WO2016038016A1 - Brenner für eine gasturbine und gasturbine - Google Patents
Brenner für eine gasturbine und gasturbine Download PDFInfo
- Publication number
- WO2016038016A1 WO2016038016A1 PCT/EP2015/070463 EP2015070463W WO2016038016A1 WO 2016038016 A1 WO2016038016 A1 WO 2016038016A1 EP 2015070463 W EP2015070463 W EP 2015070463W WO 2016038016 A1 WO2016038016 A1 WO 2016038016A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- burner
- fuel
- interaction chamber
- region
- chamber
- Prior art date
Links
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
-
- 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
- F23D11/34—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by ultrasonic means or other kinds of vibrations
- F23D11/345—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by ultrasonic means or other kinds of vibrations with vibrating atomiser surfaces
-
- 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
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- 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
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14482—Burner nozzles incorporating a fluidic oscillator
-
- 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
-
- 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
- F23R2900/03281—Intermittent fuel injection or supply with plunger pump or other means therefor
Definitions
- Burner for a gas turbine and gas turbine The invention relates to a burner for a gas turbine with at least one burner lance and / or Brennernabe and at least one burner lance and / or Brennernabe ⁇ at least partially encloses the burner passage.
- the burner also includes a fuel supply assembly having at least one fuel nozzle and at least one fuel channel.
- the burner serves to introduce fuel into one
- the fuel can be introduced to generate a diffusion flame directly in the output region of the burner in the combustion chamber.
- the fuel is introduced into the combustion chamber adjacent to a stream of air flowing out of a burner passage of the burner or is injected into the air stream.
- the burner may introduce premixed fuel into the combustion chamber by injecting the fuel into a burner passage formed as a premix passage (by means of fuel nozzles opening into the premix passage) and mixing in the premix passage with an airflow passing through the premix passage.
- the fuel / air mixture emerging from the premix passage is burned in the combustion chamber after it has left the burner and allows a combustion that is particularly low in emissions.
- Derar ⁇ term premix flames tend to Verbrennungsinsta ⁇ bilticianen, which is why such burners for stabilization, for example, pilot burner or other fuel passages um ⁇ grasp.
- the burner comprises a fuel supply system.
- the fuel supply system includes a fuel supply assembly having at least one fuel passage via which the fuel nozzles of the burner are supplied with fuel. It can be with the fuel nozzle For example, be a pressure-swirl nozzle. However, it may also be, for example, a burner passage exit.
- the generic burner comprises at least one burner lance and / or one burner hub.
- the burner lance may for example be a central lance ei ⁇ nes pilot burner or cone burner with nozzles for a diffusion operation.
- the burner lance can also be arranged centrally in egg ⁇ ner Vormischpassage or project into this stream of ⁇ on.
- the burner lance may serve the flow guidance or additionally comprise fuel nozzles, which
- the nozzles of the burner lance can be supplied with fuel via at least one fuel channel of the fuel supply arrangement extending in the burner lance.
- At the burner lance may be arranged around the lance around Brennstoffinj ector - for example, in the form of a swirl blades comprehensive swirl generator - be arranged, which also includes in the premix passage Mün ⁇ dende fuel nozzles.
- the fuel supply assembly may extend along the burner lance to the nozzles of the fuel injector.
- the burner hub designates a component which delimits a burner passage radially inward and in which runs at least one fuel passage of the fuel supply arrangement, which supplies fuel to the hub arranged fuel nozzles with fuel and / or feed channels, up to arranged in the Bren ⁇ nerpassage fuel nozzles extend.
- the Brennernabe may be disposed between the burner passage and a radially inwardly disposed fuel supply unit, so that the Brennernabe at least partially surrounds the radially further inwards ⁇ arranged feed unit.
- pressure swirl nozzles are used for this purpose.
