EP1084368B1 - Injecteur de combustible - Google Patents

Injecteur de combustible Download PDF

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Publication number
EP1084368B1
EP1084368B1 EP99936291A EP99936291A EP1084368B1 EP 1084368 B1 EP1084368 B1 EP 1084368B1 EP 99936291 A EP99936291 A EP 99936291A EP 99936291 A EP99936291 A EP 99936291A EP 1084368 B1 EP1084368 B1 EP 1084368B1
Authority
EP
European Patent Office
Prior art keywords
fuel injector
fuel
orifice
injector
edge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP99936291A
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German (de)
English (en)
Other versions
EP1084368A1 (fr
EP1084368B2 (fr
Inventor
Carsten Tiemann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
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
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=7869930&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1084368(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP1084368A1 publication Critical patent/EP1084368A1/fr
Application granted granted Critical
Publication of EP1084368B1 publication Critical patent/EP1084368B1/fr
Publication of EP1084368B2 publication Critical patent/EP1084368B2/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • 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
    • 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
    • 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 fuel nozzle for liquid Fuel with an outlet area in which along a Nozzle axis extends an outlet channel.
  • a return injection nozzle is described in DE 32 35 080 A1, with the two opposite liquid supply lines tangential in a circular cylindrical Swirl space.
  • the swirl chamber is on the one hand an injection channel and on the other hand, a return hole connected.
  • the return injector is special for the atomization of liquid fuel in gas turbine combustion chambers suitable. This will atomize achieved that fuel flows tangentially into the swirl chamber and combined into a main stream, whereby by a circular guide in the swirl chamber the main flow a swirl is given that get in the injection channel remains. This fuses the fuel jet as it exits of fuel from the injection channel in a conical shape. on the other hand fuel is returned via the return hole. While maintaining a constant fuel flow to the return injector, the amount of injected Fuel controlled by the amount of recycled Fuel is discontinued.
  • DE-OS 20 33 118 shows a gas burner for a gas-fired Melting furnace.
  • the gas burner has one in the area of the mouth converging nozzle in the form of a gap. This will ensures a high heat concentration.
  • DE 27 39 102 A1 shows a burner with two nozzles for gaseous substances, the nozzle openings being oval Cross section.
  • the mouth edge of a nozzle ends through one bevel does not converge and has a two-fold Symmetry.
  • the object of the invention is to provide a fuel nozzle for liquid fuel through which a combustion vibration is at least diminished.
  • this object is achieved by a fuel nozzle for liquid fuel with a mouth area, in which an orifice channel extends along a nozzle axis, which mouth channel at a mouth edge is not ends converging, the mouth edge not rotationally symmetrical around the nozzle axis.
  • Liquid fuel is in the fuel nozzle through the Mouth area led in the muzzle channel.
  • the mouth channel is non-converging in the mouth area, that means that it does not narrow, so that there is no pressure loss.
  • the liquid fuel emerges from the outlet channel Muzzle edge into the outside space. In doing so, the Beam, i.e. you get a divergent, fanned out Fuel jet. Because the rim of the mouth is not rotationally symmetrical around the nozzle axis is also the divergent Fuel jet not rotationally symmetrical. So you get a distorted fuel cone, which at least in two Spatial directions a different extent perpendicular to Has beam direction. This is distorted accordingly spatial area in which the combustion takes place.
  • This distortion of the combustion area has an influence taken on the occurrence of a combustion vibration.
  • the Area of combustion is shifted and pulled apart so that the acoustic system of burner and burner environment is out of tune.
  • the fuel nozzle and thus the emerging fuel cones are oriented so that a reduction in combustion vibrations down to one complete suppression of combustion vibrations results.
  • the mouth edge is preferably asymmetrical about the nozzle axis. This means that the rim of the mouth is complete Rotation around the nozzle axis must be experienced to with its to take cover again.
  • the edge of the mouth preferably has a two-fold symmetry on.
  • the mouth edge is further preferred Ellipse or a rectangle, especially with rounded corners.
  • the double symmetry means that the mouth edge half a turn, i.e. 180 °, must be experienced to with his to take cover in the original position.
  • the mouth edge preferably corresponds to a contour that is formed by a rectangle and a circle is formed, the circle with its center on the center of gravity of the rectangle lies and protrudes beyond the narrow side of the rectangle, and the outline being the outer edge of the rectangle and the circle encloses.
  • the muzzle edge preferably corresponds to a contour, that by two mutually perpendicular, a common Focus rectangles is formed, the Contour encloses the outer edge of both rectangles.
