2006-08-16 江津增压器厂 一种用于涡轮增压器的压气机

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO2009000618A1 *

Also Published As

Publication number Publication date
US8545174B2 (en) 2013-10-01
CN101688542B (zh) 2011-12-21
US20100183432A1 (en) 2010-07-22
CN101688542A (zh) 2010-03-31
WO2009000618A1 (fr) 2008-12-31
EP2009290A1 (fr) 2008-12-31

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