EP2128448B1 - Getriebeturbomaschine für einen Maschinenstrang, Maschinenstrang mit und Getriebe für Getriebeturbomaschine - Google Patents

Getriebeturbomaschine für einen Maschinenstrang, Maschinenstrang mit und Getriebe für Getriebeturbomaschine Download PDF

Info

Publication number
EP2128448B1
EP2128448B1 EP09006649.9A EP09006649A EP2128448B1 EP 2128448 B1 EP2128448 B1 EP 2128448B1 EP 09006649 A EP09006649 A EP 09006649A EP 2128448 B1 EP2128448 B1 EP 2128448B1
Authority
EP
European Patent Office
Prior art keywords
pinion
turbo machine
machine
compressor
transmission
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.)
Active
Application number
EP09006649.9A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2128448A3 (de
EP2128448A2 (de
Inventor
Ole Hansen
Arindam Khan
Klaus-Dieter Mohr
Gerd-Ulrich Dr. Woelk
Hans-Otto Jeske
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.)
MAN Energy Solutions SE
Original Assignee
MAN Energy Solutions SE
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 MAN Energy Solutions SE filed Critical MAN Energy Solutions SE
Publication of EP2128448A2 publication Critical patent/EP2128448A2/de
Publication of EP2128448A3 publication Critical patent/EP2128448A3/de
Application granted granted Critical
Publication of EP2128448B1 publication Critical patent/EP2128448B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
    • F04D25/163—Combinations of two or more pumps ; Producing two or more separate gas flows driven by a common gearing arrangement
    • 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
    • F05D2220/70—Application in combination with
    • F05D2220/72—Application in combination with a steam turbine
    • 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
    • F05D2260/40—Transmission of power

