Mixing screw for a fuel injector in a combustion chamber of a gas turbine, and corresponding combustion device
View Patent ↗In a fuel injection device at a base of a combustion chamber, a mixing air inlet screw is manufactured with its peripheral holes extending only over a sector of a circle directed towards the air's propagation cone, wherein the remainder of the periphery of the screw is closed. It is then possible to reduce load loss of the injection system while obtaining an improved quality of the mix supplied to the chamber. Such a device can be used in gas turbines fitted with centrifugal compressors and in which the air flow towards the combustion chamber must therefore be made convergent.
1. A mixing screw for a fuel injector for a combustion chamber of a gas turbine, comprising:
a general shape of a hollow cylinder having a circumference divided into two sectors, a first sector and a second sector, the first sector including an angular network of feed holes for air traversing the cylinder as far as the hollow, and the second sector being solid and free of feed holes traversing the cylinder,
wherein the feed holes of the angular network are irregularly distributed over the first sector of the circumference of the cylinder, the first sector being less than a half of the circumference.
2. A fuel mixing screw according to claim 1 , wherein the first sector with said feed holes is less than a quarter-circle.
3. A fuel mixing screw according to claim 1 , wherein the feed holes are staggered in the cylinder's axial direction.
4. A fuel mixing screw according to claim 3 , wherein said first sector with said feed holes has three feed holes.
5. A fuel mixing screw according to claim 1 , wherein the feed holes have different inclinations in their angular directions.
6. A fuel mixing screw according to claim 1 , wherein the feed holes are at a relief angle, with increasing widths in their angular directions, moving in the outer radial direction.
7. A fuel mixing screw according to claim 1 , further comprising at least one other angular network of feed holes traversing the cylinder as far as the hollow, wherein the other angular network of feed holes is distributed over a circle, or over only a sector of a circle.
8. A fuel mixing screw according to claim 1 , wherein the cylinder covers said second sector of the circumference in addition to the first sector of the circumference over which the angular network of feed holes extends.
9. A fuel mixing screw according to claim 1 , wherein said second sector extends radially from said hollow to an exterior of said cylinder.
10. A fuel mixing screw according to claim 9 , wherein said second sector free of any feed holes is more than half of said circumference.
11. A fuel mixing screw according to claim 1 , wherein said second sector free of any feed holes is more than three quarters of said circumference.
12. A gas turbine combustion device, comprising:
an annular combustion chamber;
a group of fuel injectors leading to a base of the chamber and arranged in a circle; and
an air inlet device located before the combustion chamber, and including a propagation cone of greater radius than the chamber, and directed towards the combustion chamber,
wherein the fuel injectors include mixing screws having a general shape of a hollow cylinder having a circumference divided into two sectors, a first sector and a second sector, the first sector including an angular network of feed holes traversing the cylinder as far as the hollow, the second sector being solid and free of feed holes traversing the cylinder, and the feed holes of the angular network are irregularly distributed over the first sector of the circumference of the cylinder, the first sector being less than a half of the circumference, and the angular network of feed holes extends before a radially outer portion of the combustion chamber for each of the mixing screws.
13. A gas turbine combustion device according to claim 12 , wherein said second sector extends radially from said hollow to an exterior of said cylinder.
14. A gas turbine combustion device according to claim 13 , wherein said second sector free of any feed holes is more than half of said circumference.
15. A gas turbine combustion device according to claim 12 , wherein said second sector free of any feed holes is more than three quarters of said circumference.