Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23D—BURNERS
  • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
  • F23D11/36—Details, e.g. burner cooling means, noise reduction means
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
  • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
  • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
  • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
  • F23C2900/07001—Air swirling vanes incorporating fuel injectors
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
  • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

• the invention relates to a burner for a gas turbine with a central burner axis and a burner axis at least partially surrounding Vormischpassage.
• the premix passage thus has a passage cross-sectional area which runs around the burner axis .
• the central burner axis is an imaginary, infinitely long line.
• the passage cross-sectional area can ⁇ example, be arranged as a full circle around the burner axis or annular.
• the premix passage can run coaxially (same axis of rotation) to the burner axis.
• the diameter of the ring or full circle may vary along the burner axis section.
• the premix passage can be formed, at least in sections, as a ring-chamber passage (annular cross-section), which can transition into a premix passage section, which is designed as a full circle in cross-section.
• the Vormischpassage is externally be of a wall adjacent ⁇ radially.
• the premix passage can be flowed through during operation of compressor air. It serves to mix fuel and air, wherein a burner lance or burner hub and a number of fuel injectors are arranged in the premix passage.
• the fuel injectors extending from the burner lance / hub toward the wall are fluidly coupled to fuel nozzles that are at least partially interconnected by the burner lance / hub.
• the fuel injectors may include, for example, both fuel nozzles for gaseous fuel and fuel nozzles for oil operation.
• the burner lance can also be called a burner hub in the context of this invention.
• the burner lance can be arranged centrally in the premix passage.
• the burner lance can protrude from upstream into the premix passage, so that the passage is limited only in sections radially inward from the burner lance.
• the premix passage may have a full circular cross-sectional area downstream of the burner lance.
• the burner lance may also extend substantially to the exit of the premix passage.
• the premix passage can be bounded radially inward, at least in sections, by a burner hub with a substantially truncated cone-shaped surface arranged centrally in the passage, which delimits the premix passage from radially upstream to an end region of the hub.
• the premix passage can pass downstream of the hub into a premix area which is completely circular in cross section.
• the hub thus has the Vormischpassage an annular passage cross-sectional area whose diam ⁇ ser can be reduced in the flow direction.
• further premix passages may be arranged in the burner hub or, for example, a central pilot burner.
• the premix passage may also be referred to as premix channel in the context of this invention.
• Fuel is injected into the premix passage via the fuel injectors and can pass through the premix passage downstream of the premix passage
• premix burners have low pollutant emissions during operation, they are more susceptible to the formation of pressure pulsations.
• Object of the present invention is to provide a burner of the type mentioned above for a gas turbine with which the operation of the burner, a reduction of harmful emissions ⁇ or a reduction of pressure pulsations is enables.
• the fuel supply arrangement comprises at least one fluidic oscillator with an interaction chamber, wherein an input of the interaction chamber is connected to a fuel passage of the fuel supply arrangement and a first output channel of the interaction chamber extends at least up to a first fuel nozzle and a second output ⁇ channel extends at least to a second Brennstoffdü ⁇ se, wherein the fluidic oscillator per tillka ⁇ nal a feedback line comprises, the remindp- ment line with its one end in the range downstream the at least one fuel nozzle opens out in the respective réelleka ⁇ nal and with the other end in a decidedsbe ⁇ area of the interaction chamber.
• the at least first and the at least second fuel nozzle or the first and second group of fuel nozzles can be arranged on a common fuel injector and distributed in the radial direction in order to distribute the fuel as homogeneously as possible in the premix passage.
• the at least first fuel nozzle could for example also on a suction side and the second fuel nozzle min ⁇ least angeord- on a pressure side of a swirl blade-like Brennstoffinj ector be net.
• the first and second group of fuel nozzles may be Kgs ⁇ NEN example, arranged at different Brennstoffinj ek- factors.
• Fluidic oscillators have long been known as fluid ⁇ controls that manage without expensive valves. In ⁇ game as they are used for supplying air into the boundary layer from airfoil to avoid separation of the boundary layer.
• Fluidic oscillators are operated with a pressurized fluid stream at their inlet. This fluid flow is in the interaction chamber in a
• Fluidic oscillators with feedback lines are known in the prior art which connect an output region of the interaction chamber to an input region of the interaction chamber to stabilize the oscillation in the interaction chamber.
• the invention it is now proposed not to open the feedback lines into the exit area of the interaction chamber, as in the prior art, but rather into an exit channel into a region downstream of at least one fuel nozzle or fuel nozzle group to which the exit channel extends.