Definitions

  • the present invention relates to a geared turbo machine, in particular a radial geared turbo machine, with an integrated load gear for a machine train, an integrated load gear for such a geared turbo machine, and a machine train with such a geared turbo machine and a further compressor, in particular a main compressor.
  • a machine train generally has a drive unit, for example a steam turbine, a gas turbine or an expander, in particular an expansion or residual gas turbine, and one or more compressors driven by this drive unit, for example for compressing air or other gases.
  • a drive unit for example a steam turbine, a gas turbine or an expander, in particular an expansion or residual gas turbine, and one or more compressors driven by this drive unit, for example for compressing air or other gases.
  • machine trains are known in which a double-driving steam turbine drives a booster compressor with several compressor stages on one side and a main compressor on the opposite side of the steam turbine, which draws in a medium, compresses it and feeds the booster compressor with a partial mass flow thereof, which for example, compressed to one to three pressure levels.
  • the speeds of the steam turbine, main and booster compressor must be coordinated with each other. While the speeds of the steam turbine and the compressor stages of the booster compressor should be relatively high for thermodynamic reasons, they are lower for the main compressor - due to its large diameter and the associated high centrifugal forces - and so far limit the speed of the steam turbine in particular, with regard to its Efficiency and their size is disadvantageous.
  • the booster compressor as a gear compressor, such as that from the EP 1 691 081 A2 , which is a gear compressor with an integrated gear according to the preamble of claim 1, or the DE 42 41 141 A1 is known to operate its compressor stages at higher speeds than the main compressor. Even in one of the DE 2413 674 C2 known three-stage gear compressor, the drive speed is quickly translated to higher speeds in the compressor stages.
  • the publication GB-A-2321502 discloses a turbocharger for a diesel engine, particularly an engine rated at 10 MW or more with a single turbine in a housing that drives a number of compressor impellers of compressors through a system, the impellers not being driven on the same shaft as the turbine but on separate waves.
  • DE-GM 7122098 it is also known in principle to reduce the speed of a steam turbine by means of a separate spur gear in front of the main compressor, which, however, due to the separate gear, not only the manufacturing and assembly costs, but also the axial length of the machine train and thus Transportation and building costs increased.
  • Known machine trains have further disadvantages.
  • the object of the present invention is to reduce at least one of the aforementioned disadvantages and to improve a machine train.
  • a speed-reducing load gear which is arranged between the drive unit and a compressor, into a gearbox of a geared turbo machine and thus to separate it from the compressor at the same time.
  • a geared turbo machine for a machine train comprises a drive pinion, which is non-rotatably connected to a drive shaft, one with the Drive pinion meshing large wheel and one or more, preferably at least two, in particular three or four turbomachine rotors.
  • These turbomachine rotors of the geared turbomachine each comprise a turbomachine shaft, one or more, preferably two, impellers non-rotatably connected to the turbomachine shaft and a turbomachine pinion rotatably connected to the turbomachine shaft, the turbomachine pinions of one or more turbomachine rotors being in engagement with the large wheel.
  • An impeller of a turbomachine rotor can be designed as a compressor or expander impeller.
  • two or more compressor impellers of the same turbomachine rotor and / or compressor impellers of different turbomachine rotors, preferably designed as radial compressors can form compressor stages of the geared turbo machine, which acts as a geared compressor.
  • two expander impellers of the same turbomachine rotor and / or expander impellers of different turbomachine rotors, preferably designed as radial expanders can form expander stages of the geared turbomachine, which act as gear expander.
  • both versions can also be combined, for example in that at least one turbomachine rotor equipped with one or more compressor impellers forms one or more compressor stages and at least one other turbomachine rotor equipped with one or more expander impellers forms one or more expander stages of the same geared turbomachine, and / or in that one or more turbomachine rotors are equipped with at least one compressor and at least one expander impeller and thus form both a compressor and an expander stage.
  • both pure single or multi-stage gear compressors with one or more compressor shafts equipped with at least one compressor impeller, pure single or multi-stage gear expanders with one or more expander shafts equipped with at least one expander impeller, as well as combined gear compressor / expander (“gear compander”) are generalizing referred to as a geared turbo machine, its rotors equipped with compressor and / or expander impellers as a turbo machine rotor.
  • the geared turbo machine now additionally has an output pinion of a speed-reducing load gear, which is connected in a rotationally fixed manner to an output shaft for driving a compressor drive shaft, which can be coupled to this output shaft, of a further compressor, in particular a main compressor of the machine train, which is separate from the geared turbo machine and is designed, in particular, as a single-shaft compressor can, preferably as an axial compressor, radial compressor, designed for example with a horizontal and / or vertical parting line or as an isothermal compressor, or as a combined axial-radial compressor.
  • a geared turbo machine thus combines for the first time a multi-shaft gearbox of a geared turbo machine and a load gear for a compressor separate therefrom.
  • An integrated gearbox, a geared turbo machine with such an integrated gearbox or a machine train according to this first aspect of the present invention has a number of advantages: by means of the speed-reducing gearbox, a drive unit, for example a steam turbine, a gas turbine or an expander, in particular a relaxation device - or residual gas turbine, which drives the drive shaft, a further compressor, in particular a main compressor, and the turbomachine rotors of the geared turbomachine are each operated in speed ranges that are favorable for them.
  • a drive unit for example a steam turbine, a gas turbine or an expander, in particular a relaxation device - or residual gas turbine, which drives the drive shaft
  • a further compressor in particular a main compressor
  • the turbomachine rotors of the geared turbomachine are each operated in speed ranges that are favorable for them.