- the invention has for its object to provide a burner of the type mentioned and a gas turbine with at least ei ⁇ nem such burner, with which a reduction of pollutant emissions is made possible and additionally ensures improved reliability.
- the object is achieved with a burner of the type a ⁇ initially mentioned that the Brennstoffzu- driving arrangement at least one fluidic oscillator includes a interaction chamber, the interaction ⁇ chamber at least one inlet for entry of fuel and opposite an exit region with at least ei ⁇ NEM output channel has to exit fuel, wherein at least one feedback line opens with its one end in the region of the input into the interaction chamber and with its other end in the output region or in an output channel, the two ends of the remindplungslei ⁇ tion with respect to the interaction chamber with each a flexible membrane are sealed.
- Different types of fluidic oscillators are known which differ in their construction. 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 leaves periodically through different outputs of the interaction chamber in the output region or leaves a central outlet of the interaction chamber in different directions.
- the beam thus defines at least at two opposite ⁇ opposite side wall portions periodically or peels off again, which is caused by deceleration of the flow.
- the periodic application of the jet to the sidewalls / sidewall regions can additionally be stabilized by the pressure of the respective beam
- the beam is fed back to the input area via comparatively thin feedback lines so that the beam receives a pulse pushing away from the sidewall / sidewall area to which it is currently resting.
- the feedback is not mandatory for the oscillation of the beam.
- At least one fluidic oscillator in a To integrate fuel supply arrangement of a burner for a gas turbine, wherein at least one fuel nozzle is connected downstream of the at least one output channel of the fluidic oscillator, so that in operation, the at least one fuel nozzle due to the periodically fueled output channel expels a pulsed fuel jet.
- Downstream is connected to the respective at least one fuel nozzle
- the frequency can be determined by the geometry of the fluidic oscillator, in particular by the size of the chamber, inserted ⁇ represents.
- the fuel nozzle connected to the output port may be formed by the output port itself. Example ⁇ way by the output channel is designed as a full jet nozzle.
- the fluidic oscillator according to the invention is particularly suitable for admission with fuel.
- the two ends of the at least one feedback line are sealed with respect to the interaction chamber, each with a flexible membrane.
- the feedback line serves to stabilize the oscillation and works by feeding back a pressure in the output area to the input area.
- these feedback lines to the interaction chamber are open, so that a part of the fluid flowing through the chamber fills the return ⁇ coupling line and is moved back and forth in this.
- the flexible membranes serve to transfer the pressure without the fuel being able to penetrate into the feedback line.
- the forwarding of the pressure takes over the trapped between the membranes in the feedback line air or a specially filled fluid or gel. As a result, no region is formed in the feedback lines, in which fuel remains for a long time and, in the case of oil, coked as fuel, which would clog up the feedback lines. This increases the operational safety of the burner designed according to the invention.
- the flexible membrane is made of a material resistant to the fuel.
- the membrane may be fixed in the end region of the feedback line in this. But they could be attached to the inside of the interaction chamber also, for example in the area of confluence of the feedback line and thereby cover the mouth of the feedback ⁇ line.
- the membrane could be analogously mounted on the inside of the output channel and thereby cover the A ⁇ mouth of the feedback line.
- the membrane consists of egg ⁇ nem-temperature-resistant stainless steel or a nickel- consists sismaterial.
- This material is flexible, holds the temperatures in the Be ⁇ rich, the fuel lines of gas turbine combustors stand and is corrosion resistant to fuel.
- the feedback line is filled with a fluid or gel for the transmission of a pressure.
- the fluid may be an inert gas which may be in contact with fuel upon failure of the membrane behaves unproblematically.
- the gel can be ⁇ example, be airgel, which is particularly heat resistant. It can also be regarded as advantageous that the Minim ⁇ an output channel of the interaction chamber is formed as maximum of the fuel nozzle in the form of a full jet.
- This embodiment has a simple construction and reduces the manufacturing costs.