• This makes it possible according to the invention to incorporate the pressure conditions in the premix passage in the immediate premix passage area in front of the fuel nozzles into the feedback signal.
• the output channel may have downstream of the fuel nozzle or the fuel nozzle group, an end piece, in which opens the feedback channel.
• the feedback signal falls in the invention shown SEN training feedback line low and the fuel is longer ge in the off ⁇ passage flow than the reverse pressure conditions before the fuel nozzles of the output channel in the Vormischpassa-. If the static pressure in the Vormischpassage the region of a fuel nozzle group of low flows at Beaufschla ⁇ supply of the associated output of the interaction chamber more fuel through the corresponding output channel and the dyna ⁇ mix pressure in the output channel is higher.
• the associated feedback line opens into the output channel downstream of the at least one fuel nozzle of the output channel, the pressure in the feedback line opening into the end region of the outlet channel is higher and the associated fuel jet will more rapidly detach from the side wall in the input region of the interaction chamber and the next outlet apply fuel.
• the oscillation of the fuel jet in the interaction chamber will cause the output channel to be exposed to fuel for a longer period of time.
• at least one fuel nozzle opens into a region of the premixed gas mixture in which a higher pressure prevails. This compensates for the effect that, in general, less fuel escapes from fuel nozzles which open into a region of higher passenger pressure or more fuel
• thermoacoustic oscillation and delay time it should be noted that in a combustion chamber to an interaction of acoustic vibrations and fluctuations in the heat release can occur. These can swell each other if they are frequencies that coincide with so-called eigenmodes of the gas turbine. These eigenmodes depend on the size and design of the respective gas turbine. Such thermoacoustic Schwingun ⁇ insulation can cause significant damage to the components, forcing a shutdown of the plant easier during operation of the gas turbine.
• the delay time profile of the burner which arises during operation can be as wide as possible, the delay time the time is required for a fluid leaving the fuel nozzle to reach the flame.
• the through the fluidic oscillator with fuel versorg- th fuel nozzles and fuel nozzle groups of the burner have caused a fluctuation of the fuel concentration profile in the prior ⁇ beiströmenden compressor air on the basis of both temporal and local pulsating fuel jet at the outlet of the nozzle, which in turn thermo- improved acoustic stability due to a widened delay ⁇ time profile of the burner - for example in Ver ⁇ equal to burners with conventional pressure-swirl nozzles or full-jet nozzles.
• a frequency of the pulsating injection of the fuel can be adjusted for example by the size of the interaction-effect chamber.
• the burner may comprise a plurality of fluidic oscillators, which supply at least two output channels each with at least one fuel nozzle or group of fuel nozzles with fuel.
• fluidic oscillators which differ in their construction.
• the invention is not limited to a specific type of these fluidic oscillators. All these types have in common that they have an interaction chamber into which a pressurized fluid jet enters through an entrance.
• the jet periodically abuts different sidewalls of the interaction chamber so as to speak of an interaction of the beam with the sidewalls of the chamber, thereby exciting oscillation of the beam so that the beam passes through the chamber in different ways flows therethrough and consequently exits in the output region periodically through different outputs of the interaction chamber or leaves in different directions a central exit of the interaction chamber.
• the beam thus lies at least at two opposite side wall areas perio- or dissolves again, which is caused by delaying the flow.
• the operation of fluidic oscillators is prior art, so that the fluidic oscillators are only briefly explained here.
• the drawing also shows some types of fluidic oscillators.
• the invention is independent of the type of fluidic oscillator used.
• the invention is preferably made of a fluidic oscillator which results in a fanning of the oscillation of the incoming beam of divergent side walls in workedsbe ⁇ area of the interaction chamber.
• the invention preferably proceeds from a substantially rotationally symmetrical design of the interaction chamber with the input about the rotation axis at one end of the chamber and the output region with the at least one output arranged opposite one another.
• the operation of the feedback lines has already been explained above.
• the first output channel extends up to a first group of fuel nozzles and the second output channel extends up to a two ⁇ th group fuel nozzles, wherein the remindp ⁇ ment line in each case in an area downstream of the respective group Fuel nozzles opens into the output channel.
• the first and second group of fuel nozzles and the first and second fuel nozzle may be located in a GE ector example ⁇ common Brennstoffinj.
• Stoffinj can be, for example, a swirl bucket of a swirl generator. Since different pressures prevail in the premix passage on the suction and pressure sides of the blade, the first fuel nozzle or the first group of fuel nozzles can be arranged on the suction and the second fuel nozzle or fuel nozzle group on the pressure side of the swirl blade. According to the invention, an approximately equal amount of fuel can be injected on both sides of the blade.
