WO2000034714A1 - Verbrennungsvorrichtung und verfahren zur verbrennung eines brennstoffs - Google Patents
Verbrennungsvorrichtung und verfahren zur verbrennung eines brennstoffs Download PDFInfo
- Publication number
- WO2000034714A1 WO2000034714A1 PCT/EP1999/009401 EP9909401W WO0034714A1 WO 2000034714 A1 WO2000034714 A1 WO 2000034714A1 EP 9909401 W EP9909401 W EP 9909401W WO 0034714 A1 WO0034714 A1 WO 0034714A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- combustion
- fuel
- flow
- combustion device
- area
- Prior art date
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 98
- 239000000446 fuel Substances 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims description 13
- 239000012530 fluid Substances 0.000 claims abstract description 50
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 16
- 239000007789 gas Substances 0.000 claims description 9
- 239000003345 natural gas Substances 0.000 claims description 8
- 230000015572 biosynthetic process Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000007480 spreading Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000006837 decompression Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G10—MUSICAL INSTRUMENTS; ACOUSTICS
- G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
- G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
- G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
- G10K11/161—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general in systems with fluid flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
- F23M20/005—Noise absorbing 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
- F23R3/28—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
- 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 combustion device for V erbrennung a fuel, wherein said fuel as a flow of fluid via a supply passage of the internal feed b is ar.
- the invention also relates to a corresponding method.
- a Laval nozzle is described in section 5.6.2 of the same book.
- the Laval nozzle serves to expand the outflowing fluid beyond the critical pressure ratio and thus to increase the flow speed beyond the speed of sound.
- the fluid is first compressed by a narrowing channel, the flow speed increasing up to the speed of sound.
- An expanding channel section follows, in which the fluid expands and the flow velocity reaches the supersonic area.
- Such a Laval nozzle is used, for example to achieve maximum outflow speeds for thrust gases from rocket engines.
- Different operating states of a Laval nozzle are shown in Figure 5.25. In the operating state shown first, the outlet pressure of the fluid is above the critical pressure.
- the Laval nozzle behaves like a Venturi tube here. For the definition of a Venturi tube, further details follow below.
- Section 5.7 of the same book describes compression flows.
- Section 5.7.1 explains how a subsonic diffuser works.
- Subsonic diffusers are channels widened in the direction of flow, in which a flow in the subsonic area is delayed. The delay causes an increase in pressure.
- Subsonic diffusers can be found, for example, in jet devices, Venturi tubes and in the idlers and outlet housings of turbocompressors.
- Section 5.7.2 describes a supersonic diffuser in which the channel cross-section narrows in the direction of flow.
- the European standard EN ESO 5167-1 concerns flow measurements of fluids with throttling devices.
- Part 1 describes orifices, nozzles and Venturi tubes in fully flow-through lines with a circular cross-section.
- Figure 10 shows a classic Venturi tube. A fluid flows through the Venturi tube along a flow direction.
- the Venturi tube consists of an inlet cone that narrows in the direction of flow and a widening outlet cone that adjoins the inlet cone in the direction of flow. A large pressure loss occurs in the inlet cone. This is through the outlet cone
- this object is achieved by specifying a combustion device for burning fuel with a supply channel for supplying the fuel to a combustion zone, the fuel being able to be passed through the supply channel as a fluid stream with a flow direction and a nominal speed lying within a nominal operating interval, and wherein Supply channel in a decoupling area is so narrowed that sound waves traveling from the combustion zone in the fluid flow against the direction of flow are at least partially reflected at the nominal speed in the decoupling area.
- combustion vibrations can arise in that a pressure pulse is generated in the fluid flow when there is a fluctuation in a power release during combustion. Such a pressure pulse in the fluid flow in turn results in an uneveness in the mass flow of the fluid flow entering the combustion zone. This again leads to a fluctuating release of power during combustion.
- the geometrical designs of the feed channel it can be used to form a positive feedback between pressure pulses in the fluid flow and the fluctuating power release during combustion.
- a combustion oscillation forms.
- Such a combustion vibration can have a disruptive effect, for example, as considerable noise pollution. With large power releases, however, vibrations can also occur in the combustion device, which can ultimately result in damage.
- the invention is based on the knowledge that the propagation of sound waves in the fuel via the feed channel into further, acoustically coupled areas favors the tendency to form such combustion vibrations. This mechanism is prevented by acoustically decoupling the feed channel or also a plurality of feed channels for the fuel. Such acoustic decoupling is achieved by narrowing the feed channel or channels.
- Such a constriction in the direction of flow which was previously only known for air silencers, increases the flow velocity of the fluid.
- the flow rate can be increased so far that sound waves traveling against the flow direction against the constriction are reflected.