- the interaction chamber for exciting the oscillation comprises at least two oppositely arranged side wall regions which diverge diffusely from each other at least in the input region of the interaction chamber in the direction of the exit region.
- the embodiment of the invention relates to a fluidic oscillator which, due to the wall regions diverging at least in the input region in the direction of the output, ignites an incoming beam for oscillating.
- the term is referred to in the context of this application also with side wall.
- the pressurized jet settles at the
- the opening angle of the walls is suitably chosen here. It can be chosen, for example, greater than 7.5 degrees. Suitable opening angles are known from the prior art.
- the chamber may be conical, for example, with the outputs in the base area.
- the side-walls / side wall portions may extend from the entrance area to the opposite output portion, the chamber may have a circular cross section, for example in a curv ⁇ NEN course.
- the only important thing is that the Beam is excited due to the diverging towards the exit side walls in the entrance area to an oscillation, in which he leaves the chamber periodically alternately through different outputs.
- An advantageous embodiment of the invention may provide that the two side wall portions diverge such that at least an angle of 7.5 degrees is formed between an inflow direction and the side wall portion.
- the interaction chamber is substantially rotationally symmetrical and the axis of rotation extends through the entrance and the opposite exit area, with the interaction chamber expanding in a diffuser-like manner at least in the entrance area towards the exit.
- the input is arranged on one side of the chamber and the output region on the opposite side of the interaction chamber.
- Another object of the invention is to provide a combustion chamber with at least one burner and a gas turbine with at least one such combustion chamber, with which in the
- the combustion chamber comprises at least one burner, which is designed according to one of claims 1 to 8, and the gas turbine ⁇ turbine at least one combustion chamber according to claim 14.
- the combustion chamber may be, for example, an annular combustion chamber, at whose head end one or more circumferential rows of burners are arranged. At least one of the burners may be designed according to one of claims 1 to 8.
- the combustion chamber may, for example, also be a crude oxygen silo combustion chamber.
- the combustion chamber may comprise at its head end a burner assembly with circularly arranged main burners. One or more circuits may be arranged on main burners. It can be centrally located in the middle of a pilot burner. Each or only one or one of the burners may be designed according to one of claims 1 to 8.
- the gas turbine may be a turbomachine having a plurality of combustion chambers, for example ring combustion chambers, the combustion chambers being arranged consecutively in the flow direction.
- the gas turbine may also include a circular arrangement of combustion chambers - for example, tube combustion chambers - whose outputs are arranged in the form of a ring segment at a common annular turbine inlet.
- the invention also relates to a fluidic oscillator having an interaction chamber, the interaction chamber passage having at least an input for entry of a fluid and against ⁇ opposite an exit region with at least an off ⁇ for exit of the fluid, wherein the stabilizer ⁇ capitalization a stimulable through the interaction chamber oscillation of the fluid jet at least one feedback line opens with its one end in the region of the input into the interaction chamber and with its other end in the output region or in an output channel.
- Another object of the invention is to provide a fluidic oscillator of the above type, which is particularly suitable for operation with fuel.
- the ends of the feedback line are sealed with respect to the interaction chamber, each with a flexible membrane.
- these feedback lines are open to the interaction chamber so that a portion of the fluid flowing through the chamber fills and is reciprocated in the feedback line.
- the flexible membranes serve to transfer the pressure without the fuel being able to penetrate into the feedback line. According to the invention, the forwarding of the pressure takes over the trapped between the membranes in the feedback line air or a specially filled fluid or gel.
- the fluidic oscillator according to the invention is suitable for integration into a fuel supply arrangement, wherein it increases the operational reliability of the burner.
- the flexible membrane is made of a fuel-resistant material.
- the membrane may be fixed in the end region of the feedback line in this. But they could be attached to the inside of the interaction chamber also, for example in the area of confluence of the feedback line and thereby cover the mouth of the feedback ⁇ line. If the feedback line opens into the output channel, the membrane could be attached analogously to the in ⁇ nenseite of the output channel and thereby cover the junction of the feedback line.