• the feedback line is connected downstream of the at least one fuel nozzle to the output channel.
• the output channel and the feedback line may in this case have different diameters.
• the at least first fuel nozzle and the at least second fuel nozzle are arranged in different fuel injectors.
• the two fuel injectors are arranged substantially opposite one another on the burner lance.
• the fuel concentration in the premix passage in the at least two opposite regions can be matched to one another despite different pressure conditions in the regions.
• the at least two fuel nozzles and at least two fuel ⁇ nozzle groups are in a common Brennstoffinj ector angeord- net and differ in their radial arrangement in the Vormischpassage, so that the fuel concentration in the radial direction, despite different
• the fluidic oscillator can be arranged in the burner hub or in the fuel injector.
• the fluidic oscillator can be arranged in the burner hub or in the fuel injector.
• Burner more than two such connected to the fluidic oscillator groups of fuel nozzles in different Brennstoffinj comprises sectors. This makes it possible to even out the fuel concentration in the premix passage downstream of the different fuel injectors.
• a further advantageous embodiment of the invention can provide that the different reflectors Brennstoffinj are arranged circumferentially on the burner lance and the zuge culinaryi ⁇ gen output channels circumferentially on the interaction chamber.
• the at least one fuel injector comprises a main body on which the fuel nozzles covered by the fuel injector are arranged, wherein the main body is in particular a swirl blade of a swirl generator.
• the main body is in particular a swirl blade of a swirl generator.
• Interaction chamber at one end of the input and at an opposite end comprises an output region and is bounded by side walls or side wall portions which extend from the entrance of the chamber to the exit area enclosing the exit area, wherein at least two oppositely disposed side walls or sidewall areas diverge towards the exit at least in the entrance area.
• the oscillation of a fuel jet entering the interaction chamber through the inlet under pressure is, according to this embodiment of the invention, ignited by alternately applying the jet to the divergently formed fuel jet. Deten sidewall areas.
• the excitation of the oscillation in the interaction chamber according to the invention is based on the flow delay caused in the entrance area by the diverging sidewalls / sidewall regions.
• Minim ⁇ least two oppositely disposed side walls in a ⁇ transition area of the interaction chamber in the direction of output diverge at an angle greater than 7.5 degrees to a direction of inflow of the input of the interaction chamber.
• Aperture angles of the interaction chamber suitable for inducing oscillation are known in the art.
• the interaction chamber is essentially rotationally symmetrical, with the interaction chamber expanding in a diffuser-like manner at least in the entrance area in the direction of exit.
• the fluidic oscillator for example, be centrally located in the burner lance and rotatably circumferentially arranged on the burner lance Brennstoffinj provide fuel with fuel, each extending at least one Augangskanal the fluidic oscillator to each of a group of fuel nozzles of a Brennstoffinj ector.
• the reflectors to ⁇ current Brennstoffinj may together comprise two fuel stages. Each stage can have its own
• a further object of the invention is to specify a burner arrangement with a number of burners, - Wherein main burners are arranged in one or more concentrically arranged circles, with which a reduction of pollutant emissions or a reduction of pressure pulsations is made possible during operation of the burner assembly.
• At least one burner is designed according to one of claims 1 to 11.
• the burner may be a centrally located pilot burner of the burner assembly.
• the main burner of the burner assembly according to one of claims 1 to 11 may be formed.
• the burner according to the invention or the Bren ⁇ neran angel invention allows a particularly stable combustion, especially in partial load operation.
• Another object of the invention is to provide a combustion chamber for a gas turbine and a gas turbine, with wel ⁇ cher a reduction of pollutant emissions or a reduction of pressure pulsations in the combustion chamber is made possible during operation.
• the combustion chamber comprises at least one burner according to one of claims 1 to 12 and the gas turbine at least one combustion chamber according to claim 13.
• FIG. 4 shows schematically a detail of a combustion chamber 10 of
• FIG. 5 schematically shows a main burner of the burner assembly shown in Figure 4 in a longitudinal section
• FIG. 6 shows schematically a burner according to the invention according to a first embodiment of the invention in a longitudinal section
• FIG. 7 schematically shows a burner according to the invention according to a second embodiment of the invention in a longitudinal section.
• the gas turbine 1 shows a sectional view of a gas turbine 1 according to the prior art in a schematically simplified representation.
• the gas turbine 1 has in its interior a rotatably mounted about a rotation axis 2 rotor 3 with a shaft 4, which is also referred to as a turbine runner.
