Patent ID: 11952962
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 6:
7. A propulsion system of an aircraft, comprising:
a gas turbine engine, including:
a combustor to combust a mixture of fuel and air; and
a turbine driven by a flow of combustion gases about an engine central axis; and
an exhaust nozzle to receive combustion gases from the turbine and exhaust the combustion gases; the exhaust nozzle including:
an annular inlet conduit extending along the engine central axis
at least two outlet conduits in flow communication with the inlet conduit, the at least two outlet conduits located non-parallel to the engine central axis;
wherein each of the at least two outlet conduits include an outlet port defining a distal end of each of the two outlet conduits; and
wherein at least one of the outlet ports is non-circular in cross-sectional shape;
wherein the at least one outlet port is elliptical in cross-sectional shape; and
wherein a major axis of the elliptical cross-sectional shape extends in a direction perpendicular to the engine central axis.