  • the speed-reducing load gear can reduce a speed of the drive pinion with a gear ratio to a speed of the output pinion which is in the range from 1.25 to 1.45, preferably in the range from 1.3 to 1.4 and in particular in the range between 1.32 to 1.38.
  • a gear ratio is defined in the customary manner as the quotient of the drive to output speed, here here from the drive pinion speed divided by the output pinion speed, so that a reversal of the direction of rotation is also described by a positive gear ratio.
  • a turbomachine pinion can correspondingly have a transmission ratio with the drive pinion, which is in the range from 0.28 to 0.54, preferably in the range from 0.30 to 0.52 and in particular in the range between 0.32 to 0.50, the transmission ratio resulting from the amount of the quotient of the drive pinion speed divided by the turbo-machine pinion speed.
  • a steam turbine can be operated at a nominal speed in a range from 4000 to 7000 revolutions per minute (rpm), the turbo machine rotors of a booster compressor designed as a geared turbo machine at a nominal speed in a range from 10000 to 17000 rpm, and a main compressor designed as a single-shaft compressor at a nominal speed in a range from 2000 to 6000 rpm.
  • rpm revolutions per minute
  • booster compressor designed as a geared turbo machine at a nominal speed in a range from 10000 to 17000 rpm
  • main compressor designed as a single-shaft compressor at a nominal speed in a range from 2000 to 6000 rpm.
  • the drive and output pinions form a load gear, via which a large part of the power supplied by the drive unit, which can be in the range of 40 to 80 MW for steam turbines, for example, can be transmitted to the further compressor, which for example has a power in the range between 30 to 50 MW is applied.
  • a large part of the power supplied by the drive unit which can be in the range of 40 to 80 MW for steam turbines, for example, can be transmitted to the further compressor, which for example has a power in the range between 30 to 50 MW is applied.
  • Preferably at least half, particularly preferably at least 60% of the power is transferred from the drive shaft to the output shaft.
  • the large wheel distributes the remaining differential power accordingly to the turbomachine rotors in mesh with it.
  • the toothing widths of the turbomachine pinion and the large wheel can therefore advantageously be made smaller and are preferably at most 0.91 times the toothing width of the drive pinion.
  • Another significant advantage is that a separate gearbox is no longer required to reduce the speed of the drive unit to the speed of the additional compressor, which saves manufacturing and assembly work as well as installation space.
  • the further compressor is preferably accommodated in a housing which is separate from a housing of the geared turbomachine. In this way, a vibration-like decoupling between the geared turbo machine and the further compressor can be achieved particularly advantageously.
  • the further compressor is preferably spaced axially from the geared turbomachine, which is particularly advantageous if the further compressor is large as the main compressor.
  • the load gear is not accommodated in the housing of the further or main compressor, which can be advantageous in terms of vibration.
  • the geared turbomachine can have one or more expander stages, in that one or more turbomachine rotors are each equipped with at least one, two or more expander impellers.
  • a waste medium from the process implemented in the machine train and / or the process medium previously compressed in the main compressor, preferably a partial mass flow thereof can be relaxed and its enthalpy can be used to drive the further compressor and / or compressor stages of the geared turbomachine.
  • the geared turbo machine which then acts as a booster compressor of the machine train, can have one or more compressor stages, in that one or more turbomachine rotors are each equipped with at least one, two or more compressor impellers.
  • the medium compressed in the further compressor preferably a partial mass flow from the main compressor, can be further compressed in order to act as a coolant, for example after recooling and expansion.
  • other media that do not flow through the further compressor can also be compressed in the compressor stages of the geared turbine machine.
  • the geared turbo machine can thus equally act as a work machine and / or an engine, the turbo machine shafts exerting a torque on an impeller or being acted upon by a torque from the impeller.
  • an electric machine supporting the drive unit and / or drivable by the drive unit in particular a motor, a generator or a motor / generator, can be provided, the electric machine input shaft of which engages with the drive pinion, the large wheel, the output pinion or a turbomachine pinion stands or is coupled or non-rotatably connected to the drive shaft, the output shaft, the while of the large wheel or a turbine rotor.
  • additional Drive torque is introduced into the geared turbo machine by an electric motor or the mechanical power available there is converted into electrical power in a generator and stored, for example, made available to the machine train or fed into a power grid.
  • the cross-sections through which the flow passes, and thus the housing, impeller or blading diameters of the geared turbomachine can be made smaller due to the higher pressures and in particular when only a partial mass flow flows through from the main compressor than with the other compressor.
  • a smallest cross-section of the further compressor through which flow therefore has at least 1.05 times, preferably at least 1.1 times and in particular at least 1.2 times the smallest cross-section of the geared turbomachine through which there is flow.
  • a non-rotatable connection for example between the drive pinion and drive shaft, turbomachine pinion and turbomachine shaft or output pinion and output shaft, is a detachable connection, which can comprise, for example, a spline shaft and / or screws, as well as a non-detachable connection, in particular a welded connection or an integral design , understood for example as a one-piece original and / or shaped part.
  • a clutch between the output shaft and the separate compressor drive shaft that can be coupled with it can be realized, for example, via a flange connection, a clutch for compensating for axial and / or angular misalignment, and / or a switchable or self-switching clutch, for example an overload clutch.
  • both output shafts and compressor drive shafts that are connected to one another in a releasable and non-releasable manner are referred to as couplable.
  • a coupling between the output shaft and the compressor drive shaft can advantageously dampen torsional vibrations, axial shocks or the like.
  • an engagement comprises, on the one hand, a direct engagement, ie a meshing of toothings, for example single or double helical toothings, of the two elements which are in engagement with one another.