- the membrane consists of a temperature-resistant stainless steel or a nickel base material. It may also be considered advantageous that the feedback line is filled with a fluid or gel to transmit a pressure.
- An advantageous embodiment of the invention can provide that the interaction chamber to kindling of oscillation comprises at least two oppositely disposed sowandberei- che, the manner of a diffuser diverging at least in the entrance region of the changeover ⁇ reaction chamber in the direction of the output range of each other.
- At least one output channel of the fluidic oscillator can be designed as a fuel nozzle in the form of a full-jet nozzle.
- FIG. 2 schematically shows a first type of fluidic oscillator according to the prior art in a longitudinal ⁇ section
- FIG. 5 schematically shows a burner of the combustion chamber shown in Figure 4 in a longitudinal section
- 6 shows schematically a fluidic oscillator according to the invention according to a first embodiment in a longitudinal section
- Figure 7 shows schematically a burner according to the invention according to a second embodiment in a longitudinal ⁇ section .
- FIG. 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 shaft 4 which is also referred to as a turbine runner.
- the rotor 3 successively follow an intake housing 6, a compressor 8, a combustion system 9 with one or more
- Combustion chambers 10 each comprising a burner assembly with burners 11, a fuel supply system for the burner (not shown) and a combustion chamber housing 12, a turbine 14 and an exhaust housing 15.
- the combustion chamber 10 may be, for example, an annular combustion chamber.
- the invention may also relate to gas turbines, which is designed as a turbomachine with a plurality of annular combustion chambers.
- the invention may also relate to gas turbines with one or more tube or Silobrennhuntn.
- the tube combustion chambers can be arranged, for example, annularly on the turbine inlet.
- the combustion system 9 shown in FIG. 1 communicates with an annular hot gas duct, for example. There, several turbine stages connected in series form the
- Turbine 14 Each turbine stage is formed of blade rings gebil ⁇ det. 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 fastened to an inner housing of a stator 19, whereas the moving blades 18 of a row are attached to the rotor 3, for example by means of a turbine disk.
- a generator (not shown) is coupled to the rotor 3.
- the working gas stream flows past along the hot gas channel to the guide vanes 17 and the rotor blades 18th at the rotor blades 18, the working gas flow relaxed pulse-transmitting, so that the blades 18 of the rotor 3 antrei ⁇ ben and that the coupled to it generator (not shown).
- FIG. 2 shows a fluidic oscillator of a first type according to the prior art in a longitudinal section.
- the oscillator 24a includes an interaction chamber 26 having just one input 28 with an input region 30 and an oppositely-disposed output region 32 having a first output channel 34 and a second output channel 36.
- a relatively thin feedback line 38 is arranged connecting the input region to the output region , wherein the feedback line opens in the dargestell ⁇ th example with one end in the output channel.
- the sidewall regions 40 diverge in the direction of Cinbe ⁇ rich 32, so that the interaction chamber 26 has a triangular longitudinal section.
- the oscillator 24a is not constructed rotationally symmetrical, but has normal to the plane of a constant longitudinal section.
- FIG. 3 schematically shows a burner 90 according to the prior art in a longitudinal section.
- the burner 90 includes a central burner axis 66 and at least from ⁇ cut, the burner axis 66 surrounding the burner passage 100.
- the burner passage 100 is passage 92 formed as an annular chamber shaped premix and delimited radially outwardly by a wall 70 with a centrally disposed burner scar 94, the Burner passage 100 bounded radially inward.
- a diagonal grid 96 is arranged, wel ⁇ ches of the air flowing in the Vormischpassage compressor air L "imposes a swirl.
