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EP2423597A2 - Premix burner for a gas turbine - Google Patents

Premix burner for a gas turbine Download PDF

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Publication number
EP2423597A2
EP2423597A2 EP11178196A EP11178196A EP2423597A2 EP 2423597 A2 EP2423597 A2 EP 2423597A2 EP 11178196 A EP11178196 A EP 11178196A EP 11178196 A EP11178196 A EP 11178196A EP 2423597 A2 EP2423597 A2 EP 2423597A2
Authority
EP
European Patent Office
Prior art keywords
premix burner
injection
diameter
injection openings
premix
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.)
Granted
Application number
EP11178196A
Other languages
German (de)
French (fr)
Other versions
EP2423597B1 (en
EP2423597A3 (en
Inventor
Frank Grimm
Fulvio Magni
Weiqun Geng
Douglas Anthony Pennell
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Alstom Technology AG
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Publication date
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Classifications

    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air 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
    • 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
    • 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
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D91/00—Burners specially adapted for specific applications, not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • 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
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49716—Converting

Definitions

  • the present invention relates to the field of gas turbines. It relates to a premix burner for a gas turbine according to the preamble of claim 1 and a method for reworking such premix burners.
  • the present invention is based on a premix burner for a gas turbine in the form of a so-called "double-cone burner", as it is known for example from document EP 0 851 172 A2 is known.
  • the first figure of this application is here as Fig. 1 played.
  • the premix burner 10 according to Fig. 1 consists of two extending along one axis (29 in Fig. 2 ) extending hollow Operakegelschalen 11, 12, which are nested one behind the other.
  • the displacement of the respective center axis or longitudinal axis of symmetry of the partial cone shells 11, 12 generates on both sides, in mirror image arrangement, in each case a tangential air inlet channel 18, 19, through which combustion air 20 flows into the conical interior 30 of the burner.
  • the two partial cone shells 11, 12 each have an initial part in the form of a cylinder 14, 15.
  • a nozzle 24 for atomizing a preferably liquid fuel 23 is housed, which forms a flame front 28 after ignition together with the injected combustion air 20.
  • the partial cone shells 11, 12 further each have a fuel line 16, 17 which are arranged along the tangential air inlet channels 18, 19 and provided with injection openings 21 in the form of linear rows of holes through which a gaseous fuel 22 injected into the combustion air flowing past 20 there becomes, as is symbolized by arrows.
  • These fuel lines 16, 17 are preferably at the latest at the end of the tangential inflow, before entering the interior 30, placed in order to ensure an optimal air / fuel mixture.
  • the premix burner 10 has a front plate 13 serving as an anchoring for the partial cone shells 11, 12 with a number of bores 26, through which cooling air 27 can be supplied to the front part of the combustion chamber 25 as required.
  • the design and arrangement of the injection openings 21 for the gaseous fuel 22 has a considerable influence on the mixing of the fuel with the combustion air 20.
  • the fuel 22 is injected into the air inlet channel 18, 19 of the premix burner 10 perpendicular to the air flow.
  • the mixture of the fuel 22 with the air is from both the place of Injection 21 and influenced by the flow rate of the gaseous fuel.
  • injection openings 21 are used, which in Fig. 2 are shown as a row of holes R1, wherein each of the two air inlet ducts 18, 19 each associated with such a row of holes.
  • R1 when natural gas is used as the gaseous fuel, 32 injection ports 21 having a small discharge diameter are arranged.
  • the object is solved by the entirety of the features of claim 1.
  • the inventive solution is that the injection openings are enlarged in diameter.
  • this magnification must be limited to an optimal range.
  • it has been shown that it is not the absolute size of the diameters to achieve good results that is decisive, but in each case a diameter ratio of the diameter of the injection opening 21 to the effective discharge diameter of the premix burner 10.
  • the effective exit diameter of the premix burner is to be understood as the diameter of a circle which forms the same area as the outlet opening of the premix burner.
  • a typical conventional hole diameter of a high methane natural gas burner resulted in the use of the newly introduced ratio of diameter of the injection port 21 to effective exit diameter of the premix burner 10 to a diameter ratio of 0.0086.
  • a diameter ratio of diameter of the injection port 21 to effective exit diameter of the premix burner 10 of 0.0097 was used.
  • a range of diameter ratios of diameter of the injection port to effective exit diameter of the premix burner which is between 0.011 and 0.015, has now been determined.
  • an extended range of diameter ratios of diameter of the injection port to effective exit diameter of the premix burner is proposed to be greater than 0.015 and less than 0.017 , Overall, this results in an advantageous range of diameter ratios from 0.011 to 0.017.
  • the distance between the injection openings or the total number of injection openings decreases.
  • the injection ports have been kept as small as possible to allow for good mixing.
  • a minimum size was required in order to keep the pressure losses, which occur during the injection of the fuel, small.
  • Another aspect of the disclosure is to specify a height of the air inlet ducts into which the fuel gas 2 is introduced into the premix burner in a region adapted to the injection opening, which leads to a good mixing with low pressure loss and stable combustion.
  • a ratio of the diameter of the injection opening to the height of the air inlet channel which is between 0.097 and 0.153, is advantageous in each case.
  • a ratio of the sum of the areas of the injection openings to the effective exit diameter of the premix burner in an advantageous range is to be selected. This range is between 0.0051 and 0.0097 for the proposed hole diameter ranges.
  • all injection openings of a row of holes have the same diameter and are equidistant.
  • Another embodiment of the invention is characterized in that the distance between adjacent injection openings of a row of holes is approximately 16 mm.
  • an advantageous range of the ratio of diameter of the injection opening to the height of the air inlet channels can be further specified, which is between 0.109 and 0.124.
  • two particularly advantageous partial regions of the ratio of the diameter of the injection opening to the height of the air inlet channels have been determined. These are the ranges from 0.109 to 0.112 and 0.119 to 0.124.
  • Another embodiment of the invention is characterized in that the premix burner is provided for operation with natural gas as gaseous fuel, and that the ratio of hole diameter of the injection ports to the effective exit diameter of the premix burner is 0.012 each.
  • Another embodiment of the invention is characterized in that the premix burner is designed for operation with a gaseous fuel having a calorific value which is at least 20% below the calorific value of methane, and that the injection openings each have a diameter ratio of diameter of the injection port to have effective premix burner exit diameter of 0.0137.
  • an advantageous range of the ratio of diameter of the injection port to the height of the air inlet ports can be further specified, which is between 0.123 and 0.140.
  • two particularly advantageous subregions of the ratio of the diameter of the injection opening to the height of the air inlet channels are indicated. These are the ranges from 0.123 to 0.128 and 0.134 to 0.140.
  • the fuel gas velocity in the injection openings must be high enough to achieve a good mixing, on the other hand, this should be deep to keep the pressure losses in the fuel gas system low and thus, depending on the pressure level of the gas supply system, necessary compression of the fuel gas before the introduction avoid or minimize it.
  • the fuel gas velocity in the injection openings is proportional to the amount of gas and inversely proportional to the sum of the areas of the injection openings of a burner.
  • the amount of fuel gas introduced into a burner is also proportional to the burner size.
  • a ratio of between 0.005 and 0.008 was found to be the favorable ratio of the sum of the areas of the injection ports to the effective exit area of the premix burner.
  • a ratio of between the sum of the areas of the injection ports and the effective exit area of the premix burner has been determined to be between 0.007 and 0.010 lies.
  • two parallel rows of holes with a double hole spacing between the injection openings are provided per air inlet channel, the holes are arranged offset from one another. Due to the different injection positions, the combustion stability can be positively influenced.
  • one row of holes with injection openings is provided per air inlet channel.
  • a method for reworking such Vormischbrenner subject of the invention is to rework a conventional premix burner with small injection openings with minimal effort in such a way that a novel premix burner with larger injection openings is obtained.
  • it is proposed to close every second hole of a row of holes of injection openings and to increase the diameter of the remaining injection opening.
  • To close the holes for example, welded or soldered.
  • a small closure can also be used.
  • An embodiment of the invention is characterized in that the ejection opening closest to the outlet of the premix burner to the combustion chamber is closed. Starting from there, a hole is drilled out alternately and a hole is closed.
  • An embodiment of the invention is characterized in that the injection opening closest to the outlet of the premix burner is bored to the combustion chamber. Starting from there, a hole is closed alternately and a hole drilled out.
  • the diameter of the remaining injection opening is increased so that its exit area doubles.
  • a premix burner 10 is shown in the double cone type, as used in large gas turbines. Visible is the cone character of the premix burner 10, which towards the combustion chamber (in Fig. 2 right) is limited by a front panel 13. Visible is also an air inlet channel 18, on the outside of which a fuel line 16 for the gaseous fuel is arranged transversely.
  • the gaseous fuel is injected into the air inlet channel 18 through injection openings 21, which form the illustrated row of holes R1 in shape and arrangement.
  • injection openings 21 which form the illustrated row of holes R1 in shape and arrangement.
  • the row of holes R1 has a distance a1 of 15 mm.
  • the row of holes R1 is replaced by the row of holes R2 or R3, in which only 16 injection openings 21 are provided with an enlarged diameter ratio of 0.011 and a distance d of 16 mm.
  • the sum of all flow cross sections of the injection openings with respect to the row of holes R1 remains the same, but the fewer individual beams are stronger and thus reach deeper into the flow of combustion air and lead to a significant improvement in the mixing.
  • the distance of the row of holes to the front plate 13 can remain unchanged with respect to the row of holes R1 (row of holes R2, distance a1); However, it is also conceivable to increase this distance from 15 mm to 23 mm (hole row R3, distance a2), which shifts the range of stable combustion to lower temperatures.
  • the diameter ratio of 0.012 for the injection ports 21 of the rows of holes R2 and R3 is provided for the use of natural gas. If, instead of natural gas, a gaseous fuel having a calorific value less than 80% of the calorific value of methane is injected, the injection openings 21 preferably all have a diameter ratio of 0.014.
  • two parallel rows of holes with staggered injection openings are provided, so that the two rows of holes are positioned "in gap" relative to each other.
  • the distance between the holes of a row of holes is doubled to 2 x d.
  • Essential for the improved mixing, combustion and pollutant emission is the distribution of the mass flow of the gaseous fuel to significantly less injection openings with a larger diameter. Contrary to the expectation that a large number of small injection holes with a correspondingly high pressure loss during injection would lead to improved mixing for better mixing, the emissions can be reduced due to the higher penetration depth with larger holes. It goes without saying that the diameters and distances of the injection openings 21 in a row of holes in the context of the invention may have certain variations in order to be able to compensate for irregularities in the combustion air flow.

