Burner device and method for injecting a mixture of fuel and oxidant into a combustion space

Abstract

A burner device is made available, comprising a combustion chamber with a combustion space and an injection device for injecting a mixture of fuel and oxidant into the combustion space, wherein the injection device has a plurality of nozzles arranged on a circular line, the nozzles each have a nozzle chamber, fuel nozzles or fuel pipes for the coupling in of fuel open into the nozzle chambers, oxidant can be coupled into the nozzle chambers via a feed device for generating a mixture and wherein nozzle apertures of the nozzles in the combustion space are designed as elongated holes.

1 . Burner device, comprising:
 a combustion chamber with a combustion space; and   an injection device for injecting a mixture of fuel and oxidant into the combustion space;   wherein the injection device has a plurality of nozzles arranged on a circular line;   wherein the nozzles each have a nozzle chamber;   wherein fuel nozzles or fuel pipes for the coupling in of fuel open into the nozzle chambers;   wherein oxidant is able to be coupled into the nozzle chambers via a feed device for generating a mixture; and   wherein nozzle apertures of the nozzles in the combustion space are designed as elongated holes.   
   
   
       2 . Burner device as defined in  claim 1 , wherein the ratio of hole circumference to hole surface area is greater in the case of the elongated holes than in the case of a circular hole with the same hole circumference or same hole surface area. 
   
   
       3 . Burner device as defined in  claim 2 , wherein the ratio is greater by at least a factor of 1.2. 
   
   
       4 . Burner device as defined in  claim 2 , wherein the ratio is greater by at least a factor of 1.4. 
   
   
       5 . Burner device as defined in  claim 2 , wherein the ratio is greater by at least a factor of 1.5. 
   
   
       6 . Burner device as defined in  claim 1 , wherein a length of a nozzle aperture is greater than a greatest width of the nozzle aperture. 
   
   
       7 . Burner device as defined in  claim 6 , wherein the length of the nozzle aperture is at least 1.5 times greater than the greatest width. 
   
   
       8 . Burner device as defined in  claim 1 , wherein the nozzle apertures are aligned with their center line radially or at an angle of less than 30° in relation to the radial direction. 
   
   
       9 . Burner device as defined in  claim 1 , wherein the rotational orientation in relation to an axis of a nozzle aperture parallel to the axis of the combustion space is adjustable at least in an angular range. 
   
   
       10 . Burner device as defined in  claim 1 , wherein a nozzle aperture is of a slit-like design. 
   
   
       11 . Burner device as defined in  claim 1 , wherein a nozzle aperture is of a triangular design. 
   
   
       12 . Burner device as defined in  claim 1 , wherein a nozzle aperture has one or more curved boundary lines. 
   
   
       13 . Burner device as defined in  claim 1 , wherein the combustion space is of a rotationally symmetric design. 
   
   
       14 . Burner device as defined in  claim 1 , wherein the combustion chamber has an outlet area with a narrowing inner cross section. 
   
   
       15 . Burner device as defined in  claim 1 , wherein its design is such that a recirculation of exhaust gas is able to be formed in the combustion space. 
   
   
       16 . Burner device as defined in  claim 1 , wherein several nozzles are arranged one behind the other in a radial direction on the circular line. 
   
   
       17 . Burner device as defined in  claim 1 , wherein a hole surface area of an elongated hole is greater than or equal to a surface area of an outlet aperture of a fuel nozzle or a fuel pipe into a nozzle chamber. 
   
   
       18 . Burner device as defined in  claim 1 , comprising a switching device for switching one or more nozzles to active or inactive with respect to the injection of a mixture of fuel and oxidant through the respective nozzles. 
   
   
       19 . Method for injecting a mixture of fuel and oxidant into a combustion space, comprising:
 bringing fuel and oxidant into nozzle chambers in order to produce a mixture of fuel and oxidant; and   injecting the mixture of fuel and oxidant into the combustion space via nozzle apertures adjoining the nozzle chambers;   wherein the nozzle apertures are arranged so as to be distributed on a circular line and are designed as elongated holes.   
   
   
       20 . Method as defined in  claim 19 , wherein the mixture of fuel and oxidant is injected into the combustion space with a higher velocity than the turbulent flame velocity in the combustion space. 
   
   
       21 . Method as defined in  claim 19 , wherein one or more nozzles are inactivated for the purpose of reducing the mass flow of the mixture of fuel and oxidant injected into the combustion space. 
   
   
       22 . Method as defined in  claim 21 , wherein the inactivated nozzles are selected such that they are distributed symmetrically on the circular line.