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 
  • F23C13/00—Apparatus in which combustion takes place in the presence of catalytic material
  • F23C13/08—Apparatus in which combustion takes place in the presence of catalytic material characterised by the catalytic material
• • 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
  • F23D14/12—Radiant burners
  • F23D14/18—Radiant burners using catalysis for flameless combustion
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23D—BURNERS
  • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
  • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
• • 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
  • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
• • 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
  • 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
  • F23C2900/13002—Catalytic combustion followed by a homogeneous combustion phase or stabilizing a homogeneous combustion phase

Definitions

• the invention relates to a method and an apparatus for Operation of a premix burner, in particular an agent vortex breakdown stabilized double cone type burner, which operated in particular with gaseous fuels and preferably used in gas turbine combustors becomes.
• the device relates to the fuel supply.
• premix burners are used for typical gas turbine operations Usually designed so that their fuel / air ratio the lowest NOx emissions when operating under Full load delivers. You will therefore be close to the lean extinguishing limit operated, their control range is very limited.
• the premix burner is the additional one that is located close to the axis Injection of pilot gas so that the fuel gases are enriched.
• the invention tries to avoid all these disadvantages. your the task is based on a vortex breakdown stabilized, operated with gaseous fuels Premix burner for a gas turbine combustor with simple Means to enlarge the area of flame stability, so that the premix burner can also be used without problems under partial load conditions or in the case of very lean main fuel / combustion air mixtures is working.
• this is the case with a method according to the generic term of claim 1 achieved in that the Pilot gas / air mixture at one inside the fuel lance arranged at the top of the burner arranged catalyst is ignited and burned there and the hot gas flow then the colder main burner flow inside the burner is added.
• this is for a fuel supply for a low-pollutant stabilized by vortex breakdown Premix burner, in particular a burner of the double cone type, achieved according to the preamble of claim 4, that the supply means for the pilot gas and the pilot air is a jet pump arranged in the fuel lance and that at the end of the fuel lance at the burner tip Catalyst ring-shaped between the feed channel for the liquid fuel and the main gas channel is arranged.
• the advantages of the invention include that the area of flame stability for one by means of vortex breakdown stabilized premix burner towards lean Fuel / air mixtures are shifted and the efficiency the plant is increased.
• the catalyst sets the Combustion without NOx generation in progress and the resulting hot flow mixes with the colder main burner flow. This delays a further homogeneous reaction.
• the catalytic ignition is therefore stabilized with a hot flow flame connected.
• Another advantage of the invention is that Because of the arrangement of the catalyst in the interchangeable Fuel lance also replaced the catalytic converter very quickly if operational safety problems occur. In addition, a fuel lance can already work for you burner in operation in a gas turbine plant can be easily retrofitted with the catalyst.
• pilot gas is under pressure by means of a jet pump integrated in the fuel lance is introduced and its pressure energy is used to a sufficient amount of combustion air from the plenum outside the burner hood into the fuel lance and pre-mix it with the pilot gas, because that’s one good mixing of pilot fuel and combustion air achieved and a cheap high pressure combustion of the gaseous Fuel / air mixture is reached.
• an active catalyst preferably palladium oxide PdO, platinum, metal oxide mixtures or barium hexaaluminates
• the catalyst support a honeycomb body with a suitable cell density or Pellets can be used.
• Fig. 1 shows a partial longitudinal section of a gas turbine combustion chamber 1 with a premix burner 2.
• This premix burner is a low-pollution double-cone burner, which in its basic structure described for example in EP-B1-0 321 809 becomes. It essentially consists of two hollow Partial conical bodies complementing a body with tangential ones Air inlet slots, the central axes of the Partial cone body widening in the direction of flow Have a taper and offset in the longitudinal direction to each other run.