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

Abstract

The premix burner (10) has a series of linear holes running transverse to a flow direction of combustion air (20). The linear holes are arranged at outer walls of air inlet channels (18, 19) by injection openings (21). Gaseous fuel (22) is injected into the combustion air that flows transverse to the flow direction via the injection openings. The openings exhibit ratio of diameter of the injection openings to effective outlet diameter of the burner, where the ratio ranges between 0.011 and 0.015. Distance between the openings is of about 16 mm. An independent claim is also included for a method for refinishing a premix burner for a gas turbine.

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die vorliegende Erfindung bezieht sich auf das Gebiet der Technik von Gasturbinen. Sie betrifft einen Vormischbrenner für eine Gasturbine gemäss dem Oberbegriff des Anspruchs 1 sowie ein Verfahren zum Nacharbeiten von derartigen Vormischbrennern.The present invention relates to the field of gas turbines. It relates to a premix burner for a gas turbine according to the preamble of claim 1 and a method for reworking such premix burners.

STAND DER TECHNIKSTATE OF THE ART

Die vorliegende Erfindung geht aus von einem Vormischbrenner für eine Gasturbine in Form eines so genannten "Doppelkegelbrenners", wie er beispielsweise aus der Druckschrift EP 0 851 172 A2 bekannt ist. Die erste Figur dieser Anmeldung ist hier als Fig. 1 wiedergegeben.The present invention is based on a premix burner for a gas turbine in the form of a so-called "double-cone burner", as it is known for example from document EP 0 851 172 A2 is known. The first figure of this application is here as Fig. 1 played.

Der Vormischbrenner 10 gemäss Fig. 1 besteht aus zwei sich entlang einer Achse (29 in Fig. 2) erstreckenden hohlen Teilkegelschalen 11, 12, die versetzt zueinander ineinandergeschachtelt sind. Die Versetzung der jeweiligen Mittelachse oder Längssymmetrieachse der Teilkegelschalen 11, 12 zueinander erzeugt auf beiden Seiten, in spiegelbildlicher Anordnung, jeweils einen tangentialen Lufteintrittskanal 18, 19, durch welchen Verbrennungsluft 20 in den kegelförmigen Innenraum 30 des Brenners strömt. Die beiden Teilkegelschalen 11, 12 weisen je einen Anfangsteil in Form eines Zylinders 14, 15 auf. Im Bereich der Zylinder 14, 15 ist eine Düse 24 zur Zerstäubung eines vorzugsweise flüssigen Brennstoffes 23 untergebracht, der nach der Zündung zusammen mit der eingedüsten Verbrennungsluft 20 eine Flammenfront 28 ausbildet.The premix burner 10 according to Fig. 1 consists of two extending along one axis (29 in Fig. 2 ) extending hollow Teilkegelschalen 11, 12, which are nested one behind the other. The displacement of the respective center axis or longitudinal axis of symmetry of the partial cone shells 11, 12 generates on both sides, in mirror image arrangement, in each case a tangential air inlet channel 18, 19, through which combustion air 20 flows into the conical interior 30 of the burner. The two partial cone shells 11, 12 each have an initial part in the form of a cylinder 14, 15. In the region of the cylinders 14, 15, a nozzle 24 for atomizing a preferably liquid fuel 23 is housed, which forms a flame front 28 after ignition together with the injected combustion air 20.

Selbstverständlich kann der Vormischbrenner 10 rein kegelig, also ohne die Zylinder 14, 15, ausgebildet sein. Die Teilkegelschalen 11, 12 weisen des weiteren je eine Brennstoffleitung 16, 17 auf, welche entlang der tangentialen Lufteintrittskanäle 18, 19 angeordnet und mit Eindüsungsöffnungen 21 in Form von linearen Lochreihen versehen sind, durch welche ein gasförmiger Brennstoff 22 in die dort vorbeiströmende Verbrennungsluft 20 eingedüst wird, wie dies durch Pfeile versinnbildlicht wird. Diese Brennstoffleitungen 16, 17 sind vorzugsweise spätestens am Ende der tangentialen Einströmung, vor Eintritt in den Innenraum 30, platziert, um eine optimale Luft/Brennstoff-Mischung zu gewährleisten.Of course, the premix burner 10 purely conical, so without the cylinder 14, 15, be formed. The partial cone shells 11, 12 further each have a fuel line 16, 17 which are arranged along the tangential air inlet channels 18, 19 and provided with injection openings 21 in the form of linear rows of holes through which a gaseous fuel 22 injected into the combustion air flowing past 20 there becomes, as is symbolized by arrows. These fuel lines 16, 17 are preferably at the latest at the end of the tangential inflow, before entering the interior 30, placed in order to ensure an optimal air / fuel mixture.