- the diagonal grid consists of a number around the hub circumferentially arranged Brennstoffinj ectodermal ren 98, which is arranged in the Vormischpassage base body of passing compressor air L "a. in the circumferential passage tung oriented speed component aufgar ⁇ gene in the Brennernabe 94 a Brennstoffzuchtan- does not proceed order 73 (the fuel nozzle 80, the fuel channel 82 (which may be formed circumferentially in the cone of the Brennernabe) and supply pipes shown), wherein the supply lines branch off from the fuel channel 82 and extend to the fuel nozzles 80 to supply the fuel nozzles.
- FIG. 4 schematically shows a section of a prior art combustion chamber 10 with a burner assembly 48 at a head end of the combustion chamber.
- the combustor includes a combustor wall having a combustion zone include ⁇ the flame tube 50 and a flame tube adjoining the transition piece 52, which extends to a turbine inlet of the gas turbine.
- thermoacoustic oscillations resonators 54 are arranged on the combustion chamber wall at the level of the flame.
- the burner assembly 48 includes a central pilot burner 56 having a central burner lance 58 and a burner passage 60 formed as a pilot burner premix passage. Of the Pilot burner 56 comprises a conically widening pilot cone 62 in the flow direction.
- Main burner 64 is arranged around the central pilot burner in a circular manner.
- the main burners 64 each have a burner axis 66, and a KOA xial to the burner axis burners arranged passage 68, which is bounded radially outwards by a wall 70 at the burner passage 68 ⁇ and operation of compressor air L "
- a mixing of fuel and air L "is used wherein in the burner passage 68 a central burner lance 72 and a number Brennstoffinj ectors angeord ⁇ net, which extend from the burner lance in the direction of the wall 70 and fluidly with an at least teilwei ⁇
- the fuel injectors are connected as fuel supply assemblies (not shown) extending in the burner lance 72 and having fuel nozzles
- Swirl blades of a swirl generator 74 are 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 coaxial with Bren ⁇ nerachse 66 arranged burner passage 68, wherein the torch ⁇ passage is bounded radially outwardly by a wall 70 and in the operation of compressor air L "is flowed through and a mixing of fuel and air is used.
- a central burner lance 72 and a number of reflectors Brennstoffinj 79 is disposed.
- the Brennstoffinj reflectors 79 each comprise a Vormischpassage arranged in the base body 71, which swirl vanes 76 as a
- Swirl generator 74 is formed. Fuel injectors
- the nozzles 80 are for supplying fuel
- FIG. 6 schematically shows a fluidic oscillator 25 according to the invention in a longitudinal section according to a first exemplary embodiment.
- the fluidic oscillator 25 comprises an interaction chamber 26 which is rotationally symmetrical about a rotation axis 31.
- the input 28 to input portion 30 is disposed at one end of the chamber and opposite to the output region 32 with two From ⁇ -channels 34 and 36.
- the sidewall portions 27 extend from the input to the output portion, diverge at least in the entrance area 30 towards the exit.
- Each output channel is provided with a feedback line 38a, 38b which opens into the interaction chamber with its one end in the region of the input 28 and with its other end into the output region 32, wherein the two ends of the feedback line 38 each have one opposite the interaction chamber flexible membrane 37 are sealed.
- An entering in the inflow direction 29 under pressure into the interaction chamber 26 fuel jet lies down preferably to the side walls 27 on, whereby an oscillation of the beam is fanned due to the diverging in a ⁇ transition area 30 side wall portions 27, so that the beam PE riodisch at different side wall portions applies and the two output channels 34 and 36 periodically acted upon with fuel ⁇ material.
- the feedback lines are sealed at their ends to the flexible membranes 37, which transmit pressure to a respective fluid 35 or gel trapped in the feedback line, which may be, for example, air or an inert gas. If the output channel 34 applied in the course of the oscillation with fuel, the rich ⁇ arranged in toastbe membrane 37 presses the feedback channel 38a as shown in the line 38a into it, so that the diaphragm 37 at the other end of the feedback line 38a in the input area 30 is pushed out. The two are opposite ⁇ de feedback line 38b sealing membranes 37 are essentially non-loaded at this time with pressure.
