The suction part in addition to stress area extend each amongst said trusted and trailing edges

08 Feb The suction part in addition to stress area extend each amongst said trusted and trailing edges

staging the gasoline shot below a threshold fuel flow such that the fuel was injected only throughout the suction part or perhaps the force area and/or merely through every 2nd or 3rd energy nose of a swirl vane and/or that gasoline is just inserted through the gas nozzles of each second or next swirl vane regarding the burner.

14. The axial swirler in accordance with state 1, whereby the axial swirler is actually an annular combustor, can combustors, or one or reheat system.

18. The burner in accordance with declare 6, when the gas nozzles become elongated slot nozzles expanding essentially parallel towards leading edge on the swirl vane.

19. The burner according to claim 6, whereby the energy nozzles comprise an initial nose for treatment of liquid fuel, and/or another nozzle for shot of a gaseous gasoline and a 3rd nose for injection of provider atmosphere, which encloses the first nozzle and/or the second nozzle.

20. The technique based on state 13, when the highly activated gas consists of gas fuels, hydrogen rich fuels, and hydrogen gasoline.

The aforementioned along with other stuff are accomplished by an axial swirler, particularly for premixing of oxidizer and fuel in petrol turbines, containing a string or a plurality of swirl vanes with a streamline cross-section, each swirl vane having the leading advantage, a trailing sides, and a suction side and a stress area. One swirl vane keeps a discharge circulation direction between a tangent to their camber range at its trailing side as well as the swirler axis which monotonically increasing with growing radial range through the swirler axis.

The swirl vanes is actually arranged around a swirler axis, wherein said respected borders increase radially outwardly, really in radial movement, and when circulation slots become established amongst the sucking side of each and every swirl vane together with pressure side of the closest neighboring swirl vane

• The increase in I? enables a reduction of the swirl quantity (cf. FIG. 5 ) together with force loss (cf. FIG. 6 ).

The burner comprising an axial swirler as outlined above are classified for the reason that one of the swirl vanes is actually set up as a treatment equipment with one fuel nozzle for adding one gas in to the burner.

The burner may be used for fuel-air mixing together with blending of gasoline or gas with any sort of fuel used in sealed or semi-closed petrol generators or with burning fumes of a primary combustion phase. The burner can be utilized for gas turbines comprising one compressor, one combustor and one turbine as well as for fuel turbines with one or several compressors, about two combustors as well as minimum two generators.

The inflow was coaxial to the longitudinal axis 47 on the swirler 43

Also the present creation pertains to making use of a burner as described above for all the burning under highest reactivity circumstances, preferably for burning at highest burner inlet temperature and/or when it comes down to combustion of MBtu gasoline, generally with a calorific property value 5,000-20,000 kJ/kg, ideally 7,000-17,000 kJ/kg, a lot more preferably 10,000-15,000 kJ/kg, most ideally these a gas comprising hydrogen gasoline.

The swirler vanes 3 found in FIG. 3 increase from a number one advantage 38 to a trailing sides 39. The main side part of each vane 3 features a profile, that is focused basically parallel towards inflow. The users regarding the vanes 3 turn through the main flow path 48, for example. in downstream course the improve profile twists and bends such in order to create a smoothly shaped suction part 31 and stress part 32. This shape imposes a swirl about stream and results in an outlet-flow movement, that has an angle in accordance with the inlet circulation direction 48. The primary stream are coaxial on annular swirler. The outlet stream is actually rotating across axis 47 with the swirler 43.

In FIG. 4(a) a higher swirl arrangement, i.e. a swirler with a reduced swirl amounts s_n of 0.7 is shown, whereas in FIG. 4(b) a swirler with less swirl, for example. with a diminished swirl number compared to embodiment in FIG. 4(a) is found (s_n around 0.5 to 0.6). Simply put, the vanes 3 of this embodiment of FIG. 4(a) tend to be more complicated than the vanes 3 in the embodiment of FIG. 4(b) .

2. The axial swirler in accordance with claim 1, where the leading asiandating edge of all the swirl vanes was an in essence straight-edge increasing in a radial path and/or the camber collection of the swirl vane is curved in order to create a C-shape or an S-shape.

wherein a release movement perspective (I±) on said radial distance (roentgen) is given by a purpose: brown [I±(roentgen)]=KA·RI?+H, whereby I? was ranging from 1 to 10, and K and H become constants chosen in a way that the release stream angle (I±(Rmin)) at least radial length (Rmin) was from 0 grade to 20 levels while the release stream direction (I±(Rmax)) at a maximum radial point (Rmax) is from 30 levels to 50 levels, the technique comprising: exposing air through axial swirler and identifying several fuel nozzles through which gasoline is actually injected as a function of a total injected fuel-flow; and inserting energy into the wide range of the gasoline nozzles determined given that function of the entire inserted fuel flow.