WO1999063276A1 - Injecteur de combustible et procede pour injecter un jet de combustible - Google Patents

Injecteur de combustible et procede pour injecter un jet de combustible Download PDF

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Publication number
WO1999063276A1
WO1999063276A1 PCT/DE1999/001539 DE9901539W WO9963276A1 WO 1999063276 A1 WO1999063276 A1 WO 1999063276A1 DE 9901539 W DE9901539 W DE 9901539W WO 9963276 A1 WO9963276 A1 WO 9963276A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel jet
mouth
jet nozzle
fuel
edge
Prior art date
Application number
PCT/DE1999/001539
Other languages
German (de)
English (en)
Inventor
Heinrich Pütz
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO1999063276A1 publication Critical patent/WO1999063276A1/fr

Links

Classifications

    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/48—Nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement

Definitions

  • the invention relates to a fuel jet nozzle with a mouth for generating a fuel jet emerging from the mouth along a mouth direction from a fuel / air mixture.
  • the invention further relates to a method for emitting a fuel jet.
  • the boundary layer In the case of periodic disturbances, such as those that occur in a sound field, the boundary layer cannot be excited with any frequency to form Rmg vortices, because it also has a natural frequency, depending, for example, on the Mach number and the thickness of the displacement. However, if the boundary layer is periodically excited at this frequency, it rolls up at the same frequency and forms the toroidal ring vortices. These migrate, constantly increasing, downward from the beam. When they hit the plate, they cause density fluctuations in their storage area, some of which propagate as sound waves in the exterior, but some of which also migrate upstream as density waves inside the fuel jet. These inner sound waves again stimulate the free boundary layer at the nozzle to form swirls. This closes a feedback loop. The occurring, usually un- Desired sound emission at discrete frequencies is also referred to as the screech effect for high frequencies.
  • the object of the invention is to provide a fuel jet nozzle which has favorable properties, in particular with regard to low noise emission.
  • Another object of the invention is to provide a method for emitting a fuel jet, in which a feedback between a density fluctuation in the fuel jet and an Rm vortex on the surface of the fuel jet is prevented.
  • the object directed to a fuel jet nozzle is achieved by a fuel jet nozzle with a mouth for generating a fuel jet emerging from the mouth along a direction of mouth with a surface boundary layer, the mouth having a mouth rim on which a storage agent is arranged, through which an or divisible ring vortices that can be generated in or on the surface boundary layer of the fuel jet.
  • the fuel jet can be, for example, a mixture of a combustible energy source, for example 01 or natural gas, and air.
  • the surface boundary layer of the fuel jet is the interface between the fluid and the medium that surrounds the fluid.
  • a mixture of the fluid and the surrounding medium can also be present in the surface boundary layer.
  • the feedback mechanism is interrupted between the ring vortices running down the fuel jet and density fluctuations traveling up the jet. This is achieved by mechanically cutting an ostomy vertebra that forms at the edge of the mouth through the disruptive agent. A vortex migrating downstream is thus already prevented from stable formation. This prevents a sound emission that can be traced back to downward jet vortices. With the fuel jet nozzle so there is no sound emission at discrete frequencies.
  • the disturbance means preferably has a circumferential extent along the mouth edge, an axial extent along the mouth direction and a radial extent perpendicular to the mouth direction, the circumferential extent being small compared to the length of the mouth edge.
  • the disturbance means has only a small circumferential extent makes it particularly well suited to mechanically cut open a vortex.
  • the small circumferential extent ensures that the disturbing agent is not the trigger for the formation of a ring vortex.
  • the interference means is preferably in the form of a pin, in particular cylindrical or rectangular, with a longitudinal axis in the direction of the radial extent.
  • the interference means is preferably in the form of a cutting edge, with a cutting edge in the direction of the mouth direction and a cutting surface with an extension in the direction of the radial extent.
  • At least two, in particular four, disturbance means are preferably arranged at the mouth edge. These disturbance means are more preferably arranged in an aquidistant manner at the mouth edge. By means of several, preferably aquidistantly arranged, disturbance means along the edge of the mouth, it is particularly efficiently possible to mechanically cut open the swirling vertebra at the edge of the mouth and thus to prevent it from being stable.
  • the fuel jet nozzle is preferably designed as a burner, preferably as a hybrid burner for a gas turbine.
  • a fuel jet which consists of an energy carrier / air mixture, emerges from such a burner.
  • a Density fluctuation in such a fuel jet z. B. arise from the fact that the energy / air mixture spontaneously burns locally. This fluctuation in density can cause the fuel jet to travel upstream and result in the above-described feedback effect between downstream vortex currents and fluctuations in density traveling upstream.
  • Spontaneously burning Rm vertebrae are the starting point and cause for a density fluctuation.
  • the fuel jet nozzle is a burner for a gas turbine
  • sound excitation with a comparatively low frequency a so-called hum
  • This hum can have particularly negative consequences on components of the gas turbine due to the vibrations that arise, up to the point of destroying entire components. This hum is eliminated by the disruptive agent.
  • the fuel jet nozzle is more preferably used in a burner for a gas turbine, in particular for a stationary gas turbine.
  • a fuel jet nozzle for a gas turbine dust a comparatively large-volume and intense fuel jet in a combustion chamber or in an air duct. The problem of sound emission at discrete frequencies is particularly great for such a large-volume fuel jet, since particularly intensive sound emissions are produced.