• a turbine runner Along the rotor 3 follow one another an intake housing 6, a compressor 8, a combustion system 9 with a number of combustion chambers 10, each comprising a burner assembly with burners 11, a fuel supply system for the burners (not shown) and a housing 12, a turbine 14 and an exhaust case 15.
• the combustion chamber 10 may be, for example, an annular combustion chamber.
• the gas turbine could also include tube combustion chambers, which are arranged, for example, annularly on the turbine inlet.
• the combustion system 9 communicates with a beispielswei ⁇ ring hot gas channel.
• Each turbine nenlargement is formed of vane rings. Viewed in the flow direction of a working medium follows in the hot runner formed by a number 17 vanes row formed from blades 18 row.
• the guide vanes 17 are secured to an inner housing of a stator 19 while the rotor blades 18 ⁇ a number, for example, by means of a Turbi ⁇ nenrace on the rotor 3 are attached.
• ⁇ is coupled to the rotor 3, a generator, for example (not shown).
• air is sucked in and compressed by the compressor 8 through the intake housing 6.
• the compressor air L "provided at the turbine-side end of the compressor 8 is guided along a burner plenum 7 to the combustion system 9 and conducted there in the region of the burner arrangement into the burners 11 and mixed with fuel therein and / or with fuel in the outlet region of the burner 11 enriched. fuel delivery versor ⁇ gene, the burner in this case with fuel.
• the mixture or the compressor air and fuel are introduced from the burners 11 in the combustion chamber 10 and burned to form a hot working gas stream in a combustion zone within the combustor housing 12 of the combustion chamber. from there, flows of the working gas stream along the hot gas channel to the guide vanes 17 and the blades 18 over.
• the Fig ur 2 shows a fluidic oscillator of a first type according to the prior art in longitudinal section.
• the oscillator 24a comprises an interaction chamber 26 having an input 28 with an input region 30 and an oppositely arranged output region 32 having a first output 34 and a second output 36. For each output, a relatively thin feedback line 38 is arranged, which connects the input region to the output region combines. The side wall portions 40 diverge toward the exit so that the interaction chamber 26 has a triangular longitudinal section.
• the oscillator 24a is not rotationssym ⁇ metric constructed, but has normal to the plane of egg NEN constant longitudinal section.
• FIG. 3 shows a prior art fluidic oscillator 24b of the prior art in longitudinal section.
• the oscillator 24b is also built up not rotationally symmetrical but has normal to the plane of a konstan ⁇ th longitudinal section.
• the input 28 is arranged centrally in the Wech ⁇ selviershunt 26 within a guide means 42, so that an incoming pressurized jet head is directed to the opposite side wall 44th The jet flows alternately left and right at the guide in
• Direction of the output region 32 and acts here ⁇ alternately the outputs 34 and 36 with the fluid, so that the beam alternately exits through the one and the other output from the chamber at a frequency which is determined by the size of the interaction chamber 26.
• Fig. 4 shows schematically a section of a prior art combustion chamber 10 with a burner assembly 48 at a head end of the combustion chamber.
• the combustion chamber comprises a combustion chamber wall with a flame tube 50 comprising a combustion zone and a transition piece 52 which adjoins the flame tube and which extends as far as a turbine inlet of the gas turbine.
• thermoacoustic oscillations resonators 54 are arranged at the level of the flame on the combustion chamber wall.
• Burner assembly 48 includes a central pilot burner 56 having a central pilot lance 58 and a pilot burner premix passage 60.
• the pilot burner 56 includes a conically expanding pilot cone 62.
• Arranged around the central pilot burner are main burners 64.
• the main burners 64 each have a burner axis 66, and a concentrically to the burner axis is arrange ⁇ te Vormischpassage 68, wherein said Vormischpassage 68 by is bounded radially outside of a wall 70 and in the operation of compressor air L "is flowed through and a mixing of fuel and air L" is used, wherein in the Vormischpassa ⁇ ge 68 a central burner lance 72 and a number of fuel Injectors are arranged, which extending from the burner lance toward the wall 70 and fluidly connected to a fuel supply arrangement encompassed by the burner lance 72 and having fuel nozzles.
• the fuel injectors are as swirl blades of a
• Swirl generator 74 is formed, wherein fuel nozzles are arranged on the swirl blades.
• FIG. 5 shows a main burner 64 of the burner arrangement of FIG. 4 schematically in longitudinal section.
• the burner 64 has a central burner axis 66 and a burner passage at least partially surrounding Vormischpassage 68, wherein the Vormischpassage radially outward of a wall 70 be ⁇ limits and during operation of compressor air L "is flowed through and serves a mixing of fuel and air
• a central burner lance 72 and a number of fuel injectors 79 are disposed in the premix passage 68.