  • a direct engagement ie a meshing of toothings, for example single or double helical toothings, of the two elements which are in engagement with one another.
  • this also includes an indirect intervention with the interposition of one or more gear stages, in particular Includes spur gear and / or planetary gear stages, such as from the DE 42 41 141 A1 is known, the disclosure of which is expressly included in this description in this regard.
  • a geared turbo machine according to the first aspect of the present invention has two or more turbo machine rotors, all turbo machine pinions can be meshed with the large wheel, which enables a more even loading of the large wheel and a narrower built geared turbo machine.
  • one or more turbomachine pinions can also be in engagement with the output pinion. This increases the distance between these turbomachine rotors and those driven by the large wheel, which advantageously increases the design freedom of the individual turbomachine rotors or the compressor and / or expander stages formed by them.
  • an axis of rotation of the drive pinion, an axis of rotation of the large wheel and an axis of rotation of the output pinion are arranged in a common, preferably substantially horizontal, plane. This advantageously reduces the overall height of the geared turbo machine perpendicular to this plane.
  • the axis of rotation of a turbomachine pinion meshing with the large wheel and / or the axis of rotation of a turbomachine pinion meshing with the output pinion can also be arranged in this plane and thus further reduce the overall height. If further turbomachine pinions are in engagement with the large wheel, their axes of rotation are preferably arranged in a further common plane which is parallel to the plane in which the axis of rotation of the large wheel lies.
  • a geared turbo machine preferably has a multi-part housing which accommodates the drive pinion, the large wheel, the output pinion and the turbomachine pinion.
  • the axes of rotation lie in one or two mutually parallel, preferably horizontal planes, it is preferred that this housing is divided in this plane or these planes. This simplifies assembly and maintenance.
  • the output pinion and the large wheel are preferably arranged in the same transverse plane of the drive pinion.
  • This builds the geared turbo machine advantageous axially particularly short.
  • the large wheel and the output pinion can also be arranged in axially offset planes, the large wheel or the drive pinion then advantageously being designed in two stages and two different pitch circle diameters for engagement with drive and turbo-machine pinions (for a two-stage large wheel) or for engagement with the large wheel and output pinion (for two-stage drive pinion).
  • Such an arrangement can be made narrower, particularly in the plane of the axes of rotation of the drive pinion and large wheel.
  • the drive pinion, the large wheel, the turbomachine pinions and the output pinion are preferably axially mounted in a housing of the geared turbine machine, which for this purpose has, for example, two to six axial bearings.
  • the rest of the drive pinion, the large wheel, the turbomachine pinions and the driven pinion can then be supported axially on these elements, in particular upper pressure combs, axially supported in the housing of the geared turbomachine, as is known from the DE 42 41 141 A1 are known, the disclosure of which is expressly included in this description in this regard.
  • the axial thrust of the impellers or the drive unit can be absorbed with less structural effort.
  • the further compressor can be arranged particularly advantageously on the side of the geared turbo machine opposite the drive unit.
  • the drive unit which is thus free on the side opposite the geared turbomachine, as a steam turbine with an axial outflow.
  • a condenser connected downstream of the steam turbine can also be arranged essentially on the same horizontal plane, which significantly reduces the overall height of such a machine train.
  • a steam turbine with axial outflow is provided as the drive unit.
  • the above-explained first and second aspects of the present invention according to claims 1, 10 and 12 and 18 respectively solve the aforementioned Task to improve a machine train. Both aspects are particularly advantageously combined with one another, but this is not mandatory.
  • Fig. 1 , 3rd show the essential elements of a machine train according to a first embodiment of the present invention, in which the first and second aspects of the present invention are realized together.
  • Fig. 1 4 denotes a main compressor designed as an axially suction single-shaft compressor, which draws air in the manner indicated by an arrow and compresses it to, for example, 7 bar.
  • a partial mass flow of this compressed air is then fed in a manner not shown to a first turbomachine rotor 3.10 of a booster compressor, which is designed as a geared turbomachine 2 explained in more detail below.
  • the first turbomachine rotor 3.10 comprises two compressor impellers 3.12, 3.13 (indicated by triangles) Figure 3B ), which sit on a common turbomachine shaft and rotate in spiral housings (not shown) in order to further compress the air supplied by the main compressor, and thus form two compressor stages of the booster compressor 2. From these, the air then becomes a second turbomachine rotor 3.20 of the booster compressor in a manner not shown in any more detail 2 supplied, the two compressor impellers 3.22, 3.23 (also indicated as triangles ( Figure 3B ) have a smaller diameter and rotate faster than the impellers of the first turbomachine rotor 3.10 in order to further compress the air and thus form two further compressor stages of the booster compressor 2.
  • the air which is further compressed therein is then fed to a third turbomachine rotor 3.30 of the booster compressor 2, the two compressor impellers 3.32, 3.33 ( Figure 3B ) have a further smaller diameter and rotate faster than the impellers of the second turbomachine rotor 3.20 in order to finally compress the air to a desired final pressure of 75 bar and thus form two further compressor stages of the six-stage booster compressor 2.
  • three turbo machine rotors 3.10, 3.20 and 3.30 of the booster compressor 2 are structurally analogous.
  • the turbo machine pinion 3.11 of the first, slowest rotating turbo machine rotor 3.10 has the largest diameter
  • more, for example four or five turbomachine rotors, each with one, two or more impellers, are also possible.
  • the large wheel 2.2 is in turn driven by a drive pinion 2.1 of smaller diameter, which is rotatably fixed in a manner not shown with a drive shaft of a steam turbine 1 ( Fig. 1 ) or another drive unit, for example a gas turbine or an expander, is connected so that the turbine speed is rapidly translated to the turbomachine shafts of the three turbomachine rotors with different transmission ratios.