- the fluidic oscillator 25 is suitable to be traversed by fuel and fuel the fuel jet ⁇ to the oscillation, with a security risk by standing fuel in the feedback ⁇ lines is reliably avoided.
- FIG. 7 schematically shows a burner 84 according to the invention in longitudinal section according to a second exemplary embodiment of the invention.
- the fuel supply arrangement 73 has at least one fluidic oscillator 85 with an interaction chamber 26, an input 28 of the interaction chamber communicating with the fuel channel 82 of FIG.
- Fuel supply assembly 73 is connected.
- the interaction chamber 26 has, opposite the input region 30, an output region 32 with two output channels 34 and
- a first output channel 34 extends up to ei ⁇ ner first group of fuel nozzles 80a in a first Brennstoffinj ector 79a.
- a second output channel 36 extends to a second group of fuel nozzles 80b in an oppositely disposed Brennstoffinj ector 79b, wherein the fluidic oscillator for each output channel comprises 85 is a rear Kopp ⁇ lung line 38a, 38b, wherein the feedback line 38a, 38b each in its one end Outlet channel 34, 36 downstream of the fuel nozzles 80a, 80b encompassed by the output channel and opens at the other end in the input region 30 of the interaction chamber 26th
- the feedback lines 38a, 38b couple the pressure prevailing at the end of the outlet channel back to the input region 30 of the interaction chamber.
- the diaphragms 37 seal the feedback lines against the fuel, with a pressure on the diaphragms from one end to the other. Re end of the feedback line is transmitted via a trapped in the feedback line fluid or gel.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Feeding And Controlling Fuel (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE112015001975.8T DE112015001975A5 (de) | 2014-09-12 | 2015-09-08 | Brenner für eine Gasturbine und Gasturbine |
US15/500,438 US20170219210A1 (en) | 2014-09-12 | 2015-09-08 | Burner for a gas turbine, and a gas turbine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102014218285.9 | 2014-09-12 | ||
DE102014218285 | 2014-09-12 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2016038016A1 true WO2016038016A1 (de) | 2016-03-17 |
Family
ID=54140426
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2015/070463 WO2016038016A1 (de) | 2014-09-12 | 2015-09-08 | Brenner für eine gasturbine und gasturbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US20170219210A1 (de) |
DE (1) | DE112015001975A5 (de) |
WO (1) | WO2016038016A1 (de) |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3748852A (en) * | 1969-12-05 | 1973-07-31 | L Cole | Self-stabilizing pressure compensated injector |
EP0672862A2 (de) * | 1994-03-14 | 1995-09-20 | The Boc Group, Inc. | Verfahren und Vorrichtung für pulsierende Verbrennung |
EP2423589A1 (de) * | 2010-08-27 | 2012-02-29 | Siemens Aktiengesellschaft | Brenneranordnung |
-
2015
- 2015-09-08 DE DE112015001975.8T patent/DE112015001975A5/de not_active Withdrawn
- 2015-09-08 WO PCT/EP2015/070463 patent/WO2016038016A1/de active Application Filing
- 2015-09-08 US US15/500,438 patent/US20170219210A1/en not_active Abandoned
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3748852A (en) * | 1969-12-05 | 1973-07-31 | L Cole | Self-stabilizing pressure compensated injector |
EP0672862A2 (de) * | 1994-03-14 | 1995-09-20 | The Boc Group, Inc. | Verfahren und Vorrichtung für pulsierende Verbrennung |
EP2423589A1 (de) * | 2010-08-27 | 2012-02-29 | Siemens Aktiengesellschaft | Brenneranordnung |
Also Published As
Publication number | Publication date |
---|---|
US20170219210A1 (en) | 2017-08-03 |
DE112015001975A5 (de) | 2017-02-09 |
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