• the fuel injectors 79 each include a base body 71 disposed in the premix passage, which is formed as swirl vanes 76 of a swirler 74.
• the fuel injectors 79 include fuel nozzles 80, which open at the surface of the swirl vanes 76 into the premix passage 68.
• the fuel nozzles 80 are fluidly connected to a fuel supply assembly 73 for fuel supply.
• the fuel supply assembly 73 includes a fuel passage 82 and fuel passage extending in the burner lance in the swirl vanes 76 to the respective fuel nozzles 80.
• FIG. 6 schematically shows a burner 84 according to the invention in longitudinal section according to a first exemplary embodiment of the invention.
• the fuel supply arrangement 73 has at least one fluidic oscillator 85 with an interaction chamber 26, wherein an input 28 of the interaction chamber to the fuel passage 82 of the
• Fuel supply assembly 73 is connected.
• the interaction chamber 26 has, opposite the input region 30 with input 28, an output region 32 with two outputs 34 and 36.
• a first exit passage 86 extends from the exit 34 to a first group of fuel nozzles 80a in a first fuel injector 79a.
• a second output channel 88 extends from the output 36 to a two-th group of fuel nozzles 80b in an oppositely disposed Brennstoffinj ector 79b, wherein the fluidic oscillator 85 includes a feedback line for each output channel 38a, 38b, wherein the feedback line 38a, 38b ⁇ with ih rem, one end into the respective output channel 86, 88 downstream of the fuel nozzle 80a, 80b encompassed by the output channel, and with the other end into the input region 30 of the interaction chamber 26.
• the fuel nozzles may, for example, be full-jet nozzles or pressure-swirl nozzles.
• the feedback line 38a connects downstream of the fuel nozzles 80a to the output channel 86 and couples the pressure prevailing at the end of the output channel back to the input region 30 of the interaction chamber.
• the pressure prevailing at the end of the outlet channel is in this case influenced by the pressure in the premix passage immediately in front of the fuel nozzles 80a, so that, at a high pressure in this region, the fuel supply slows down second group fuel nozzles 80b is switched over, as would be the case at a lower pressure.
• the group of fuel nozzles is a longer time inject fuel into the flowing past the compressor air stream prior to the pressure in the Vormischpassage is higher, so that 72 is a gleichmäßi ⁇ Gere on both sides of the burner lance, even with different pressure conditions ⁇ Nissen at from ⁇ passage of the burner Adjust fuel concentration. This counteracts an increase in pressure pulsations and reduces the generation of pollutant emissions.
• FIG. 7 schematically shows a burner 90 according to the invention in accordance with a second exemplary embodiment of the invention.
• the burner 90 has a central burner axis 66, an annular space which runs concentrically with the burner axis 66
• Vormischpassage 92 which is bounded on the outside by a wall 70, and a centrally arranged burner scar 94.
• a diagonal lattice 96 The diagonal grating is arranged, wel ⁇ ches of the air flowing in the Vormischpassage compressor air L "imposes a swirl. Consists of a
• the fludische oscillator is fluidically between the Brennstoffka- nal 82 and at least a first and second group are arranged from internal ⁇ nozzles that are 100 is supplied via a first and a second output channel (not Darge ⁇ represents) of the fluidic oscillator with fuel in the Brennstoffinj ector.
• the Br fuel nozzles of the first group are designated 80a and arranged on the fuel injectors on the hub side. net, wherein the fuel nozzles of the second group are distinguished with 80b be and radially further outside of the Brennstoffinj ek tor inject fuel into the premix passage.
• the exporting ⁇ approximately example allows flow velocities also at different Strö or pressure conditions in the exterior area of the hub-side Vormischpassage or a homogeneous in the radial direction of the fuel concentration to obtain Before mixing passage at the output.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Gas Burners (AREA)
• Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
• Nozzles For Spraying Of Liquid Fuel (AREA)
• Pre-Mixing And Non-Premixing Gas Burner (AREA)

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• 2015
  • 2015-09-07 EP EP15763533.5A patent/EP3134677B1/de not_active Not-in-force
  • 2015-09-07 WO PCT/EP2015/070355 patent/WO2016037966A1/de active Application Filing
  • 2015-09-07 US US15/503,990 patent/US20170254541A1/en not_active Abandoned
  • 2015-09-07 JP JP2017504403A patent/JP6321282B2/ja active Active
  • 2015-09-07 CN CN201580033859.5A patent/CN106662328A/zh active Pending

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