Combustor swirl vane apparatus

A combustor for a gas turbine engine, comprising:

• an annular inner liner;
• an annular outer liner spaced apart from the annular inner liner;
• a domed end disposed at an upstream end of the annular inner liner and the annular outer liner, the domed end including an annular dome;
• the annular dome including an annular array of swirler assemblies, each swirler assembly having a primary swirler and a secondary swirler disposed axially adjacent to each other along a swirler centerline;
• the primary swirler including a plurality of primary swirl vanes arrayed around the swirler centerline, each primary swirl vane includes opposed sides bounded between a forward edge and an aft edge and between a leading edge and a trailing edge;
• and
• the secondary swirler including a plurality of secondary swirl vanes arrayed around the swirler centerline, each secondary swirl vane including opposed sides bounded between a forward edge and an aft edge and between a leading edge and a trailing edge,
• wherein the forward edge of each secondary swirl vane is oriented at a first vane angle with respect to a radial direction, the aft edge is oriented at a second vane angle with respect to the radial direction, and the first vane angle is greater than the second vane angle, and
• wherein the forward edge of each primary swirl vane is oriented at a third vane angle with respect to the radial direction, the aft edge of each primary swirl vane is oriented at a fourth vane angle with respect to the radial direction, and the third vane angle is less than the fourth vane angle.