  • the object directed to a method is achieved by a method for emitting a fuel jet, in which the fuel jet emerges from a mouth with a mouth rim of a fuel jet nozzle and subsequently causes a density fluctuation in the fuel jet, which density fluctuation moves the fuel jet upstream and during Reaching the mouth causes the swirl on the surface boundary layer of the fuel jet, whereby the swirl is divided.
  • the swivel is split at the mouth of the mouth.
  • the division is further preferably carried out by a fluid disturbance jet, in particular a compressed air jet.
  • the compressed air jet is preferably directed at the fuel jet in the area of the mouth rim.
  • Such a compressed air jet divides an ostomy vertebra that forms at the edge of the mouth and thus prevents it from building up stably.
  • the division preferably takes place by means of a passive component, preferably by means of a sheet or a pin.
  • FIG. 1 shows a fuel jet emerging from a fuel jet nozzle and hitting a wall
  • FIG. 2 shows a longitudinal section through a fuel jet nozzle with an interference agent
  • FIG. 3 shows a cross section through a fuel jet nozzle with three disrupting means
  • FIG. 4 shows a longitudinal section through a fuel jet nozzle with a cutting-shaped storage medium
  • FIG. 5 shows a cross section through a fuel jet nozzle with four disrupting means
  • FIG. 1 shows a fuel jet nozzle 1. It has a mouth rim 3 which surrounds a mouth 5. An axially symmetrical fuel jet 7 with a surface 7A emerges from the mouth 5 along a mouth direction 8. The fuel jet 7 strikes a wall 9 of a chamber 10, which is oriented not perpendicular to the mouth direction 8.
  • the wall 9 is preferably a combustion chamber wall of a combustion chamber 10 or an air duct wall of an air duct.
  • I is preferably a fuel jet nozzle or a fuel jet nozzle 1 designed as a burner
  • the fuel jet 7 is preferably a fuel jet or a fuel jet 7 made of a fuel-air mixture.
  • a density fluctuation 11 is caused in the fuel jet 7. This density fluctuation 11 travels the fuel jet 7 upstream to the mouth 5. Due to the density fluctuation
  • the feedback coupling mechanism is then stabilized by downwardly running, spontaneously burning belt vortices 13, which each cause an upstream density fluctuation 11 due to their combustion, which in turn is the cause of the formation of a belt vortex 13.
  • Such a mechanism can also result in sound emission without the fuel jet 7 striking a wall.
  • FIG. 2 shows a longitudinal section through a fuel jet nozzle 1.
  • a fuel jet 7 emerges from the mouth 5 of the fuel jet nozzle 1 along a mouth direction 8.
  • the feedback of the vortex 13, density fluctuation 11 and sound emission 15 explained in relation to FIG. 1 is prevented in the fuel jet nozzle 1 by an interference means 19.
  • This storage medium 19 is arranged directly on the mouth edge 3. It has a radial extent RL perpendicular to the mouth direction 8 and an axial extent AL along the mouth direction 8.
  • the disturbance means 19 mechanically cuts the rm vertebra 13, which is at the mouth edge 3
  • FIG. 3 shows a cross section through a fuel jet nozzle 1 with three pin-shaped disrupting means 19, which are arranged along the edge 3 of the mouth in an aquidistant manner, ie at a distance of 120 ° from one another.
  • Each disturbance means 19 has a small circumferential extent UL compared to the length L of the mouth edge 3. This narrow design of the storage means 19 ensures that e on Mouth edge 3 forming R vortex 13 is cut open.
  • the small circumferential extent UL also ensures that not every disruptive means 19 in turn is the starting point for the formation of a swirl
  • FIG. 4 shows a longitudinal section through a fuel jet nozzle 1, in which the disturbance means 19 is designed in the form of a cutting edge.
  • the disturbance means 19 has a cutting edge 20 which is directed along the mouth direction 8.
  • the interference means 19 protrudes far into the mouth 5.
  • the disturbance means 19 also penetrates a piece into a fuel jet 7 em emerging from the fuel jet nozzle 1.
  • FIG. 5 shows a cross section through a fuel jet nozzle 1.
  • Four disturbing means 19 are arranged along the mouth rim 3, which are designed in the shape of a knife as in FIG.
  • the interference means 19 are arranged at a distance of 90 ° from one another and, as in FIG. 4, stuck far into the mouth 5 of the fuel jet nozzle 1 em, with the advantages described above.
  • FIG. 6 shows a longitudinal section through a hybrid burner 22 for a gas turbine, not shown.
  • E pilot burner 24 is surrounded concentrically by a premix burner 26 in the form of a rmgkanal.
  • Several fuel jet nozzles 1 open into the premix burner 26, two of which are visible in longitudinal section.
  • e fuel jet 7 emerges from the fuel jet nozzles perpendicular to the channel direction of the premix burner 26 and strikes an opposite channel wall 9.
  • the pilot burner 24 becomes pilot fuel 30 and Pilot combustion air 32 is supplied, whereby a pilot flame 34 is stabilized in the area of the mouth of the pilot burner 24.
  • Combustion air 36 is conducted in the premix burner 26.
  • the fuel jet 7 em enters the combustion air 36 perpendicular to its direction of flow.
  • each fuel jet nozzle 1 is subject to the feedback mechanism explained above, which leads to undesirable noise emissions under unfavorable conditions.
  • Each fuel jet nozzle 1 is provided with an interference means 19 to prevent this feedback.
  • the hybrid burner 22 itself represents a fuel jet nozzle 1: the fuel-air mixture emerges as a fuel jet 7 from the mouth 5 of the hybrid burner 1.
  • two cutting-shaped interference means 19 are arranged opposite one another on the mouth edge 3 of the mouth 5. This also prevents the formation of a rm vortex by mechanical cutting for the fuel jet 7 emerging from the hybrid burner 22.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne un injecteur de combustible (1) avec une ouverture (5) servant à produire un jet de combustible (7) qui sort de ladite ouverture (5) le long d'une direction d'ouverture (8) et qui présente une couche limite superficielle (7A). L'ouverture (5) comporte un bord (3) présentant une longueur (L), au niveau duquel est placé un élément perturbateur (19) qui permet de diviser le tourbillon annulaire (13) pouvant être produit au niveau de la couche limite superficielle (7A) du jet de combustible (7).
PCT/DE1999/001539 1998-06-04 1999-05-25 Injecteur de combustible et procede pour injecter un jet de combustible WO1999063276A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19825027 1998-06-04
DE19825027.4 1998-06-04

