Exhaust diffuser for a gas turbine engine exhaust system

An exhaust system for a gas turbine engine, the exhaust system comprising:

• an exhaust diffuser including
• a diffuser inlet,
• a diffuser exit,
• an inner diffuser wall extending between the diffuser inlet and the diffuser exit, the inner diffuser wall defining a surface of revolution with a first flared downstream portion about a diffuser axis, and
• an outer diffuser wall extending between the diffuser inlet and the diffuser exit, the outer diffuser wall defining a truncated surface of revolution with a second flared downstream portion about the diffuser axis, the second flared downstream portion obliquely truncated proximate the diffuser exit and relative to a plane normal to the diffuser axis, the second flared downstream portion including a maximum cutback, the inner diffuser wall and the outer diffuser wall forming a diffusing flowpath between the diffuser inlet and the diffuser exit;
• and
• an exhaust collector including
• an exhaust collector exit configured to discharge exhaust gas along a discharge direction, the exhaust collector exit located substantially opposite from the maximum cutback, relative to the diffuser axis and along the discharge direction,
• a forward wall,
• an aft wall, and
• a circumferential wall extending between the forward wall and the aft wall, the circumferential wall encircling a majority of the diffuser exit.

An exhaust system for a gas turbine engine, the gas turbine engine having a center axis and a turbine, the exhaust system comprising:

• an exhaust diffuser including a diffuser inlet, a diffuser exit, an inner diffuser wall, and an outer diffuser wall, the inner diffuser wall, and the outer diffuser wall extending between the diffuser inlet and the diffuser exit and forming a diffusing flowpath therebetween, the diffuser inlet configured to axially receive exhaust gas from the turbine, the diffuser exit configured to radially discharge the exhaust gas,
• the inner diffuser wall including a first surface of revolution about the center axis, the first surface of revolution including a first conic region and a first flared downstream portion, the first flared downstream portion including a first flare radius,
• the outer diffuser wall including a second surface of revolution about the center axis, the second surface of revolution including a second conic region and a second flared downstream portion, the second flared downstream portion including a second flare radius and an cutback portion with a maximum cutback located substantially radially opposite from the exhaust collector exit;
• and
• an exhaust collector including an exhaust collector exit, a forward wall, a circumferential wall, and an aft wall, the circumferential wall extending between the forward wall and the aft wall, the exhaust collector configured to receive the exhaust gas circumferentially about the center axis from the diffuser exit, the exhaust collector exit configured to discharge the exhaust gas in a discharge direction radially between positive 135 degrees and negative 135 degrees around the center axis from top dead center, the discharge direction substantially radially opposite from the maximum cutback, relative to the center axis.