Zum Brennraum 25 weist der Vormischbrenner 10 eine als Verankerung für die Teilkegelschalen 11, 12 dienende Frontplatte 13 mit einer Anzahl Bohrungen 26 auf, durch welche bei Bedarf Kühlluft 27 dem vorderen Teil des Brennraumes 25 zugeführt werden kann.For the combustion chamber 25, the premix burner 10 has a front plate 13 serving as an anchoring for the partial cone shells 11, 12 with a number of bores 26, through which cooling air 27 can be supplied to the front part of the combustion chamber 25 as required.

Die Ausgestaltung und Anordnung der Eindüsungsöffnungen 21 für den gasförmigen Brennstoff 22 hat erheblichen Einfluss auf die Vermischung des Brennstoffs mit der Verbrennungsluft 20. Der Brennstoff 22 wird in den Lufteintrittskanal 18, 19 des Vormischbrenners 10 senkrecht zum Luftstrom eingedüst. Die Mischung des Brennstoffs 22 mit der Luft wird sowohl vom Ort der Eindüsungsöffnungen 21 als auch von der Strömungsgeschwindigkeit des gasförmigen Brennstoffs beeinflusst.The design and arrangement of the injection openings 21 for the gaseous fuel 22 has a considerable influence on the mixing of the fuel with the combustion air 20. The fuel 22 is injected into the air inlet channel 18, 19 of the premix burner 10 perpendicular to the air flow. The mixture of the fuel 22 with the air is from both the place of Injection 21 and influenced by the flow rate of the gaseous fuel.

Bei den bisher im Einsatz befindlichen Vormischbrennern der beschriebenen Art werden Eindüsungsöffnungen 21 eingesetzt, die in Fig. 2 als Lochreihe R1 dargestellt sind, wobei jedem der beiden Lufteintrittskanäle 18, 19 jeweils eine solche Lochreihe zugeordnet ist. In der Lochreihe R1 sind, wenn als gasförmiger Brennstoff Erdgas verwendet wird, 32 Eindüsungsöffnungen 21 mit kleinem Austrittsdurchmesser angeordnet.In the previously used in the premix burners of the type described injection openings 21 are used, which in Fig. 2 are shown as a row of holes R1, wherein each of the two air inlet ducts 18, 19 each associated with such a row of holes. In the row of holes R1, when natural gas is used as the gaseous fuel, 32 injection ports 21 having a small discharge diameter are arranged.

Es hat sie nun herausgestellt, dass beim Betrieb derartiger Vormischbrenner die Durchmischung der Verbrennungsluft und des gasförmigen Brennstoffs noch verbessert werden kann, um die Spitzenwerte der Flammentemperatur im Brenner zu senken und damit die Schadstoffemissionen (z.B. NOx) zu verringern.It has now been found that, in the operation of such premix burners, the mixing of the combustion air and the gaseous fuel can still be improved in order to reduce the peak values of the flame temperature in the burner and thus to reduce the pollutant emissions (for example NOx).

DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION

Es ist daher Aufgabe der Erfindung, einen Vormischbrenner der eingangs genannten Art zu schaffen, der hinsichtlich der Vermischung von Verbrennungsluft und gasförmigem Brennstoff deutlich verbessert ist.It is therefore an object of the invention to provide a premix burner of the type mentioned, which is significantly improved in terms of the mixing of combustion air and gaseous fuel.

Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Wichtig für die erfindungsgemässe Lösung ist, dass die Eindüsungsöffnungen in ihrem Durchmesser vergrössert werden. Diese Vergrösserung muss aber auf einen optimalen Bereich beschränkt werden. Ferner wurde gezeigt, das nicht die absolute Grösse der Durchmesser zur Erzielung guter Ergebnisse entscheidend ist, sondern jeweils ein Durchmesserverhältnis von Durchmesser der Eindüsungsöffnung 21 zu effektivem Austrittsdurchmesser des Vormischbrenners 10. Als effektiver Austrittsdurchmesser des Vormischbrenners ist dabei der Durchmesser eines Kreises zu verstehen, der die selbe Fläche hat, wie die Austrittsöffnung des Vormischbrenners.The object is solved by the entirety of the features of claim 1. Important for the inventive solution is that the injection openings are enlarged in diameter. However, this magnification must be limited to an optimal range. Furthermore, it has been shown that it is not the absolute size of the diameters to achieve good results that is decisive, but in each case a diameter ratio of the diameter of the injection opening 21 to the effective discharge diameter of the premix burner 10. The effective exit diameter of the premix burner is to be understood as the diameter of a circle which forms the same area as the outlet opening of the premix burner.

Eine typischer herkömmlicher Lochdurchmesser eines Brenners für Erdgas mit hohem Methananteil führte beispielsweise bei der Benutzung des neu eingeführten Verhältnisses von Durchmesser der Eindüsungsöffnung 21 zu effektivem Austrittsdurchmesser des Vormischbrenners 10 zu einem Durchmesserverhältnis von 0.0086. Für einen gasförmigen Brennstoff mit einem geringeren Heizwert wurde beispielsweise ein Durchmesserverhältnis von Durchmesser der Eindüsungsöffnung 21 zu effektivem Austrittsdurchmesser des Vormischbrenners 10 von 0.0097 benutzt.For example, a typical conventional hole diameter of a high methane natural gas burner resulted in the use of the newly introduced ratio of diameter of the injection port 21 to effective exit diameter of the premix burner 10 to a diameter ratio of 0.0086. For example, for a gaseous fuel having a lower calorific value, a diameter ratio of diameter of the injection port 21 to effective exit diameter of the premix burner 10 of 0.0097 was used.

Für beste Vermischung und Verbrennung ist neu ein Bereich der Durchmesserverhältnisse von Durchmesser der Eindüsungsöffnung zu effektivem Austrittsdurchmesser des Vormischbrenners, der zwischen 0.011 und 0.015 liegt, bestimmt worden. Für den Betrieb mit einem gasförmigen Brennstoff, der einen Heizwert hat, der um mindestens 20% unter dem Heizwert von Methan liegt wird ein erweiterter Bereich der Durchmesserverhältnisse von Durchmesser der Eindüsungsöffnung zu effektivem Austrittsdurchmesser des Vormischbrenners, vorgeschlagen das grösser als 0.015 ist und kleiner 0.017 ist. Insgesamt ergibt sich damit ein Vorteilhafter Bereich der Durchmesserverhältnisse von 0.011 bis 0.017. Entsprechend vergrössert sich auch der Abstand zwischen den Eindüsungsöffnungen beziehungsweise erniedrigt sich die Gesamtzahl der Eindüsungsöffnungen.For best mixing and combustion, a range of diameter ratios of diameter of the injection port to effective exit diameter of the premix burner, which is between 0.011 and 0.015, has now been determined. For operation with a gaseous fuel having a calorific value at least 20% below the net calorific value of methane, an extended range of diameter ratios of diameter of the injection port to effective exit diameter of the premix burner is proposed to be greater than 0.015 and less than 0.017 , Overall, this results in an advantageous range of diameter ratios from 0.011 to 0.017. Correspondingly, the distance between the injection openings or the total number of injection openings decreases.

