presenting the fuel injections below a limit fuel flow such that the energy is injected best on sucking part or perhaps the pressure side and/or best through every next or third gasoline nose of a swirl vane and/or that gasoline is only inserted through gas nozzles of every second or 3rd swirl vane on the burner.
14. The axial swirler in accordance with state 1, where the axial swirler is within an annular combustor, can combustors, or just one or reheat engine.
18. The burner according to claim 6, where the energy nozzles is elongated slot nozzles expanding in essence parallel into leading edge regarding the swirl vane.
19. The burner relating to claim 6, when the energy nozzles include an initial nozzle for injection of liquid-fuel, and/or another nozzle for treatment of a gaseous energy and a third nozzle for shot of company air, which encloses initial nozzle and/or the next nozzle.
20. The method according to state 13, where the very reactive gas consists of natural gas fuels, hydrogen rich fuels, and hydrogen gasoline.
These and various other objects are achieved by an axial swirler, specifically for premixing of oxidizer and fuel in gas turbines, containing a series or a plurality of swirl vanes with a streamline cross-section, each swirl vane having a prominent advantage, a trailing edge, and a sucking area and a force part. One or more swirl vane has a discharge circulation angle between a tangent to their camber range at their trailing sides in addition to swirler axis that will be monotonically growing with growing radial range from swirler axis.
The swirl vanes are positioned around a swirler axis, where stated respected sides increase radially outwardly, basically in radial way, and where flow slot machines tend to be developed between the suction area of every swirl vane while the force side of the closest neighboring swirl vane
- The rise in I? enables a decrease in the swirl number (cf. FIG. 5 ) as well as the pressure losings (cf. FIG. 6 ).
The burner containing an axial swirler as described above are characterized where one or more associated with swirl vanes try set up as an injections tool with one or more gas nozzle for adding one or more fuel inside burner.
The burner may be used for fuel-air mixing in addition to mixing of gas or fuel with whatever gas utilized in closed or semi-closed gasoline turbines or with burning gases of an initial combustion period. The burner can be utilized for fuel turbines comprising one compressor, one combustor and another turbine and for gas generators with one or several compressors, at the very least two combustors and at least two generators.
The inflow was coaxial towards the longitudinal axis 47 of the swirler 43
Also today’s innovation relates to the effective use of a burner as identified above for your combustion under large reactivity conditions, preferably when it comes down to burning at higher burner inlet temperature and/or for your burning of MBtu fuel, ordinarily with a calorific value of 5,000-20,000 kJ/kg, ideally 7,000-17,000 kJ/kg, much more ideally 10,000-15,000 kJ/kg, most preferably this type of a fuel comprising hydrogen petrol.
The swirler vanes 3 found in FIG. 3 extend from a respected edge 38 to a trailing advantage 39. The key edge area of each vane 3 provides a profile, that will be oriented essentially parallel to your inflow. The pages regarding the vanes 3 turn through the main flow movement 48, for example. in downstream movement the streamline visibility twists and curve eg to create a smoothly designed suction side 31 and pressure side 32. This profile imposes a swirl on stream and brings about an outlet-flow course, with an angle relative to the inlet stream direction 48. The primary movement was coaxial towards the annular swirler. The retailer movement are spinning all over axis 47 associated with the swirler 43.
In FIG. 4(a) increased swirl configuration, in other words. a swirler with a low swirl quantity sn of 0.7 are found, whereas in FIG. 4(b) a swirler with a lowered swirl, i.e. with a diminished swirl number than the embodiment in FIG. 4(a) is actually found (sletter of approximately 0.5 to 0.6). Simply put, the vanes 3 with the embodiment of FIG. 4(a) tend to be more twisted versus vanes 3 for the embodiment of FIG. 4(b) .
2. The axial swirler per state 1, when the key edge of each of the swirl vanes was an essentially straight edge increasing in a radial direction and/or the camber distinctive line of the swirl vane try rounded in order to create a C-shape or an S-shape.
when a discharge movement direction (I±) in said radial range (roentgen) is given by a work: brown [I±(R)]=KA·RI arablounge reviews?+H, wherein I? try starting from 1 to 10, and K and H were constants plumped for so that the release circulation direction (I±(Rmin)) at least radial range (Rmin) are from 0 grade to 20 qualifications as well as the discharge circulation angle (I±(Rmax)) at a max radial length (Rmax) was from 30 grade to 50 qualifications, the strategy comprising: adding air through axial swirler and determining many gasoline nozzles by which gasoline is injected as a purpose of a complete injected fuel flow; and injecting fuel into the range the gas nozzles determined just like the function of the entire injected fuel flow.