  • the outlet channel preferably has a channel wall, where each point of the duct wall has an axial distance from the nozzle axis and has an axial position along the nozzle axis, and wherein the center distance for at least two points on the channel wall, which have the same axial position, is different.
  • the changes more preferably Axial distance for points on the channel wall of the same axial Position continuously along a circumferential direction around the nozzle axis
  • the mouth channel is therefore not rotationally symmetrical the nozzle axis. With that, the liquid fuel is already there a bit in the mouth area in a non-rotationally symmetrical Electricity led. So the fuel flow imprinted a non-rotationally symmetrical shape, which at In particular, the fuel escapes from the fuel nozzle efficiently leads to a non-rotationally symmetrical, distorted fuel cone.
  • the mouth channel preferably extends to the mouth edge out.
  • the edge of the mouth preferably has a notch.
  • Such an indentation turns liquid fuel into Leaves from the fuel nozzle more towards the notch distracted than in the other directions of the mouth rim.
  • Such an indentation will in turn achieved that liquid fuel does not move in all directions is distracted equally. It also imagines distorted fuel cone.
  • a fuel nozzle for petroleum is preferred.
  • the fuel nozzle is in a burner for a gas turbine, especially for a stationary gas turbine, used.
  • Figure 1 shows the side view of a fuel nozzle 1.
  • Ein cylindrical nozzle body 3 tapers in a truncated cone Section to an also cylindrical Mouth area 5 with an end face 5A.
  • a nozzle axis 2 directed runs into the fuel nozzle 1 Mouth channel 7, which at the end of the mouth area 5 with a Mouth edge 9 opens.
  • Through the mouth area 5 is a right-angled cut, so that a bevel 10 of the Channel wall 8 of the mouth channel 7 is visible.
  • the mouth edge 9 is not rotationally symmetrical around the nozzle axis 2. This is clear in Figure 2.
  • FIG. 2 shows a top view of the fuel nozzle 1 Figure 1.
  • the mouth edge 9 receives a two-fold Symmetry.
  • the mouth edge 9 thus corresponds to a contour, through the outer edge of a rectangle 11 and one Circle 13 is formed, the circle 13 with its center 15 lies on the center of gravity 17 of the rectangle 11 and protrudes beyond the narrow side of the rectangle 11.
  • the fuel nozzle 1 also has a favorable influence a nitrogen oxide reduction. Because of the distorted fuel cone can be a better fine distribution of liquid Reach fuel. In particular, there is a small one Droplet size for the fuel. Because of the better distribution and the small droplet size of the fuel results there is an equalization of the flame temperatures of the combustion. As a result, maximum temperatures are not as high achieved, which largely determine nitrogen oxide production. Furthermore, there is a better mixing with if necessary water sprayed at the same time. Water becomes Lowering flame temperatures injected into the combustion, which reduces nitrogen oxide formation. Not with one rotationally symmetrical fuel cone 33 (see FIG. 4) there is a better penetration of liquid Fuel and water.
  • FIG. 3 shows a top view of a fuel nozzle 1.
  • the mouth edge 9 represents a contour, which by a rectangle 21 and a perpendicular to it standing rectangle 23 is formed.
  • the two rectangles 21, 23 have a common focus 25, 27.
  • FIG. 4 shows a longitudinal section through the mouth region 5 a fuel nozzle 1 shown.
  • the fuel channel 7 expanded towards the mouth edge 9.
  • Two opposite Points P1, P2 on the channel wall 8 point towards one arbitrarily chosen zero position along an axial position B. the nozzle axis 2.
  • the point P1 is at a distance A1 from Nozzle axis 2.
  • Point P2 is at a distance A2 from the nozzle axis 2.
  • the distance A1 is greater than the distance A2.
  • a circumferential direction U around the nozzle axis 2 that is for Points P on the channel wall 8, which are all the same axial Having position B along the nozzle axis 2 changes the respective distance A to the nozzle axis 2 steadily.
  • a fuel flow in the mouth channel 7 is a non-rotationally symmetrical Embossed shape. This manifests itself on leaving the fuel from the outlet channel 7 in a non-rotationally symmetrical, distorted fuel cone 33. This has the suppression advantages discussed above of combustion vibrations and the reduction of Nitrogen oxide emissions result.
  • Figure 5 shows a plan view of a fuel nozzle 1.
  • Figure 6 shows the fuel nozzle 1 of FIG. 5 in a side view.
  • a semi-cylindrical indentation 31 is milled or sawn, which intersects the mouth of the mouth channel 7.
  • the mouth edge 9 also has a notch 31 this notch 31 becomes liquid fuel particularly wide sprayed on the side.
  • FIG. 7 shows a burner arrangement 40 from a multiplicity of Burners 42 in an annular combustion chamber 44 one not closer shown gas turbine.
  • the annular combustion chamber 44 is rotationally symmetrical about a combustion chamber axis 46
  • the inside of the outer wall 50 and the outside the inner wall 48 are with a fireproof outer lining 52 provided.
  • the mouth edges 9 of the burner 42 are not rotationally symmetrical and oriented irregularly to each other. So that results there is a reduced tendency to form a combustion oscillation, since those emanating from the individual burners 42 Combustion vibrations overlap irregularly and largely wipe it out.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Gas Burners (AREA)
  • Spray-Type Burners (AREA)