  • a drive pinion 2.1 of smaller diameter which is rotatably fixed in a manner not shown with a drive shaft of a steam turbine 1 ( Fig. 1 ) or another drive unit, for example a gas turbine or an expander, is connected so that the turbine speed is rapidly translated to the turbomachine shafts of the three turbomachine rotors with different transmission ratios.
  • the axis of rotation of an output pinion 2.3 is arranged, which is connected to the drive pinion 2.1 on the large wheel 2.2 opposite side is engaged.
  • Drive pinion 2.1, large gear 2.2 and output pinion 2.3 are in the same transverse plane (plane of the Figure 3A ) arranged so that the same toothing of the drive pinion 2.1 meshes with both the large gear 2.2 and the output pinion 2.3.
  • Figure 3B schematically indicated, due to the different torque flows, the tooth width of the turbo machine pinion 3.11, 3.21, 3.31 is smaller than that of the input and output pinion 2.1, 2.3.
  • the diameter of the driven pinion 2.3 is larger than the diameter of the driving pinion 2.1, so that the speed of the steam turbine 1, which drives the driving pinion 2.1 seated on its drive shaft, onto the driven shaft with the driven pinion 2.3 is slowed down.
  • the output shaft with the output pinion 2.3 is by a in Fig. 1 indicated coupling with a compressor drive shaft 4.1 of the main compressor 4 designed as a single-shaft compressor ( Fig. 1 ) connected, so that the turbine drives it with a reduction in the slow. Input and output pinions 2.1, 2.3 thus form a speed-reducing load gear, via which the majority of the turbine power is transferred to the main compressor 4.
  • steam turbine 1, booster compressor 2 and main compressor 4 can be operated simultaneously in optimal speed ranges.
  • the speed of the steam turbine 1 can be higher with a lower main compressor speed, which improves the efficiency of the steam turbine 1 and allows the use of smaller, faster rotating steam turbines.
  • Input and output pinions 2.1, 2.3, the large gear 2.2 and the engaging turbo machine pinions 3.11, 3.21 and 3.31 are accommodated in a common housing (not shown).
  • This three-part housing is in the Figure 3A Dash-dotted plane, in which the axes of rotation of the input and output pinions 2.1, 2.3, large gear 2.2 and turbo machine pinion 3.11 lie, horizontally divided, so that they can be easily mounted in a first, lower housing part on which a second, middle housing part is put on.
  • the axes of rotation of the turbomachine pinions 3.21, 3.31 of the second and third turbomachine rotors 3.20 and 3.30 lie in one Figure 3A dash-dot indicated further horizontal plane, which is parallel to the plane in which the axes of rotation of the input and output pinions 2.1, 2.3, large wheel 2.2 and turbo machine pinion 3.11 lie.
  • the housing is also divided horizontally in this plane, so that the turbomachine pinions 3.21, 3.31 can be mounted in the middle housing part in a simple manner after the middle housing part has been put in place. on which a third, upper housing part is placed.
  • turbo machine pinions 3.21, 3.31 in the further horizontal plane vertically above the plane of the input, output pinion and large wheel axis of rotation advantageously means that no installation space is required below the large wheel 2.2 for the arrangement of turbo machine rotors.
  • the main compressor 4 has a housing which is separate from the booster compressor 2 and is connected to it only via the compressor drive shaft 4.1.
  • the two housings of the main compressor and the booster compressor which for example rest on a concrete or metal foundation (not shown), can thus be largely decoupled in terms of vibration technology.
  • the steam turbine 1 drives the booster compressor 2 and the main compressor 4 arranged on the opposite side with only one drive shaft.
  • a steam turbine with only one end of the shaft advantageously has other natural frequencies or critical speeds - in particular, the area between neighboring natural frequencies or critical speeds, from which a sufficient distance should be kept during operation, to avoid resonance problems avoid, advantageously enlarged and thus the permissible operating range can be expanded.
  • the arrangement of the booster compressor 2 and the main compressor 4 on the same side of the steam turbine 1 enables an in Fig. 1 axial outflow indicated by an arrow from the steam turbine 1 to the opposite side of the main compressor 4 and the booster compressor 2 (to the left in Fig. 1 ) according to the second aspect of the present invention. This advantageously improves the efficiency of the steam turbine 1.
  • the axial exhaust steam from the steam turbine 1 flows into one of these condensers (not shown).
  • the capacitor of a machine train according to the second aspect of the present invention due to the axial outflow of the steam turbine 1, are arranged essentially on the same horizontal plane as this.
  • This advantageously enables a one-storey structure of the machine train, which leads to considerable cost savings due to the more compact foundation and the lower construction and thus building height.
  • FIG. 2 , 4th show in Fig. 1 , 3rd corresponding illustration, the essential elements of a machine train according to a second embodiment of the present invention, which essentially coincides with the first embodiment and in which the first and second aspects of the present invention are also realized together.
  • Elements that correspond to the first embodiment are identified by identical reference numerals, so that in this respect reference is made to the above explanations of the essentially identical first embodiment and only the differences between the first and second embodiments are discussed below.
  • the main compressor 4 sucks radially in the second embodiment.
  • the booster compressor 2 of the second embodiment differs from the booster compressor 2 of the first embodiment in the arrangement of the second and third turbomachine rotors 3.20, 3.30. While the axes of rotation of their turbomachine pinions 3.21, 3.31, as in Figure 3A shown, lie in a common further horizontal plane, which is parallel to the plane of the axes of rotation of the input, output pinion and large wheel, are inferior in the second embodiment Fig.
  • turbomachine pinions 3.11, 3.21 of the first and second turbomachine rotors 3.10, 3.20 mesh with the large wheel 2.2
  • the interposition of large wheel 2.2 or output pinion 2.3 can maintain the direction of rotation of the drive shaft in the turbomachine shafts, but can be reversed in the output shaft. If it is advantageous, the direction of rotation can of course also be oriented differently by interposing further gear stages between the input and output pinion, large wheel and / or turbo machine pinion.
  • the turbomachine pinion it is possible to design the turbomachine pinion as ring gears of a planetary gear which drives the turbomachine shaft, as is shown in FIG DE 42 41 141 A1 is described, the disclosure of which is expressly included in the present description.