Publications (1)

Publication Number Publication Date
WO1999063276A1 true WO1999063276A1 (fr) 1999-12-09

Family

ID=7869929

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE1999/001539 WO1999063276A1 (fr) 1998-06-04 1999-05-25 Injecteur de combustible et procede pour injecter un jet de combustible

Country Status (1)

Country Link
WO (1) WO1999063276A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1391653A3 (fr) * 2002-08-21 2005-05-04 Rolls-Royce Plc Système d'injection de carburant

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5129266A (en) * 1991-02-28 1992-07-14 Eastern Instrument Laboratories, Inc. Mechanical weigh beam and damping circuit therefor
US5487274A (en) * 1993-05-03 1996-01-30 General Electric Company Screech suppressor for advanced low emissions gas turbine combustor
EP0789193A2 (fr) * 1996-02-07 1997-08-13 DVGW Deutscher Verein des Gas- und Wasserfaches -Technisch-wissenschaftliche Vereinigung- Procédé et dispositif pour supprimer des vibrations par flamme et par pression dans un four
US5676538A (en) * 1993-06-28 1997-10-14 General Electric Company Fuel nozzle for low-NOx combustor burners
US5758587A (en) * 1995-07-20 1998-06-02 Horst Buchner Process and device for suppression of flame and pressure pulsations in a furnace
WO1999006767A1 (fr) * 1997-07-31 1999-02-11 Siemens Aktiengesellschaft Brûleur

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5129266A (en) * 1991-02-28 1992-07-14 Eastern Instrument Laboratories, Inc. Mechanical weigh beam and damping circuit therefor
US5487274A (en) * 1993-05-03 1996-01-30 General Electric Company Screech suppressor for advanced low emissions gas turbine combustor
US5676538A (en) * 1993-06-28 1997-10-14 General Electric Company Fuel nozzle for low-NOx combustor burners
US5758587A (en) * 1995-07-20 1998-06-02 Horst Buchner Process and device for suppression of flame and pressure pulsations in a furnace
EP0789193A2 (fr) * 1996-02-07 1997-08-13 DVGW Deutscher Verein des Gas- und Wasserfaches -Technisch-wissenschaftliche Vereinigung- Procédé et dispositif pour supprimer des vibrations par flamme et par pression dans un four
WO1999006767A1 (fr) * 1997-07-31 1999-02-11 Siemens Aktiengesellschaft Brûleur

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1391653A3 (fr) * 2002-08-21 2005-05-04 Rolls-Royce Plc Système d'injection de carburant

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