Herkömmlich wurden die Eindüseöffnungen so klein wie möglich gehalten, um eine gute Vermischung zu ermöglichen. Eine Mindestgrösse war jedoch erforderlich, um die Druckverluste, die bei der Eindüsung des Brennstoffes entstehen, klein zu halten.Traditionally, the injection ports have been kept as small as possible to allow for good mixing. However, a minimum size was required in order to keep the pressure losses, which occur during the injection of the fuel, small.

Durch die neue Ausgestaltung der Lochreihen mit grösserem Durchmesser ergibt sich ein höherer Impuls der aus den Eindüsungsöffnungen kommenden Gasstrahlen, der zu einer verstärkten Durchdringung der querströmenden Verbrennungsluft und damit zu einer verbesserten Mischung führt. Mit der verbesserten Mischung vergleichmässigen sich die Flammentemperaturen, was mit einer Reduktion der Temperaturspitzen und der dadurch verursachten Schadstoffemissionen einhergeht.The new design of the rows of holes with a larger diameter results in a higher momentum of the gas jets coming from the injection openings, which leads to an increased penetration of the cross-flow combustion air and thus to an improved mixture. With the improved mix the flame temperatures, what associated with a reduction of the temperature peaks and the pollutant emissions caused thereby.

Ein weiterer Aspekt der Offenbarung ist es eine Höhe der Lufteintrittskanäle, in die das Brenngas 2. in den Vormischbrenner eingeleitet wird in einem auf die Eindüsungsöffnung angepassten Bereich anzugeben, der zu einer guten Durchmischung bei tiefem Druckverlust und stabiler Verbrennung führt. In Kombination mit dem genannten Verhältnissen der Durchmesser der Eindüsungsöffnung zu effektivem Austrittsdurchmesser des Vormischbrenners ist jeweils ein Verhältnis von Durchmesser der Eindüsungsöffnung zur Höhe des Lufteintrittskanals, das zwischen 0.097 und 0.153 liegt, vorteilhaft.Another aspect of the disclosure is to specify a height of the air inlet ducts into which the fuel gas 2 is introduced into the premix burner in a region adapted to the injection opening, which leads to a good mixing with low pressure loss and stable combustion. In combination with said ratios of the diameter of the injection opening to the effective discharge diameter of the premix burner, a ratio of the diameter of the injection opening to the height of the air inlet channel, which is between 0.097 and 0.153, is advantageous in each case.

Nach einer weiteren Ausgestaltung der Erfindung ist jeweils ein Verhältnis von der Summe der Flächen der Eindüsungsöffnungen zu effektivem Austrittsdurchmesser des Vormischbrenners in einem vorteilhaften Bereich zu wählen. Dieser Bereich liegt für die vorgeschlagenen Lochdurchmesserbereiche zwischen 0.0051 und 0.0097.According to a further embodiment of the invention, in each case a ratio of the sum of the areas of the injection openings to the effective exit diameter of the premix burner in an advantageous range is to be selected. This range is between 0.0051 and 0.0097 for the proposed hole diameter ranges.

Gemäss einer Ausgestaltung der Erfindung weisen alle Eindüsungsöffnungen einer Lochreihe denselben Durchmesser auf und sind äquidistant.According to one embodiment of the invention, all injection openings of a row of holes have the same diameter and are equidistant.

Eine andere Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass der Abstand zwischen benachbarten Eindüsungsöffnungen einer Lochreihe in etwa 16 mm beträgt.Another embodiment of the invention is characterized in that the distance between adjacent injection openings of a row of holes is approximately 16 mm.

Für den Betrieb mit Erdgas kann weiter ein vorteilhafter Bereich des Verhältnisses von Durchmesser der Eindüsungsöffnung zur Höhe der Lufteintrittskanäle angegeben werden, der zwischen 0.109 und 0.124 liegt. In Kombination mit den gegeben Lochdurchmesserbereichen sind insbesondere zwei besonders vorteilhafte Teilbereiche des Verhältnisses von Durchmesser der Eindüsungsöffnung zur Höhe der Lufteintrittskanäle bestimmt worden. Dies sind die Bereiche von 0.109 bis 0.112 und 0.119 bis 0.124.For operation with natural gas, an advantageous range of the ratio of diameter of the injection opening to the height of the air inlet channels can be further specified, which is between 0.109 and 0.124. In combination with the given hole diameter ranges, in particular two particularly advantageous partial regions of the ratio of the diameter of the injection opening to the height of the air inlet channels have been determined. These are the ranges from 0.109 to 0.112 and 0.119 to 0.124.

Eine andere Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass der Vormischbrenner für den Betrieb mit Erdgas als gasförmigem Brennstoff vorgesehen ist, und dass das Verhältnis von Lochdurchmesser der Eindüsungsöffnungen zu dem effektiven Austrittsdurchmesser des Vormischbrenners jeweils 0.012 beträgt.Another embodiment of the invention is characterized in that the premix burner is provided for operation with natural gas as gaseous fuel, and that the ratio of hole diameter of the injection ports to the effective exit diameter of the premix burner is 0.012 each.

Eine andere Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass der Vormischbrenner für den Betrieb mit einem gasförmigen Brennstoff vorgesehen ist, der einen Heizwert hat, der um mindestens 20% unter dem Heizwert von Methan liegt, und dass die Eindüsungsöffnungen jeweils ein Durchmesserverhältnis von Durchmesser der Eindüsungsöffnung zu effektivem Austrittsdurchmesser des Vormischbrenners von 0.0137 aufweisen.Another embodiment of the invention is characterized in that the premix burner is designed for operation with a gaseous fuel having a calorific value which is at least 20% below the calorific value of methane, and that the injection openings each have a diameter ratio of diameter of the injection port to have effective premix burner exit diameter of 0.0137.

Für den Betrieb mit einem gasförmigen Brennstoff , der einen Heizwert hat, der um mindestens 20% unter dem Heizwert von Methan liegt, kann weiter ein vorteilhafter Bereich des Verhältnisses von Durchmesser der Eindüsungsöffnung zur Höhe der Lufteintrittskanäle angegeben werden, der zwischen 0.123 und 0.140 liegt. In Kombination mit dem gegeben Lochdurchmesserbereich sind insbesondere zwei besonders vorteilhafte Teilbereiche des Verhältnisses von Durchmesser der Eindüsungsöffnung zur Höhe der Lufteintrittskanäle angegeben. Dies sind die Bereiche von 0.123 bis 0.128 und 0.134 bis 0.140.For operation with a gaseous fuel having a calorific value at least 20% below the calorific value of methane, an advantageous range of the ratio of diameter of the injection port to the height of the air inlet ports can be further specified, which is between 0.123 and 0.140. In combination with the given hole diameter range, in particular two particularly advantageous subregions of the ratio of the diameter of the injection opening to the height of the air inlet channels are indicated. These are the ranges from 0.123 to 0.128 and 0.134 to 0.140.