  • FIG. 5 shows In Figure 3B , 4B Corresponding representation of the essential elements of a gear arrangement of a geared turbo machine with an integrated gear according to a third embodiment of the present invention, which essentially corresponds to the first and second embodiments and in which the first and second aspects of the present invention are also realized jointly.
  • Elements corresponding to the first and second versions are identified by identical reference numerals, so that reference is made to the above explanations regarding the essentially identical first and second versions and only the differences between the first, second and third versions are discussed below.
  • the first turbomachine rotor 3.10 is replaced by an electric machine input shaft 5.1, which is connected to an electric machine 5, for example an electric motor or generator, via a clutch.
  • the electric machine input shaft 5.1 has an electric machine pinion 2.4, which engages with the large wheel 2.2 instead of the turbo machine pinion 3.11.
  • a higher speed of the drive pinion 2.1 can be reduced to a lower speed of the electrical machine pinion, which is - depending on a mains frequency - for example 3000 or 3600 rpm.
  • the electric machine 5 is designed as a generator or motor / generator, mechanical power of the steam turbine 1, which is not required to drive the main compressor 4 and the compressor stages of the geared turbine machine 2, can be converted into electrical energy and fed into a power supply network, for example.
  • the electric machine 5 is designed as a motor or motor / generator, conversely, additional torque for driving the main compressor 4 and the compressor stages of the geared turbo machine 2 can be fed into the geared turbo machine 2.
  • one impeller of the third turbomachine rotor 3.30 is designed as an expander impeller 3.34, the other as in the first and second embodiment as a compressor impeller 3.33, which is In Fig. 5 is indicated by triangles in the same direction.
  • the geared turbo machine 2 thus has five compressor stages and one expander stage and at the same time acts as a working machine and as an engine (compander).
  • a medium for example a residual gas arising in the process, can be relaxed in the expander stage of the expander impeller 3.34 and thus additional torque for driving the main compressor 4 and the compressor stages of the geared turbine engine 2 in the geared turbo machine 2 are fed.
  • Fig. 6 shows in Fig. 5 Corresponding representation of the essential elements of a gear arrangement of a geared turbomachine with an integrated gear according to a fourth embodiment of the present invention, which essentially corresponds to the third embodiment and in which the first and second aspects of the present invention are also realized jointly.
  • Matching elements are identified with identical reference numerals, so that in this respect reference is made to the above explanations for the essentially identical third embodiment and only the differences between the third and fourth embodiments are discussed below.
  • the turbomachine pinions 3.21, 3.31 of the second and third turbomachine rotors 3.20, 3.30 both mesh with the large wheel 2.2 and their axes of rotation are arranged in a common horizontal plane, in which a dividing or separating joint of the housing of the geared turbomachine 2 is also arranged
  • the turbomachine pinion 3.21 of the turbomachine rotor 3.20 meshes with the large gear 2.2
  • the turbomachine pinion 3.31 of the turbomachine rotor 3.30 which carries a compressor impeller 3.33 and an expander impeller 3.34, is in engagement with the output pinion 2.3, as is also the case in the second version (cf. Figure 4B ) the case is.
  • Fig. 7 shows In Flg. 6 corresponding representation, the essential elements of a gear arrangement of a geared turbomachine with an integrated gear according to a fifth embodiment of the present invention, which essentially corresponds to the fourth embodiment and in which the first and second aspects of the present invention are also realized jointly.
  • Elements that correspond to the fourth embodiment are identified by identical reference numerals, so that in this respect reference is made to the above explanations of the fourth embodiment, which is essentially identical in construction, and only the differences between the fourth and fifth embodiments are discussed below.
  • a further turbomachine rotor 3.10 is provided with two compressor impellers 3.12, 3.13, the turbomachine pinion 3.11 of which engages with the electric machine pinion 2.4 on the side opposite the large wheel 2.2.
  • the geared turbo machine 2 thus has four compressor stages and two expander stages and also acts as a compander. While a partial mass flow of the air compressed in the main compressor 4 is further compressed in the compressor stages, a medium, for example a residual gas arising in the process, can be relaxed in the expander stages and thus additional torque for driving the main compressor 4 and the compressor stages of the geared turbo machine 2 into the geared turbo machine 2 be fed.
  • some or all of the compressor impellers of the geared turbomachine 2 can compress medium, preferably a partial mass flow thereof, that has flowed through the main compressor, or another medium, for example another process gas.
  • the geared turbo machine 2 can also compress different media with its different compressor impellers.
  • the steam turbine, main compressor and the turbomachine rotors of the geared turbomachine can each be operated in optimal speed ranges, which can be coordinated with one another by appropriate selection of the ratios in the gearbox of the geared turbomachine 2 and the load gear 2.1, 2.3.
  • the steam turbine can rotate faster due to the coupling with the slower rotating main compressor 4 via the speed-reducing load transmission, so that its efficiency improves and smaller steam turbine sizes can be used.
  • the integration of the load gear in the geared turbo machine 2 advantageously means that no separate load gear is required, which leads to a more compact machine train and less manufacturing and assembly work. Because of the main compressor housing, which is separate from this, it is partially vibration-related Decoupling of main compressor and geared turbo machine possible.
  • turbomachines in particular a gas turbine or an expander such as a relaxation or residual gas turbine, can equally be used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gear Transmission (AREA)
  • Supercharger (AREA)
EP09006649.9A 2008-05-29 2009-05-16 Getriebeturbomaschine für einen Maschinenstrang, Maschinenstrang mit und Getriebe für Getriebeturbomaschine Active EP2128448B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102008025695 2008-05-29
DE102008030103 2008-06-25
DE102008031116.2A DE102008031116B4 (de) 2008-05-29 2008-07-01 Getriebeturbomaschine für einen Maschinenstrang, Maschinenstrang mit und Getriebe für Getriebeturbomaschine

