Premixer assembly for mixing air and fuel for combustion
A premixer assembly for mixing air and fuel for combustion includes a plurality of tubes disposed at a head end of a combustor assembly. Also included is a tube of the plurality of tubes, the tube including an inlet end and an outlet end. Further included is at least one non-circular portion of the tube extending along a length of the tube, the at least one non-circular portion having a non-circular cross-section, and the tube having a substantially constant cross-sectional area along its length
1. A premixer assembly for mixing air and fuel for combustion comprising:
a plurality of tubes disposed at a head end of a combustor assembly;
a tube of the plurality of tubes, the tube having a longitudinal axis;
an inlet portion of the tube having a non-circular cross-section, the non-circular cross-section being perpendicular to the longitudinal axis at the inlet portion;
an outlet portion of the tube having a substantially circular cross-section, a cross-sectional area of the tube remaining substantially constant over an entire length of the tube, the cross-sectional area defined by a cross-section of the tube perpendicular to the longitudinal axis at the cross-section; and
at least one fuel injection aperture disposed at a fuel injection plane located between an inlet end of the tube and an outlet end of the tube, the non-circular cross-section being perpendicular to the longitudinal axis of the at least one non-circular portion of the tube.
2. The premixer assembly of claim 1 , wherein the non-circular cross-section extends to a location between the fuel injection plane and the outlet end.
3. The premixer assembly of claim 1 , wherein the non-circular cross-section includes a geometry comprising at least one of substantially oval, substantially triangular with fillets at an intersection of edges, substantially quadrilateral with fillets at an intersection of edges, and a pair of semi-circular ends connected by a pair of parallel walls.
4. The premixer assembly of claim 1 , wherein the non-circular cross-section includes a geometry comprising a substantially cardioid shape, wherein a cusp of the substantially cardioid shape comprises a fillet.
5. A gas turbine engine comprising:
a compressor section;
a turbine section; and
a combustor assembly comprising:
a plurality of tubes disposed proximate a head end of the combustor assembly and configured to mix air and fuel for combustion in a combustion region of the combustor assembly disposed downstream of the plurality of tubes;
a tube of the plurality of tubes including an inlet end and an outlet end;
at least one fuel injection aperture disposed at a fuel injection plane located between the inlet end and the outlet end of the tube;
a non-circular portion of the tube having a non-circular cross-section, the non-circular portion of the tube located at the fuel injection plane, the non-circular cross-section being perpendicular to a longitudinal axis of the non-circular portion of the tube; and
at least one circular portion of the tube having a circular cross-section, the at least one circular portion of the tube located proximate the outlet end of the tube, the circular cross-section being perpendicular to a longitudinal axis of the at least one circular portion of the tube, wherein a cross-sectional area of the tube remains substantially constant over an entire length of the tube.
6. A premixer assembly for mixing air and fuel for combustion comprising:
a plurality of tubes disposed at a head end of a combustor assembly;
a tube of the plurality of tubes, the tube including an inlet end, an outlet end, and a longitudinal axis;
at least one non-circular portion of the tube extending along a first length of the tube, the at least one non-circular portion of the tube comprising a first non-circular portion and a second non-circular portion, the first non-circular portion located proximate the inlet end of the tube and having a first non-circular cross-section, the second non-circular portion having a second non-circular cross-section distinct from the first non-circular cross-section, the first non-circular cross-section and the second non-circular cross-section being perpendicular to a longitudinal axis at the at least one non-circular portion of the tube; and
at least one circular portion of the tube extending along a second length of the tube, the at least one circular portion of the tube located proximate the outlet end of the tube, the at least one circular portion of the tube having a circular cross-section perpendicular to a longitudinal axis at the at least one circular portion of the tube, wherein a cross-sectional area of the tube remains substantially constant over an entire length of the tube.
7. The premixer assembly of claim 6 , further comprising at least one fuel injection aperture disposed at a fuel injection plane located between the inlet end and the outlet end of the tube.
8. The premixer assembly of claim 7 , wherein the second non-circular portion extends from a location between the inlet end and the fuel injection plane to a location between the fuel injection plane and the outlet end.
9. The premixer assembly of claim 6 , wherein the second non-circular portion is located upstream of the at least one circular portion proximate the outlet end of the tube.
10. The premixer assembly of claim 7 , wherein the second non-circular portion is located proximate the fuel injection plane.
11. The premixer assembly of claim 6 , wherein the non-circular cross-section comprises a geometry consisting of at least one of substantially oval, substantially triangular with fillets at an intersection of edges, substantially quadrilateral with fillets at an intersection of edges, and a pair of semi-circular ends connected by a pair of parallel walls.
12. The premixer assembly of claim 6 , wherein the non-circular cross-section has a substantially cardioid shape, wherein a cusp of the substantially cardioid shape comprises a fillet.