Einerseits muss die Brenngasgeschwindigkeit in den Eindüsungsöffnungen hoch genug sein, um einen gute Durchmischung zu erreichen, andererseits sollte diese tief sein, um die Druckverluste im Brenngassystem niedrig zu halten und damit eine, je nach Druckniveau des Gasversorgungssystems nötige, Verdichtung des Brenngases vor der Einleitung zu vermeiden oder auf ein Minimum zu beschränken. Die Brenngasgeschwindigkeit in den Eindüsungsöffnungen ist dabei proportional zur Gasmenge und umgekehrt proportional zur Summe der Flächen der Eindüsungsöffnungen eines Brenners. Typischerweise ist die in einen Brenner eingeleitete Brenngasmenge ausserdem proportional zu der Brennergrösse. Als Kenngrösse für eine optimale Brennerwahl ist Verhältnis von der Summe der Flächen der Eindüsungsöffnungen eines Brenners zur effektiven Austrittsfläche des Vormischbrenners vorgeschlagen, wobei der zur effektiven Austrittsfläche gehörende effektiven Austrittsdurchmesser typischerweise als Mass für die Brennergrösse angegeben wird.On the one hand, the fuel gas velocity in the injection openings must be high enough to achieve a good mixing, on the other hand, this should be deep to keep the pressure losses in the fuel gas system low and thus, depending on the pressure level of the gas supply system, necessary compression of the fuel gas before the introduction avoid or minimize it. The fuel gas velocity in the injection openings is proportional to the amount of gas and inversely proportional to the sum of the areas of the injection openings of a burner. Typically, the amount of fuel gas introduced into a burner is also proportional to the burner size. As a parameter for an optimal burner choice is ratio of the sum of the Areas of the injection openings of a burner to the effective exit surface of the premix burner proposed, wherein the effective exit area belonging effective exit diameter is typically given as a measure of the burner size.

Für den Betrieb mit Erdgas wurde als vorteilhaftes Verhältnis von der Summe der Flächen der Eindüsungsöffnungen zur effektiven Austrittsfläche des Vormischbrenners ein Verhältnis gefunden, das zwischen 0.005 und 0.008 liegt. Für den Betrieb mit einem gasförmigen Brennstoff, der einen Heizwert hat, der um mindestens 20% unter dem Heizwert von Methan liegt, wurde als vorteilhaftes Verhältnis von der Summe der Flächen der Eindüsungsöffnungen zur effektiven Austrittsfläche des Vormischbrenners ein Verhältnis bestimmt, das zwischen 0.007 und 0.010 liegt.For natural gas operation, a ratio of between 0.005 and 0.008 was found to be the favorable ratio of the sum of the areas of the injection ports to the effective exit area of the premix burner. For operation with a gaseous fuel having a calorific value at least 20% below the calorific value of methane, a ratio of between the sum of the areas of the injection ports and the effective exit area of the premix burner has been determined to be between 0.007 and 0.010 lies.

Gemäss einer Ausgestaltung der Erfindung sind pro Lufteintrittskanal jeweils zwei parallele Lochreihen mit doppeltem Lochabstand zwischen den Eindüsungsöffnungen vorgesehen, deren Löcher versetzt zueinander angeordnet sind. Durch die unterschiedlichen Einspritzpositionen kann die Verbrennungsstabilität positiv beeinflusst werden.According to one embodiment of the invention, two parallel rows of holes with a double hole spacing between the injection openings are provided per air inlet channel, the holes are arranged offset from one another. Due to the different injection positions, the combustion stability can be positively influenced.

Gemäss einer weiteren Ausgestaltung der Erfindung ist pro Lufteintrittskanal jeweils eine Lochreihe mit Eindüsungsöffnungen vorgesehen.According to a further embodiment of the invention, one row of holes with injection openings is provided per air inlet channel.

Neben dem neuartigen Vormischbrenner ist ein Verfahren zum Nacharbeiten derartiger Vormischbrenner Gegenstand der Erfindung. Aufgabe des Verfahrens ist es, einen herkömmlichen Vormischbrenner mit kleinen Eindüsungsöffnungen mit minimalem Aufwand so nachzuarbeiten, dass ein neuartiger Vormischbrenner mit grösseren Eindüsungsöffnungen erhalten wird. Zu diesem Zweck wird vorgeschlagen jedes zweite Loch einer Lochreihe von Eindüsungsöffnungen zu schliessen und den Durchmesser der verbleibenden Eindüsungsöffnung zu vergrössern. Zum Schliessen werden die Löcher beispielsweise zugeschweisst oder zugelötet. Beispielsweise kann auch ein kleiner Verschluss eingesetzt werden.In addition to the novel premix burner, a method for reworking such Vormischbrenner subject of the invention. The object of the method is to rework a conventional premix burner with small injection openings with minimal effort in such a way that a novel premix burner with larger injection openings is obtained. For this purpose, it is proposed to close every second hole of a row of holes of injection openings and to increase the diameter of the remaining injection opening. To close the holes, for example, welded or soldered. For example, a small closure can also be used.

Eine Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass die dem Austritt des Vormischbrenners zur Brennkammer am nächsten liegende Eindüsungsöffnung geschlossen wird. Von dort ausgehend wird alternierend jeweils ein Loch aufgebohrt und ein Loch verschlossen.An embodiment of the invention is characterized in that the ejection opening closest to the outlet of the premix burner to the combustion chamber is closed. Starting from there, a hole is drilled out alternately and a hole is closed.

Eine Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass die dem Austritt des Vormischbrenners zur Brennkammer am nächsten liegende Eindüsungsöffnung aufgebohrt wird. Von dort ausgehen werden alternierend jeweils ein Loch verschlossen wird und ein Loch aufgebohrt.An embodiment of the invention is characterized in that the injection opening closest to the outlet of the premix burner is bored to the combustion chamber. Starting from there, a hole is closed alternately and a hole drilled out.

Gemäss einer Ausgestaltung der Erfindung wird der Durchmesser der verbleibenden Eindüsungsöffnung so vergrössert, dass sich deren Austrittsfläche verdoppelt.According to one embodiment of the invention, the diameter of the remaining injection opening is increased so that its exit area doubles.

KURZE ERLÄUTERUNG DER FIGURENBRIEF EXPLANATION OF THE FIGURES

Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Es zeigen

Fig. 1
in einer perspektivischen, teilweise geschnittenen Seitenansicht einen bekannten Vormischbrenner vom Doppelkegel-Typ, wie er zur Verwirklichung der Erfindung geeignet ist; und
Fig. 2
verschiedene Lochreihen von Eindüsungsöffnungen bekannter und neuer Konfiguration im Verhältnis zum Vormischbrenner.
The invention will be explained in more detail with reference to embodiments in conjunction with the drawings. Show it
Fig. 1
in a perspective, partially sectioned side view of a known premix burner of the double-cone type, as it is suitable for implementing the invention; and
Fig. 2
different rows of holes of injection openings of known and new configuration in relation to the premix burner.

WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS FOR CARRYING OUT THE INVENTION

In Fig. 2 ist eine Hälfte eines Vormischbrenners 10 vom Doppelkegel-Typ dargestellt, wie er in grossen Gasturbinen zum Einsatz kommt. Erkennbar ist der Kegelcharakter des Vormischbrenners 10, der zum Brennraum hin (in Fig. 2 rechts) durch eine Frontplatte 13 begrenzt wird. Erkennbar ist auch ein Lufteintrittskanal 18, auf dessen Aussenseite quer eine Brennstoffleitung 16 für den gasförmigen Brennstoff angeordnet ist.In Fig. 2 One half of a premix burner 10 is shown in the double cone type, as used in large gas turbines. Visible is the cone character of the premix burner 10, which towards the combustion chamber (in Fig. 2 right) is limited by a front panel 13. Visible is also an air inlet channel 18, on the outside of which a fuel line 16 for the gaseous fuel is arranged transversely.