Publications (3)

Publication Number Publication Date
EP2128448A2 EP2128448A2 (de) 2009-12-02
EP2128448A3 EP2128448A3 (de) 2017-07-26
EP2128448B1 true EP2128448B1 (de) 2020-06-24

Family

ID=41254065

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09006649.9A Active EP2128448B1 (de) 2008-05-29 2009-05-16 Getriebeturbomaschine für einen Maschinenstrang, Maschinenstrang mit und Getriebe für Getriebeturbomaschine

Country Status (5)

Country Link
US (1) US8414250B2 (zh)
EP (1) EP2128448B1 (zh)
JP (1) JP4991789B2 (zh)
CN (1) CN101592045B (zh)
DE (1) DE102008031116B4 (zh)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011003525A1 (de) * 2011-02-02 2012-08-02 Siemens Aktiengesellschaft Gestufte Teilfuge an einem Getriebegehäuse
NO335032B1 (no) * 2011-06-01 2014-08-25 Vetco Gray Scandinavia As Undersjøisk kompresjonssystem med pumpe drevet av komprimert gass
JP5863320B2 (ja) 2011-08-05 2016-02-16 三菱重工コンプレッサ株式会社 遠心圧縮機
DE102012018468B4 (de) * 2012-09-19 2022-07-14 Man Energy Solutions Se Getriebeturbomaschine
DE102012217441A1 (de) * 2012-09-26 2014-03-27 Siemens Aktiengesellschaft Getriebeverdichter
DE102012022131A1 (de) * 2012-11-13 2014-05-15 Man Diesel & Turbo Se Getriebeturbomaschine
DE102013208564A1 (de) 2013-05-08 2014-11-13 Voith Patent Gmbh Getriebe und Getriebeverdichteranlage
DE102013210497A1 (de) * 2013-06-06 2014-12-11 Siemens Aktiengesellschaft Getriebeverdichter
US20150211539A1 (en) 2014-01-24 2015-07-30 Air Products And Chemicals, Inc. Systems and methods for compressing air
DE102014221339A1 (de) * 2014-10-21 2016-04-21 Siemens Aktiengesellschaft Gestufte Teilfuge an einem Getriebegehäuse
WO2016079281A1 (de) 2014-11-21 2016-05-26 Voith Patent Gmbh Getriebe und getriebeturbomaschine
DE102015001418A1 (de) * 2015-02-06 2016-08-11 Man Diesel & Turbo Se Getriebeturbomaschine
DE202015000883U1 (de) 2015-02-06 2015-03-16 Man Diesel & Turbo Se Getriebeturbomaschine
US11280226B2 (en) 2016-12-08 2022-03-22 Atlas Copco Comptec, Llc Waste heat recovery system
CN108445488B (zh) * 2018-06-14 2020-08-14 西安交通大学 一种激光主动成像探测系统及方法
KR20210141068A (ko) 2020-05-15 2021-11-23 한화파워시스템 주식회사 압신기
FR3115812B1 (fr) * 2020-10-29 2023-09-08 Safran Helicopter Engines Turbogénérateur à turbine libre comprenant une machine électrique réversible couplée à la turbine libre
JP2021156281A (ja) 2021-02-01 2021-10-07 三菱重工コンプレッサ株式会社 ギアド圧縮機、ギアド圧縮機の設計方法
JP2023082432A (ja) 2021-12-02 2023-06-14 三菱重工コンプレッサ株式会社 ギアド圧縮機