• the two partial cone bodies each have one Fuel line 3 for supplying the main gaseous fuel 4 on which of the through the tangential air inlet slots flowing combustion air 5 is mixed.
• the combustion air 5 is used before mixing with the Main fuel gas 4 as cooling air from the combustion chamber 1. This collects then in turn within the burner hood 6 located plenum 7 before starting with the main fuel is mixed. The mixture formation with the combustion air takes place directly at the end of the air inlet slots.
• the fuel lance 8 is easily exchangeable and contains supply means 9 for the gaseous pilot fuel 10, supply means 11 for a possibly usable liquid fuel 12 through a nozzle 13, for example a swirl nozzle or a pressure atomizer into the burner interior 14 is dusted, and feed means 15 for from a plenum 16th pilot air 17 supplied outside the burner hood 6.
• the main fuel 4 flows in the feed line 3 in the Double cone burner and mixes with the combustion air 15, which are formed by the partial cone bodies 18, 19 Air inlet slots 20 in the burner interior of the double-cone burner 2 flows. Ignition of the fuel / air mixture occurs only at the top of the backflow zone, so that there is a stable flame front. The flame strikes not back inside the burner.
• a catalyst 21 within the fuel lance 8 is at the top of the cone arranged a catalyst 21 according to the invention. He is is annular between the feed channel 11 for liquid fuel 12 and the feed channel 3 for the main fuel 4. Upstream of the catalyst 21 is a jet pump 22 in the Fuel lance 8 arranged. By means of this into the fuel lance 8 integrated jet pump 22 becomes the pilot gas 10 introduced into the lance under pressure. At the same time, his Pressure energy used a sufficient amount of pilot air 17 to be introduced from the plenum 16 outside the burner hood 6 and mix it well with the pilot fuel. By Installation of vortex elements in the feed channel 15 of the pilot air 17 a further advantageous mixing can be achieved will. The pilot fuel / air mixture 25 then flows to the catalyst located at the top of the double cone burner 21 to. The catalyst now initiates the combustion, whereby Hardly measurable NOx emissions arise. The through the Hot gas flow generated by the catalyst mixes in the interior of the burner 14 with the colder main burner flow and improved thereby the stability of the main flame.
• the area of flame stability is expanded significantly, by catalytic ignition with hot gas flow flame stabilization is linked.
• a material is used as the catalyst 21, which a the highest possible catalytic activity with sufficient thermal Stability guaranteed. It is particularly advantageous the use of palladium oxide PdO as catalyst 21 because it is the most active material for igniting methane oxidation is.
• thermally stable compared to PdO catalytic somewhat less active materials are used, for example Platinum, metal oxide mixtures (such as perovskite, spinels) or barium hexaaluminate.
• the catalyst 21 is in a honeycomb body 24 arranged, the cell density of the honeycomb body 24 different Stress conditions can be adjusted.
• the design must be such that a sufficiently large one Catalyst area is available.
• the catalyst 21 can be replaced quickly and easily will.
• the fuel lances 8 can already be existing burner 2 well with this catalyst 21 and the Retrofit jet pump 22.
• the previous embodiment referred to a burner 2, which is operated with gaseous fuels 4, 10.
• the invention can also be used for combined operation or for operation with liquid fuel 12.
• pilot gas 10 into the fuel lance 8 not necessary, but this will be 22 additional with the jet pump Air 17 pumped in, for example, at part-load operation in addition to atomizing the liquid fuel 12 can be used.
• the catalyst then has 21 lost its actual function; but it bothers not even the operational process.

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

Applications Claiming Priority (2)

Publications (3)

Family

ID=6532614

Family Applications (1)

Country Status (3)

Cited By (9)

Families Citing this family (31)

Citations (1)

Family Cites Families (10)

• 1994
  • 1994-11-05 DE DE4439619A patent/DE4439619A1/de not_active Withdrawn
• 1995
  • 1995-10-17 DE DE59509509T patent/DE59509509D1/de not_active Expired - Fee Related
  • 1995-10-17 EP EP95810645A patent/EP0710797B1/fr not_active Expired - Lifetime
  • 1995-10-30 US US08/550,351 patent/US5569020A/en not_active Expired - Fee Related

Patent Citations (1)

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