Bei den herkömmlichen Vormischbrennern wird der gasförmige Brennstoff in den Lufteintrittskanal 18 durch Eindüsungsöffnungen 21 eingedüst, die in Form und Anordnung die dargestellte Lochreihe R1 bilden. Hierbei handelt es sich um 32 Eindüsungsöffnungen 21 mit einem Durchmesserverhältnis von 0.0086 (für Erdgas; 0.0097 für einen Gas mit geringerem Heizwert), die untereinander einen Abstand von 8 mm haben und damit über eine Länge L von 8x31 mm verteilt sind. Von der Aussenseite der Frontplatte 13 hat die Lochreihe R1 einen Abstand a1 von 15 mm.In the conventional premix burners, the gaseous fuel is injected into the air inlet channel 18 through injection openings 21, which form the illustrated row of holes R1 in shape and arrangement. These are 32 injection ports 21 with a diameter ratio of 0.0086 (for natural gas, 0.0097 for a gas with a lower calorific value) spaced 8 mm apart and thus distributed over a length L of 8x31 mm. From the outside of the front panel 13, the row of holes R1 has a distance a1 of 15 mm.

Um hier nun kräftigere Brennstoffstrahlen zu erreichen, wird die Lochreihe R1 ersetzt durch die Lochreihe R2 oder R3, bei der nur noch 16 Eindüsungsöffnungen 21 mit einem vergrösserten Durchmesserverhältnis von 0.011 und einem Abstand d von jeweils 16 mm vorgesehen sind. Damit bleibt die Summe aller Strömungsquerschnitte der Eindüsungsöffnungen gegenüber der Lochreihe R1 gleich, die wenigeren Einzelstrahlen sind aber kräftiger und reichen somit tiefer in den Strom der Verbrennungsluft hinein und führen zu einer deutlichen Verbesserung der Vermischung. Der Abstand der Lochreihe zur Frontplatte 13 kann dabei gegenüber der Lochreihe R1 unverändert bleiben (Lochreihe R2; Abstand a1); es ist aber auch denkbar, diesen Abstand von 15 mm auf 23 mm zu vergrössern (Lochreihe R3; Abstand a2), wodurch der Bereich einer stabilen Verbrennung zu tieferen Temperaturen verschoben wird.In order to achieve more powerful fuel jets here, the row of holes R1 is replaced by the row of holes R2 or R3, in which only 16 injection openings 21 are provided with an enlarged diameter ratio of 0.011 and a distance d of 16 mm. Thus, the sum of all flow cross sections of the injection openings with respect to the row of holes R1 remains the same, but the fewer individual beams are stronger and thus reach deeper into the flow of combustion air and lead to a significant improvement in the mixing. The distance of the row of holes to the front plate 13 can remain unchanged with respect to the row of holes R1 (row of holes R2, distance a1); However, it is also conceivable to increase this distance from 15 mm to 23 mm (hole row R3, distance a2), which shifts the range of stable combustion to lower temperatures.

Das Durchmesserverhältnis von 0.012 für die Eindüsungsöffnungen 21 der Lochreihen R2 und R3 ist für die Verwendung von Erdgas vorgesehen. Wird anstelle von Erdgas ein gasförmiger Brennstoff mit Heizwert kleiner als 80% des Heizwertes von Methan eingedüst, habend die Eindüsungsöffnungen 21 vorzugsweise alle ein Durchmesserverhältnis von 0.014.The diameter ratio of 0.012 for the injection ports 21 of the rows of holes R2 and R3 is provided for the use of natural gas. If, instead of natural gas, a gaseous fuel having a calorific value less than 80% of the calorific value of methane is injected, the injection openings 21 preferably all have a diameter ratio of 0.014.

In der Ausführungsform R5 sind zwei parallele Lochreihen mit relativ zueinander versetzten Eindüsungsöffnungen vorgesehen, sodass die beiden Lochreihen relativ zueinander "auf Lücke" positioniert sind. Der Abstand zwischen den Löchern einer Lochreihen ist dabei auf 2 x d verdoppelt.In the embodiment R5, two parallel rows of holes with staggered injection openings are provided, so that the two rows of holes are positioned "in gap" relative to each other. The distance between the holes of a row of holes is doubled to 2 x d.

Wesentlich für die verbesserte Vermischung, Verbrennung und Schadstoffemission ist die Aufteilung des Massenstroms des gasförmigen Brennstoffs auf deutlich weniger Eindüsungsöffnungen mit grösserem Durchmesser. Entgegen der Erwartung, nach der für eine bessere Durchmischung eine grosse Anzahl kleiner Eindüsungslöcher mit entsprechend hohem Druckverlust bei der Eindüsung, zu einer verbesserten Durchmischung führen würde, können die Emissionen aufgrund der höheren Eindringtiefe mit grösseren Löchern reduziert werden. Es versteht sich von selbst, dass die Durchmesser und Abstände der Eindüsungsöffnungen 21 in einer Lochreihe im Rahmen der Erfindung gewisse Variationen aufweisen können, um Ungleichmässigkeiten in der Verbrennungsluftströmung ausgleichen zu können.Essential for the improved mixing, combustion and pollutant emission is the distribution of the mass flow of the gaseous fuel to significantly less injection openings with a larger diameter. Contrary to the expectation that a large number of small injection holes with a correspondingly high pressure loss during injection would lead to improved mixing for better mixing, the emissions can be reduced due to the higher penetration depth with larger holes. It goes without saying that the diameters and distances of the injection openings 21 in a row of holes in the context of the invention may have certain variations in order to be able to compensate for irregularities in the combustion air flow.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

1010
Vormischbrennerpremix
11,1211.12
TeilkegelschalePartial cone shell
1313
Frontplattefront panel
14,1514.15
Zylindercylinder
16,1716.17
Brennstoffleitungfuel line
18,1918.19
LufteintrittskanalAir inlet channel
2020
Verbrennungsluftcombustion air
2121
Eindüsungsöffnunginjection orifice
2222
Brennstoff (gasförmig)Fuel (gaseous)
2323
Brennstoff (flüssig)Fuel (liquid)
2424
Düsejet
2525
Brennraumcombustion chamber
2626
Bohrungdrilling
2727
Kühlluftcooling air
2828
Flammenfrontflame front
2929
Achseaxis
3030
Innenraum (kegelförmig)Interior (cone-shaped)
a1, a2a1, a2
Abstanddistance
dd
Abstanddistance
HH
Höhe der LufteintrittskanäleHeight of the air inlet ducts
LL
Längelength
R1,..,R5R1, .., R5
Lochreiherow of holes

Claims (15)