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE7122098U (de) 1971-06-08 1972-02-10 Aeg-Kanis Gmbh Stirnradgetriebegehaeuse
US3826587A (en) 1973-04-10 1974-07-30 Ingersoll Rand Co Centrifugal gas compressor unit
DE4003482A1 (de) * 1990-02-06 1991-08-08 Borsig Babcock Ag Getriebe-turboverdichter
US5402631A (en) * 1991-05-10 1995-04-04 Praxair Technology, Inc. Integration of combustor-turbine units and integral-gear pressure processors
DE9201858U1 (de) * 1992-02-11 1992-04-02 Mannesmann AG, 4000 Düsseldorf Getriebe-Turboverdichter
DE4234739C1 (de) 1992-10-15 1993-11-25 Gutehoffnungshuette Man Getriebe-Mehrwellenturbokompressor mit Rückführstufen
DE4241141A1 (de) * 1992-12-07 1994-06-09 Bhs Voith Getriebetechnik Gmbh Verdichteranlage mit einem im Antriebsstrang zwischen einer Antriebseinheit und einem Verdichterbereich der Anlage eingeschalteten Zahnradgetriebe
JPH10196313A (ja) * 1997-01-13 1998-07-28 Fuji Electric Co Ltd 軸流排気式の復水器
GB2321502B (en) 1997-01-24 2001-02-07 Europ Gas Turbines Ltd Turbocharger arrangement
US6116027A (en) 1998-09-29 2000-09-12 Air Products And Chemicals, Inc. Supplemental air supply for an air separation system
DE102005002702A1 (de) * 2005-01-19 2006-07-27 Man Turbo Ag Mehrstufiger Turbokompressor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP2128448A3 (de) 2017-07-26
JP4991789B2 (ja) 2012-08-01
JP2009287555A (ja) 2009-12-10
CN101592045B (zh) 2012-08-15
DE102008031116A1 (de) 2009-12-03
US20090297337A1 (en) 2009-12-03
CN101592045A (zh) 2009-12-02
US8414250B2 (en) 2013-04-09
EP2128448A2 (de) 2009-12-02
DE102008031116B4 (de) 2022-02-03

Similar Documents

Publication Publication Date Title
EP2128448B1 (de) Getriebeturbomaschine für einen Maschinenstrang, Maschinenstrang mit und Getriebe für Getriebeturbomaschine
EP0592803B1 (de) Getriebe-Mehrwellenturbokompressor
EP0521379B1 (de) Propfantriebwerk mit gegenläufigem Niederdruckverdichter (Booster)
EP2569542B1 (de) Mehrstufiger getriebeverdichter
EP1726814B1 (de) Strahltriebwerk
DE102015001418A1 (de) Getriebeturbomaschine
DE10134245A1 (de) Getriebe mit Leistungsaufteilung
DE102018133388B4 (de) Planetengetriebe und Verfahren zur Montage eines Planetengetriebes
DE102012022131A1 (de) Getriebeturbomaschine
EP1757839A1 (de) Schwerlastgetriebe für Walzenschüsselmühlen
EP2136032A2 (de) Gasturbine mit zumindest einer mehrstufigen, mehrere Verdichtermodule umfassenden Verdichtereinheit
DE102014225136A1 (de) Getriebeverdichter, Anordnung mit einem Antrieb und einem Getriebeverdichter
WO2011023690A2 (de) Verdichter
DE102019117038A1 (de) Getriebe und Gasturbinentriebwerk
DE102005023161A1 (de) Verfahren und Anlage zur Herstellung von Salpetersäure
WO2014195390A1 (de) Getriebeverdichter
DE102009003386A1 (de) Turbinensysteme zur Energieerzeugung
DE102011121925A1 (de) Verdichter und Verfahren zum Betrieb eines Verdichters
EP2711503B1 (de) Getriebeturbomaschine
DE202015000883U1 (de) Getriebeturbomaschine
EP2143912A1 (de) Gasturbine mit zumindest einer mehrstufigen, mehrere Verdichtermodule umfassenden Verdichtereinheit
EP3299630A1 (de) Anordnung zum verdichten
EP3597887B1 (de) Getriebeanordnung und verfahren zu deren herstellung
EP3767102A1 (de) Triebstranganordnung
WO2021008901A1 (de) Wellenkupplung mit einer steckverzahnung

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MAN DIESEL & TURBO SE

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA RS

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 25/16 20060101ALI20170616BHEP

Ipc: F04D 25/02 20060101AFI20170616BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20170828

RBV Designated contracting states (corrected)

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MAN ENERGY SOLUTIONS SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20200211

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1284158

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502009016224

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200925

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200924

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200924

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200624

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201026

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201024

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502009016224

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20210325

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502009016224

Country of ref document: DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20210516

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210531

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210516

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210531

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210517

Ref country code: CZ

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210516

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20210531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210516

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210516

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210531

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1284158

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210516

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210516

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210516

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20090516

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200624