- the constriction is designed in such a way that at a nominal velocity of the fluid flow in the supply channel at the constriction there is such a high acceleration of the fluid that a high proportion of the sound waves traveling against the constriction is reflected.
- the nominal speed is e.g. within a speed interval that corresponds to those operating states of the combustion device in which there is a high tendency to form combustion oscillations.
- the decoupling area is preferably designed as a continuous narrowing of the feed channel along the flow direction. Such a continuous constriction results in lower flow and pressure losses due to turbulence compared to a discontinuous constriction.
- a continuous narrowing could e.g. B. something like that be designed, such as the supersonic diffuser described in the above-mentioned book by Willi Bohl.
- the decoupling area is preferably followed by a pressure-increasing area which corresponds to an expansion of the feed channel.
- a pressure increase range increases the pressure in the fluid flow. This is done by expanding the feed channel.
- the passage from the decoupling area and pressure increase area thus corresponds e.g. the Venturi tube or a Laval nozzle shown in the above European standard.
- Such a configuration is particularly advantageous when a high fluid mass flow has to be provided.
- the combination of the decoupling area and the pressure-increasing area thus ensures that a great power release can be achieved in the combustion device with the aid of a large fluid mass flow, with an effective acoustic decoupling of the combustion zone and supply channel being provided at the same time.
- the fuel is preferably natural gas or oil.
- the combustion zone is preferably in a combustion chamber.
- the combustion chamber can have any shape, but a tubular or annular combustion chamber is of particular importance.
- Combustion vibrations can form in a combustion chamber through an interaction of a fluctuation in power during combustion and acoustic modes of the combustion chamber.
- Such combustion chamber vibrations can spread in fluidically coupled rooms, e.g. into the supply lines of fuel or air and possibly penetrate to a supply pump, which can be mechanically heavily loaded.
- An acoustic decoupling by means of the tapering of the feed channel prevents such a spreading of the combustion chamber vibrations.
- the combustion chamber vibrations can spread in fluidically coupled rooms, e.g. into the supply lines of fuel or air and possibly penetrate to a supply pump, which can be mechanically heavily loaded.
- the combustion device is preferably a gas turbine, in particular with an annular combustion chamber.
- a gas turbine With a gas turbine, there is a particularly high release of power during combustion. Combustion vibrations can lead to particularly large noise pollution and damaging vibrations.
- a ring combustion chamber the intrinsic acoustic modes are practically unpredictable due to the complicated geometry, so that the formation of combustion chamber vibrations is particularly difficult to prevent here.
- the acoustic decoupling between the ring combustion chamber and the feed channels of the combustion media is of particular importance here.
- the object is also achieved according to the invention by specifying a method for combusting fuel, the fuel being fed as a fluid stream with a flow direction with a flow direction and a nominal speed lying within a nominal operating interval, and the fluid stream being tapered in a decoupling area in such a way that sound waves traveling against the direction of flow from the combustion zone in the fluid flow are at least partially reflected at the nominal speed in the decoupling area.
- the fluid flow is preferably continuously narrowed in the direction of flow.
- the pressure in the fluid flow is preferably increased by a subsequent expansion of the fluid flow following the constriction.
- Natural gas or oil is more preferably used as fuel.
- Figure 2 shows a gas turbine
- FIG. 1 shows a combustion device 1.
- a fuel duct 5 which is likewise circular in cross section and which represents a supply duct 5 is arranged concentrically.
- Air 6 is guided in the air duct 3 in the form of an air flow 7 with a flow direction 8.
- fuel 14 for example oil
- the air 6 and the fuel 14 are burned in a combustion zone 11 in a flame 13.
- a fluctuation in the power release during combustion causes a sound wave 15 in the fluid flow 9 of the fuel 14. This sound wave 15 travels upstream in the direction of flow 10 in the fluid flow 9.
- the sound wave 15 could penetrate the entire feed channel 5 and travel, for example, to a fuel pump (not shown) and possibly damage it.
- a fuel pump not shown
- considerably extensive spaces were acoustically coupled to the combustion zone 11 by means of the feed channel 5, through which combustion vibrations could spread in the combustion device 1 and which also resonance spaces represent that can favor the formation of combustion vibrations.
- an acoustic decoupling of the feed channel 5 from the combustion zone 11 is achieved by a decoupling area 17.
- the decoupling area 17 is formed by a narrowing of the feed channel 5 along the flow direction 10. The flow velocity of the fluid flow 9 is thus increased in the decoupling area 17.
- the decoupling area 17 is designed such that at a nominal speed of the fluid flow 9 in the supply channel 5, this flow rate in the decoupling area 17 is greatly increased, preferably to a value close to the speed of sound in the fluid flow.
- the sound wave 15 is largely reflected in the decoupling area 17 as a reflection wave 19.