Vormischbrenner (10) für eine Gasturbine, in Form eines Doppelkegelbrenners, welcher zwei ineinander verschachtelt angeordnete Teilkegelschalen (11, 12) umfasst, die zwischen sich Lufteintrittskanäle (18, 19) bilden, durch die von aussen Verbrennungsluft (20) in einen kegelförmigen Innenraum (30) des Vormischbrenners (10) einströmt, wobei an den Aussenwänden der Lufteintrittskanäle (18, 19) quer zur Strömungsrichtung der Verbrennungsluft (20) verlaufende, lineare Lochreihen (R2, R3, R4) von Eindüsungsöffnungen (21) angeordnet sind, durch welche ein gasförmiger Brennstoff (22) in die quer dazu vorbeiströmende Verbrennungsluft (20) eingedüst wird, dadurch gekennzeichnet, dass die Eindüsungsöffnungen (21) jeweils ein Durchmesserverhältnis von Durchmesser der Eindüsungsöffnung (21) zu effektivem Austrittsdurchmesser des Vormischbrenners aufweisen, das zwischen 0.011 und 0.015 liegt.Premix burner (10) for a gas turbine, in the form of a double-cone burner, comprising two nested sub-cone shells (11, 12) between them forming air inlet ducts (18, 19) through which external combustion air (20) into a conical interior ( 30) of the premix burner (10) flows in, wherein on the outer walls of the air inlet ducts (18, 19) transverse to the flow direction of the combustion air (20) extending, linear rows of holes (R2, R3, R4) of injection openings (21) are arranged through which a gaseous fuel (22) is injected into the transverse thereto combustion air (20), characterized in that the injection openings (21) each have a diameter ratio of diameter of the injection opening (21) to the effective discharge diameter of the premix burner, which is between 0.011 and 0.015. Vormischbrenner (10) für eine Gasturbine, in Form eines Doppelkegelbrenners, welcher zwei ineinander verschachtelt angeordnete Teilkegelschalen (11, 12) umfasst, die zwischen sich Lufteintrittskanäle (18, 19) bilden, durch die von aussen Verbrennungsluft (20) in einen kegelförmigen Innenraum (30) des Vormischbrenners (10) einströmt, wobei an den Aussenwänden der Lufteintrittskanäle (18, 19) quer zur Strömungsrichtung der Verbrennungsluft (20) verlaufende, lineare Lochreihen (R2, R3, R4) von Eindüsungsöffnungen (21) angeordnet sind, durch welche ein gasförmiger Brennstoff (22) in die quer dazu vorbeiströmende Verbrennungsluft (20) eingedüst wird, dadurch gekennzeichnet, dass die Eindüsungsöffnungen (21) jeweils ein Durchmesserverhältnis von Durchmesser der Eindüsungsöffnung (21) zu effektivem Austrittsdurchmesser des Vormischbrenners aufweisen, das grösser als 0.015 und kleiner als 0.017 ist.Premix burner (10) for a gas turbine, in the form of a double-cone burner, comprising two nested sub-cone shells (11, 12) between them forming air inlet ducts (18, 19) through which external combustion air (20) into a conical interior ( 30) of the premix burner (10) flows in, wherein on the outer walls of the air inlet ducts (18, 19) transverse to the flow direction of the combustion air (20) extending, linear rows of holes (R2, R3, R4) of injection openings (21) are arranged through which a gaseous fuel (22) is injected into the transverse thereto combustion air (20), characterized in that the injection openings (21) each have a diameter ratio of diameter of the injection opening (21) to the effective outlet diameter of the premix burner, which is greater than 0.015 and less than Is 0.017. Vormischbrenner nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Eindüsungsöffnungen (21) jeweils ein Verhältnis von Durchmesser der Eindüsungsöffnung (21) zu Höhe (H) des Lufteintrittskanals (18, 19) aufweisen, das zwischen 0.097 und 0.153 liegt.Premix burner according to claim 1 or 2, characterized in that the injection openings (21) each have a ratio of diameter of the injection opening (21) to height (H) of the air inlet channel (18, 19), which is between 0.097 and 0.153. Vormischbrenner nach einem der Ansprüche 1-3 dadurch gekennzeichnet, dass die Eindüsungsöffnungen (21) jeweils ein Verhältnis von der Summe der Flächen der Eindüsungsöffnungen (21) zur effektiven Austrittsfläche des Vormischbrenners aufweisen, das zwischen 0.0051 und 0.0097 liegt.Premix burner according to one of claims 1-3, characterized in that the injection openings (21) each have a ratio of the sum of the areas of the injection openings (21) to the effective exit area of the premix burner, which is between 0.0051 and 0.0097. Vormischbrenner nach einem der Ansprüche 1-4, dadurch gekennzeichnet, dass alle Eindüsungsöffnungen (21) einer Lochreihe (R2, R3, R4) äquidistant sind und denselben Durchmesser aufweisen.Premix burner according to one of claims 1-4, characterized in that all injection openings (21) of a row of holes (R2, R3, R4) are equidistant and have the same diameter. Vormischbrenner nach einem der Ansprüche 1-5, dadurch gekennzeichnet, dass der Abstand zwischen benachbarten Eindüsungsöffnungen (21) einer Lochreihe (R2, R3, R4) in etwa 16 mm beträgt.Premix burner according to one of claims 1-5, characterized in that the distance between adjacent injection openings (21) of a row of holes (R2, R3, R4) is approximately 16 mm. Vormischbrenner nach einem der Ansprüche 1-6, dadurch gekennzeichnet, dass der Vormischbrenner (10) für den Betrieb mit Erdgas als gasförmigem Brennstoff (22) vorgesehen ist, und dass die Eindüsungsöffnungen (21) jeweils ein Verhältnis von Durchmesser der Eindüsungsöffnung (21) zu Höhe (H) der Lufteintrittskanäle (18, 19) aufweisen, das zwischen 0.109 und 0.124 liegt.Premix burner according to one of claims 1-6, characterized in that the premix burner (10) is provided for operation with natural gas as a gaseous fuel (22), and that the injection openings (21) each have a ratio of diameter of the injection opening (21) Height (H) of the air inlet channels (18, 19), which is between 0.109 and 0.124. Vormischbrenner nach einem der Ansprüche 1-6, dadurch gekennzeichnet, dass der Vormischbrenner (10) für den Betrieb mit einem gasförmigen Brennstoff (22) vorgesehen ist, der einen geringeren Heizwert hat als Erdgas, und dass die Eindüsungsöffnungen (21) jeweils ein Verhältnis von Durchmesser der Eindüsungsöffnung (21) zu Höhe (H) der Lufteintrittskanäle (18, 19) aufweisen, das zwischen 0.123 und 0.140 liegt.Premix burner according to one of claims 1-6, characterized in that the premix burner (10) is provided for operation with a gaseous fuel (22) having a lower calorific value than natural gas, and that the injection openings (21) each have a ratio of Diameter of the injection opening (21) to height (H) of the air inlet channels (18, 19), which is between 0.123 and 0.140. Vormischbrenner nach einem der Ansprüche 1-6, dadurch gekennzeichnet, dass der Vormischbrenner (10) für den Betrieb mit Erdgas als gasförmigem Brennstoff (22) vorgesehen ist und die Eindüsungsöffnungen (21) jeweils ein Verhältnis von der Summe der Flächen der Eindüsungsöffnungen (21) zur effektiven Austrittsfläche des Vormischbrenners aufweisen, das zwischen 0.005 und 0.008 liegt, oder dass der Vormischbrenner (10) für den Betrieb mit einem gasförmigen Brennstoff (22) vorgesehen ist, der einen geringeren Heizwert hat als Erdgas, und dass die Eindüsungsöffnungen (21) jeweils ein Verhältnis von der Summe der Flächen der Eindüsungsöffnungen (21) zur effektiven Austrittsfläche des Vormischbrenners aufweisen, das zwischen 0.007 und 0.010 liegt.Premix burner according to one of Claims 1-6, characterized in that the premix burner (10) is provided for operation with natural gas as gaseous fuel (22) and the injection openings (21) each have a ratio of the sum of the areas of the injection openings (21). to the effective exit area of the premix burner, which is between 0.005 and 0.008, or that the premix burner (10) is intended for operation with a gaseous fuel (22) having a lower calorific value than natural gas and in that the injection openings (21) respectively a ratio of the sum of the areas of the injection orifices (21) to the effective exit area of the premix burner, which is between 0.007 and 0.010. Vormischbrenner nach einem der Ansprüche 1-9, dadurch gekennzeichnet, dass pro Lufteintrittskanal (18, 19) jeweils zwei parallele Lochreihen (R5) mit zueinander versetzten Eindüsungsöffnungen (21) vorgesehen sind.Premix burner according to one of claims 1-9, characterized in that per each air inlet channel (18, 19) two parallel rows of holes (R5) are provided with staggered injection openings (21). Verfahren zum Nacharbeiten von Vormischbrennern (10) für eine Gasturbine, in Form eines Doppelkegelbrenners, welcher zwei ineinander verschachtelt angeordnete Teilkegelschalen (11, 12) umfasst, die zwischen sich Lufteintrittskanäle (18, 19) bilden, durch die von aussen Verbrennungsluft (20) in einen kegelförmigen Innenraum (30) des Vormischbrenners (10) einströmt, wobei an den Aussenwänden der Lufteintrittskanäle (18, 19) quer zur Strömungsrichtung der Verbrennungsluft (20) verlaufende, lineare Lochreihen (R1) von Eindüsungsöffnungen (21) angeordnet sind, durch welche ein gasförmiger Brennstoff (22) in die quer dazu vorbeiströmende Verbrennungsluft (20) eingedüst wird, dadurch gekennzeichnet, dass jedes zweite Loch einer Lochreihe (R1) von Eindüsungsöffnungen (21) geschlossen wird und der Durchmesser der verbleibenden Eindüsungsöffnung (21) vergrössert wirdA method for reworking premix burners (10) for a gas turbine, in the form of a double-cone burner, comprising two nested sub-cone shells (11, 12), which form between them air inlet ducts (18, 19) through which outside combustion air (20) in a conical interior (30) of the premix burner (10) flows, wherein on the outer walls of the air inlet channels (18, 19) transversely to the flow direction of the combustion air (20) extending, linear rows of holes (R1) of injection openings (21) are arranged, through which a gaseous fuel (22) is injected into the combustion air (20) flowing past it, characterized in that every second hole of a row of holes (R1) is closed by injection openings (21) and the diameter of the remaining injection opening (21) is increased Verfahren zum Nacharbeiten von Vormischbrennern (10) für eine Gasturbine nach Anspruch 11, dadurch gekennzeichnet, dass die Eindüsungsöffnungen zum Schliessen zugeschweisst oder zugelötet werden.A method for reworking premix burners (10) for a gas turbine according to claim 11, characterized in that the injection openings are closed or soldered for closing. Verfahren zum Nacharbeiten von Vormischbrennern (10) für eine Gasturbine nach Anspruch 11 oder 12, dadurch gekennzeichnet, die dem Austritt des Vormischbrenners (10) zur Brennkammer am nächsten liegende Eindüsungsöffnung (21) geschlossen wird und von dort ausgehend alternierend jeweils eine Eindüsungsöffnung (21) aufgebohrt und eine Eindüsungsöffnung (21) verschlossen wird.Method for reworking premix burners (10) for a gas turbine according to claim 11 or 12, characterized in that the outlet of the premix burner (10) to the combustion chamber closest to the injection port (21) is closed and from there starting from each one injection port (21) drilled and a injection port (21) is closed. Verfahren zum Nacharbeiten von Vormischbrennern (10) für eine Gasturbine nach Anspruch 11 oder 12, dadurch gekennzeichnet, dass die dem Austritt des Vormischbrenners zur Brennkammer am nächsten liegende Eindüsungsöffnung (21) aufgebohrt wird und von dort ausgehend alternierend jeweils eine Eindüsungsöffnung (21) verschlossen wird und eine Eindüsungsöffnung (21) aufgebohrt. wirdA method for reworking premix burners (10) for a gas turbine according to claim 11 or 12, characterized in that the outlet of the premix burner to the combustion chamber closest to the injection port (21) is drilled and from there starting from each one injection port (21) is closed and an injection port (21) drilled. becomes Verfahren zum Nacharbeiten von Vormischbrennern (10) für eine Gasturbine nach einem der Ansprüche 11 bis 14, dadurch gekennzeichnet, dass der Durchmesser der verbleibenden Eindüsungsöffnungen (21) so vergrössert wird, dass sich deren Austrittsfläche verdoppelt.Method for reworking premix burners (10) for a gas turbine according to one of claims 11 to 14, characterized in that the diameter of the remaining injection openings (21) is increased so that their exit area doubles.
EP11178196.9A 2010-08-27 2011-08-19 Premix burner for a gas turbine Active EP2423597B1 (en)