Abstract

L'invention concerne un injecteur de combustible (1) comportant une zone d'ouverture (5) dans laquelle s'étend, le long d'un axe d'injecteur (2), un canal d'ouverture (7) qui se termine au niveau d'un bord d'ouverture (9). Cet injecteur est caractérisé en ce que le bord d'ouverture (9) ne présente pas de symétrie de révolution autour de l'axe d'injecteur (2).

Claims (15)

  1. Injecteur (1) de combustible pour du combustible liquide, ayant une région (5) d'embouchure dans laquelle un canal (7) d'embouchure s'étend le long d'un axe (2) d'injecteur, canal (7) qui se termine de façon non convergente sur un bord (9) d'embouchure,
    caractérisé en ce que le bord (9) d'embouchure n'est pas à symétrie de révolution autour de l'axe (2) d'injecteur.
  2. Injecteur (1) de combustible suivant la revendication 1, caractérisé en ce que le bord (9) d'embouchure est asymétrique autour de l'axe (2) d'injecteur.
  3. Injecteur (1) de combustible suivant la revendication 1, caractérisé en ce que le bord (9) d'embouchure présente une symétrie d'ordre 2.
  4. Injecteur (1) de combustible suivant la revendication 3, caractérisé en ce que le bord (9) d'embouchure est une ellipse.
  5. Injecteur (1) de combustible suivant la revendication 3, caractérisé en ce que le bord (9) d'embouchure est un rectangle, notamment à coins arrondis.
  6. Injecteur (1) de combustible suivant la revendication 1 ou 3, caractérisé en ce que le bord (9) d'embouchure correspond à un contour qui est formé par un rectangle (11) et un cercle (13), le centre (15) du cercle (13) coïncidant avec le centre (17) de gravité du rectangle (11) et le cercle (13) s'étendant au-delà du petit côté du rectangle (11), ledit contour faisant le tour du bord extérieur du rectangle (11) et du cercle (13).
  7. Injecteur (1) de combustible suivant la revendication 1 ou 3, caractérisé en ce que le bord (9) d'embouchure correspond à un contour qui est formé par deux rectangles (21, 23) mutuellement perpendiculaires ayant un centre (25, 27) de gravité commun, ledit contour faisant le tour du bord extérieur des deux rectangles (21, 23).
  8. Injecteur (1) de combustible suivant l'une des revendications précédentes, caractérisé en ce que le canal (7) d'embouchure possède une paroi (8) de canal, chaque point (P) de la paroi (8) de canal ayant une distance (A) axiale avec l'axe (2) d'injecteur et une position (B) axiale le long de l'axe (2) d'injecteur, et la distance (A) axiale étant différente pour au moins deux points (P1, P2) de la paroi (8) de canal qui ont la même position (B) axiale.
  9. Injecteur (1) de combustible suivant la revendication 8, caractérisé en ce que la distance (A) axiale pour les points (P) de la paroi (8) de canal de même position (B) axiale se modifie continûment le long d'une direction (U) circonférentielle autour de l'axe (2) d'injecteur.
  10. Injecteur (1) de combustible suivant l'une des revendications précédentes, caractérisé en ce que le canal (7) d'embouchure s'élargit en direction du bord (9) d'embouchure.
  11. Injecteur (1) de combustible suivant l'une des revendications précédentes, caractérisé en ce que le bord (9) d'embouchure comporte une entaille (31).
  12. Injecteur (1) de combustible suivant l'une des revendications précédentes, pour du pétrole.
  13. Injecteur (1) de combustible suivant l'une des revendications précédentes dans un brûleur (42) pour une turbine à gaz, notamment pour une turbine à gaz fixe.
  14. Ensemble (40) de brûleur comportant plusieurs brûleurs (42) qui sont disposés dans une chambre (44) de combustion commune, au moins deux des brûleurs (42) comportant un injecteur (1) de combustible suivant l'une des revendications précédentes.
  15. Ensemble (40) de brûleur suivant la revendication 14, qui est disposé dans une chambre (44) de combustion annulaire pour une turbine à gaz.
EP99936291A 1998-06-04 1999-05-20 Injecteur de combustible Expired - Lifetime EP1084368B2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19825028 1998-06-04
DE19825028 1998-06-04
PCT/DE1999/001514 WO1999063268A1 (fr) 1998-06-04 1999-05-20 Injecteur de combustible