- the remaining part runs as a residual sound wave 21 upstream of the feed channel 5.
- the nominal speed lies in a nominal operating interval, which corresponds to an interval of operating states close to a full load and a full load state.
- the full load of the combustion apparatus 1 ' is the maximum value. for a power release during combustion. In the operating states of the combustion device 1, which correspond to a lower power release than a full load, there is less reflection of the
- a pressure increase area 23 adjoins the decoupling area 17.
- the pressure increasing area 23 corresponds to an expansion of the supply channel 5, in this case to the cross section of the supply channel 5, which also extends in the direction of flow 10 before decompression.
- Coupling area 17 is present.
- the reflection section 24 is a venturi tube.
- the pressure increase area 23 is preferably designed so that there is a maximum pressure increase in the fluid flow 9 at the nominal speed.
- the decoupling area 17 has an entry area 25 and an end area 27.
- the end region 27 is at the same time an inlet region 29 of the pressure increase region 23.
- the pressure increase region 23 ends at an outlet region 31.
- a schematic illustration of the pressure curve in the decoupling region 17 and in the pressure increase region 23 is also included in FIG. Between the inlet area 25 of the decoupling area 17 and the end area 27 of the decoupling area 17 there is a clear pressure loss in the fluid flow 9.
- FIG. 2 schematically shows a combustion device 1 designed as a gas turbine.
- a compressor 45 and a turbine 47 are arranged along an axis 43.
- a combustion chamber 49 which is designed as an annular combustion chamber, is connected between the compressor 45 and the turbine 47.
- a plurality of burners 51 open into the combustion chamber 49; only one burner 51 is shown here for the sake of clarity.
- the burner 51 has an air duct 3 which is connected to the compressor 45 in terms of flow technology.
- the burner 51 also has a supply channel 5 for supplying natural gas '14.
- Combustion media are air 6 from the compressor 45 and natural gas 14 here. These burn in the combustion chamber 49.
- the hot combustion gases 53 thus generated drive the turbine 47.
- the large power release in such a gas turbine 1 can result in combustion vibrations with particularly large amplitudes.
- Such combustion vibrations can occur as combustion chamber vibrations in the combustion chamber 49 form.
- a decoupling area 17 is provided in the feed channel 5. This is followed by a pressure increase region 23 in the direction of flow.
- the effects and advantages of the decoupling area 17 and the pressure increasing area 23 correspond to those explained for FIG. 1.
- the natural gas supply system, not shown in detail, is thus effectively acoustically decoupled from the combustion chamber 49.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid Mechanics (AREA)
- Acoustics & Sound (AREA)
- Multimedia (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
- Feeding And Controlling Fuel (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/857,939 US6615587B1 (en) | 1998-12-08 | 1999-12-01 | Combustion device and method for burning a fuel |
EP99964516A EP1137899B1 (de) | 1998-12-08 | 1999-12-01 | Verbrennungsvorrichtung und verfahren zur verbrennung eines brennstoffs |
DE59907751T DE59907751D1 (de) | 1998-12-08 | 1999-12-01 | Verbrennungsvorrichtung und verfahren zur verbrennung eines brennstoffs |
JP2000587129A JP2002531805A (ja) | 1998-12-08 | 1999-12-01 | 燃焼装置および燃焼方法 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP98123359 | 1998-12-08 | ||
EP98123359.6 | 1998-12-08 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2000034714A1 true WO2000034714A1 (de) | 2000-06-15 |
Family
ID=8233108
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP1999/009401 WO2000034714A1 (de) | 1998-12-08 | 1999-12-01 | Verbrennungsvorrichtung und verfahren zur verbrennung eines brennstoffs |
Country Status (5)
Country | Link |
---|---|
US (1) | US6615587B1 (de) |
EP (1) | EP1137899B1 (de) |
JP (1) | JP2002531805A (de) |
DE (1) | DE59907751D1 (de) |
WO (1) | WO2000034714A1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2001033138A1 (de) * | 1999-10-29 | 2001-05-10 | Siemens Aktiengesellschaft | Brenner |