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EP2685162A1 (en) * 2012-07-10 2014-01-15 Alstom Technology Ltd Premix burner of the multi-cone type for a gas turbine and method for operating such a burner
EP2685160A1 (en) 2012-07-10 2014-01-15 Alstom Technology Ltd Premix burner of the multi-cone type for a gas turbine
EP2685161A1 (en) 2012-07-10 2014-01-15 Alstom Technology Ltd Combustor arrangement, especially for a gas turbine
EP2685163A1 (en) 2012-07-10 2014-01-15 Alstom Technology Ltd Premix burner of the multi-cone type for a gas turbine
EP3299720A1 (en) 2016-09-22 2018-03-28 Ansaldo Energia IP UK Limited Combustor front assembly for a gas turbine
EP2700879B1 (en) * 2012-08-24 2019-03-27 Ansaldo Energia Switzerland AG Method for mixing a dilution air in a sequential combustion system of a gas turbine, and sequential combustion system for a gas turbine comprising dilution air injector
CN112922744A (en) * 2021-03-05 2021-06-08 中国空气动力研究与发展中心空天技术研究所 Wall-embedded aircraft fuel conveying device

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US11242804B2 (en) 2017-06-14 2022-02-08 General Electric Company Inleakage management apparatus
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CN108006640B (en) * 2017-12-21 2024-02-13 靖江博鑫柯曼燃烧器制造有限公司 Multipurpose oxygen-enriched burner
KR102065582B1 (en) 2018-03-16 2020-01-13 두산중공업 주식회사 Fuel injection device for gas turbine, fuelnozzle and gas turbinehaving it

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Publication number Priority date Publication date Assignee Title
EP2685162A1 (en) * 2012-07-10 2014-01-15 Alstom Technology Ltd Premix burner of the multi-cone type for a gas turbine and method for operating such a burner
EP2685160A1 (en) 2012-07-10 2014-01-15 Alstom Technology Ltd Premix burner of the multi-cone type for a gas turbine
EP2685161A1 (en) 2012-07-10 2014-01-15 Alstom Technology Ltd Combustor arrangement, especially for a gas turbine
EP2685163A1 (en) 2012-07-10 2014-01-15 Alstom Technology Ltd Premix burner of the multi-cone type for a gas turbine
US8950187B2 (en) 2012-07-10 2015-02-10 Alstom Technology Ltd Premix burner of the multi-cone type for a gas turbine
RU2561767C2 (en) * 2012-07-10 2015-09-10 Альстом Текнолоджи Лтд Burner of multi-cone type for pre-mixing for gas turbine
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US9933163B2 (en) 2012-07-10 2018-04-03 Ansaldo Energia Switzerland AG Combustor arrangement with slidable multi-cone premix burner
EP2700879B1 (en) * 2012-08-24 2019-03-27 Ansaldo Energia Switzerland AG Method for mixing a dilution air in a sequential combustion system of a gas turbine, and sequential combustion system for a gas turbine comprising dilution air injector
EP3299720A1 (en) 2016-09-22 2018-03-28 Ansaldo Energia IP UK Limited Combustor front assembly for a gas turbine
CN112922744A (en) * 2021-03-05 2021-06-08 中国空气动力研究与发展中心空天技术研究所 Wall-embedded aircraft fuel conveying device

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KR101525463B1 (en) 2015-06-03
CH703655A1 (en) 2012-02-29
KR20120021213A (en) 2012-03-08
AU2011213841A1 (en) 2012-03-15
US9170022B2 (en) 2015-10-27
EP2423597B1 (en) 2016-08-17
US20120047898A1 (en) 2012-03-01
EP2423597A3 (en) 2012-08-15
AU2011213841B2 (en) 2014-10-23

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