Publications (3)

Publication Number Publication Date
EP1084368A1 EP1084368A1 (fr) 2001-03-21
EP1084368B1 true EP1084368B1 (fr) 2002-08-14
EP1084368B2 EP1084368B2 (fr) 2005-11-02

Family

ID=7869930

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99936291A Expired - Lifetime EP1084368B2 (fr) 1998-06-04 1999-05-20 Injecteur de combustible

Country Status (5)

Country Link
US (1) US6676048B1 (fr)
EP (1) EP1084368B2 (fr)
JP (1) JP2002517700A (fr)
DE (1) DE59902355D1 (fr)
WO (1) WO1999063268A1 (fr)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6805832B2 (en) * 2001-07-09 2004-10-19 Jonathan Mohler Thermite torch cutting nozzle
GB0219461D0 (en) * 2002-08-21 2002-09-25 Rolls Royce Plc Fuel injection arrangement
WO2005095863A1 (fr) * 2004-03-31 2005-10-13 Alstom Technology Ltd Brûleur
US7572997B2 (en) * 2007-02-28 2009-08-11 Caterpillar Inc. EDM process for manufacturing reverse tapered holes
US8146365B2 (en) * 2007-06-14 2012-04-03 Pratt & Whitney Canada Corp. Fuel nozzle providing shaped fuel spray
EP2423589A1 (fr) * 2010-08-27 2012-02-29 Siemens Aktiengesellschaft Agencement de brûleur
DE102012002465A1 (de) * 2012-02-08 2013-08-08 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit unsymmetrischen Kraftstoffdüsen
GB201222304D0 (en) * 2012-12-12 2013-01-23 Rolls Royce Plc A fuel injector and a gas turbine engine combustion chamber
JP6563687B2 (ja) * 2014-06-18 2019-08-21 リンナイ株式会社 コンロバーナ用二重ノズル
US9889420B2 (en) 2014-12-04 2018-02-13 Exxonmobil Research And Engineering Company Fluid injection nozzle for fluid bed reactors
WO2019177947A1 (fr) * 2018-03-12 2019-09-19 Buckner Todd T Système de séchage pour installation de lavage de voiture
US12092332B2 (en) 2021-12-29 2024-09-17 General Electric Company Fuel nozzle and swirler

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US5235813A (en) * 1990-12-24 1993-08-17 United Technologies Corporation Mechanism for controlling the rate of mixing in combusting flows

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Also Published As

Publication number Publication date
WO1999063268A1 (fr) 1999-12-09
DE59902355D1 (de) 2002-09-19
EP1084368A1 (fr) 2001-03-21
EP1084368B2 (fr) 2005-11-02
US6676048B1 (en) 2004-01-13
JP2002517700A (ja) 2002-06-18

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