EP2110602A1 (de) * | 2008-04-16 | 2009-10-21 | Siemens Aktiengesellschaft | Akustiche Teilentkopplung zur Verringerung von selbstinduzierten Flammenschwingungen |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6820431B2 (en) * | 2002-10-31 | 2004-11-23 | General Electric Company | Acoustic impedance-matched fuel nozzle device and tunable fuel injection resonator assembly |
US20100089065A1 (en) * | 2008-10-15 | 2010-04-15 | Tuthill Richard S | Fuel delivery system for a turbine engine |
JP5448762B2 (ja) * | 2009-12-02 | 2014-03-19 | 三菱重工業株式会社 | ガスタービン用燃焼バーナ |
US8322140B2 (en) * | 2010-01-04 | 2012-12-04 | General Electric Company | Fuel system acoustic feature to mitigate combustion dynamics for multi-nozzle dry low NOx combustion system and method |
WO2013172777A1 (en) * | 2012-05-15 | 2013-11-21 | Andritz Technology And Asset Management Gmbh | Cellulose pulp dryer having blow boxes, and a method of drying a web of cellulose pulp |
JP5762481B2 (ja) * | 2013-07-16 | 2015-08-12 | 三菱日立パワーシステムズ株式会社 | 燃料ノズル、これを備えた燃焼器及びガスタービン |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0122526A1 (de) * | 1983-04-13 | 1984-10-24 | BBC Aktiengesellschaft Brown, Boveri & Cie. | Brennstofflanze für die Brennkammer einer Gasturbine |
WO1993010401A1 (de) * | 1991-11-15 | 1993-05-27 | Siemens Aktiengesellschaft | Einrichtung zur unterdrückung von verbrennungsschwingungen in einer brennkammer einer gasturbinenanlage |
EP0572202A1 (de) * | 1992-05-27 | 1993-12-01 | General Electric Company | Verfahren und Vorrichtung zum Verhindern der Konzentrierungschwingungen von Luft-Kraftstoff in einer Brennkammer |
DE4430697C1 (de) * | 1994-08-30 | 1995-09-14 | Freudenberg Carl Fa | Zuluftschalldämpfer |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3958413A (en) * | 1974-09-03 | 1976-05-25 | General Motors Corporation | Combustion method and apparatus |
US4835962A (en) * | 1986-07-11 | 1989-06-06 | Avco Corporation | Fuel atomization apparatus for gas turbine engine |
GB2224315B (en) | 1988-08-10 | 1992-09-02 | Fawcett Christie Hydraulics Li | Hydraulic noise attenuators |
US5319931A (en) * | 1992-12-30 | 1994-06-14 | General Electric Company | Fuel trim method for a multiple chamber gas turbine combustion system |
NL1000492C1 (nl) | 1995-06-02 | 1996-12-03 | Q E International Bv | Geluidsdemper, een hiermee uitgeruste cokesovengasinstallatie, en een schot voor de geluidsdemper. |
-
1999
- 1999-12-01 US US09/857,939 patent/US6615587B1/en not_active Expired - Lifetime
- 1999-12-01 JP JP2000587129A patent/JP2002531805A/ja active Pending
- 1999-12-01 EP EP99964516A patent/EP1137899B1/de not_active Revoked
- 1999-12-01 DE DE59907751T patent/DE59907751D1/de not_active Revoked
- 1999-12-01 WO PCT/EP1999/009401 patent/WO2000034714A1/de not_active Application Discontinuation
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0122526A1 (de) * | 1983-04-13 | 1984-10-24 | BBC Aktiengesellschaft Brown, Boveri & Cie. | Brennstofflanze für die Brennkammer einer Gasturbine |
WO1993010401A1 (de) * | 1991-11-15 | 1993-05-27 | Siemens Aktiengesellschaft | Einrichtung zur unterdrückung von verbrennungsschwingungen in einer brennkammer einer gasturbinenanlage |
EP0572202A1 (de) * | 1992-05-27 | 1993-12-01 | General Electric Company | Verfahren und Vorrichtung zum Verhindern der Konzentrierungschwingungen von Luft-Kraftstoff in einer Brennkammer |
DE4430697C1 (de) * | 1994-08-30 | 1995-09-14 | Freudenberg Carl Fa | Zuluftschalldämpfer |
Non-Patent Citations (1)
Title |
---|
ABBOT A. PUTNAM: "Combustion-Driven Oscillations in Industry", 1971, AMERICAN ELSEVIER, NEW YORK, XP002099925 * |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2001033138A1 (de) * | 1999-10-29 | 2001-05-10 | Siemens Aktiengesellschaft | Brenner |
EP2110602A1 (de) * | 2008-04-16 | 2009-10-21 | Siemens Aktiengesellschaft | Akustiche Teilentkopplung zur Verringerung von selbstinduzierten Flammenschwingungen |
WO2009127507A1 (de) * | 2008-04-16 | 2009-10-22 | Siemens Aktiengesellschaft | Akustische teilentkopplung zur verringerung von selbstinduzierten flammenschwingungen |
Also Published As
Publication number | Publication date |
---|---|
EP1137899A1 (de) | 2001-10-04 |
EP1137899B1 (de) | 2003-11-12 |
JP2002531805A (ja) | 2002-09-24 |
US6615587B1 (en) | 2003-09-09 |
DE59907751D1 (de) | 2003-12-18 |
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