presenting the fuel injections below a threshold fuel-flow in a way that the gasoline try inserted only on the sucking area or even the pressure side and/or best through every next or 3rd gas nozzle of a swirl vane and/or that fuel is just inserted through the gas nozzles of every 2nd or third swirl vane in the burner.
14. The axial swirler hookup according to declare 1, when the axial swirler is during an annular combustor, can combustors, or just one or reheat motor.
18. The burner relating to state 6, where the gas nozzles tend to be elongated position nozzles expanding basically parallel towards industry leading in the swirl vane.
19. The burner in accordance with declare 6, whereby the gasoline nozzles make up a first nozzle for injections of liquid-fuel, and/or another nose for shot of a gaseous energy and a 3rd nozzle for shot of service environment, which encloses the most important nose and/or another nose.
20. The technique in accordance with claim 13, where the highly activated energy includes natural gas fuels, hydrogen rich fuels, and hydrogen energy.
The aforementioned as well as other objects tend to be achieved by an axial swirler, particularly for premixing of oxidizer and gas in gas generators, comprising a set or a plurality of swirl vanes with an improve cross-section, each swirl vane creating the leading advantage, a trailing edge, and a suction side and a force part. One or more swirl vane has a discharge movement angle between a tangent to their camber range at its trailing sides and swirler axis that is monotonically increasing with growing radial point through the swirler axis.
The swirl vanes was arranged around a swirler axis, whereby said trusted border extend radially outwardly, really in radial direction, and where flow slot machines is created involving the sucking area of each and every swirl vane in addition to force side of their closest neighboring swirl vane
- The increase in I? provides a decrease in the swirl numbers (cf. FIG. 5 ) while the stress losings (cf. FIG. 6 ).
The burner containing an axial swirler as outlined above was defined because at least one for the swirl vanes are configured as an injections product with one energy nose for bringing in at least one gas to the burner.
The burner can be utilized for fuel-air blending in addition to mixing of gasoline or gasoline with almost any fuel included in closed or semi-closed gas generators or with burning fumes of an initial combustion period. The burner can be used for fuel generators comprising one compressor, one combustor and another turbine as well as for gasoline generators with one or numerous compressors, at the least two combustors and also at least two turbines.
The inflow was coaxial on the longitudinal axis 47 of this swirler 43
Moreover the present development pertains to the application of a burner as described above for all the combustion under highest reactivity problems, ideally for combustion at high burner inlet conditions and/or for any combustion of MBtu gasoline, typically with a calorific property value 5,000-20,000 kJ/kg, preferably 7,000-17,000 kJ/kg, more preferably 10,000-15,000 kJ/kg, more ideally these a fuel comprising hydrogen gas.
The swirler vanes 3 found in FIG. 3 stretch from the leading edge 38 to a trailing sides 39. The best side part of each vane 3 enjoys a profile, in fact it is focused in essence parallel towards the inflow. The pages of this vanes 3 turn through the biggest stream course 48, for example. in downstream direction the improve profile twists and bends particularly in order to create a smoothly shaped suction side 31 and stress area 32. This profile imposes a swirl in the circulation and leads to an outlet-flow way, with an angle in accordance with the inlet stream course 48. An important flow was coaxial into annular swirler. The socket circulation are turning all over axis 47 on the swirler 43.
In FIG. 4(a) increased swirl configuration, in other words. a swirler with the lowest swirl amounts sn of 0.7 was found, whereas in FIG. 4(b) a swirler with a lesser swirl, in other words. with a reduced swirl amounts compared to embodiment in FIG. 4(a) was found (sn of approximately 0.5 to 0.6). This means that, the vanes 3 of embodiment of FIG. 4(a) tend to be more complicated versus vanes 3 on the embodiment of FIG. 4(b) .
2. The axial swirler in accordance with state 1, whereby the leading edge of all the swirl vanes was a really straight-edge extending in a radial direction and/or the camber type of the swirl vane try curled to form a C-shape or an S-shape.
when a release stream perspective (I±) on mentioned radial range (R) is provided by a purpose: tan [I±(roentgen)]=KA·RI?+H, whereby I? was which range from 1 to 10, and K and H are constants chosen such that the discharge stream angle (I±(Rmin)) at the very least radial point (Rmin) was from 0 qualifications to 20 levels and also the release stream angle (I±(Rmax)) at a max radial length (Rmax) try from 30 levels to 50 degrees, the technique comprising: launching air through axial swirler and identifying several energy nozzles through which gasoline is injected as a function of an overall injected fuel flow; and injecting fuel to the amount of the fuel nozzles determined as the purpose of the entire inserted fuel-flow.