Granted Patent B2

US 12,372,044 · App. 18/593,232 · Granted Jul 29, 2025

Inventors: Eray Akcayoz (Cote-Saint-Luc, CA); Mark Cunningham (Montreal-Ouest, CA)

Assignee: PRATT & WHITNEY CANADA CORP.

F02K1/40F05D2220/323F05D2250/51F05D2250/52F05D2250/71F05D2250/73

Abstract

Claims (28)

1. An exhaust duct of an aircraft engine, comprising:

an annular inlet conduit having an inlet central axis; and

at least two outlet conduits in flow communication with the inlet conduit, the at least two outlet conduits located non-parallel to the inlet 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;

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 parallel to the inlet central axis.

2. The exhaust duct of claim 1 , wherein an aspect ratio of the major axis to a minor axis of the elliptical cross-sectional shape is between 1 and 2.

3. The exhaust duct of claim 1 , wherein each of the outlet conduits extend curvilinearly from an intersection of the outlet conduits and the inlet conduit.

4. The exhaust duct of claim 1 , wherein the inlet conduit includes a central bore to accommodate a shaft of the aircraft engine therein.

5. The exhaust duct of claim 1 , wherein the at least two outlet conduits are two outlet conduits located 180 degrees apart relative to the inlet central axis.

6. 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;

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 parallel to the engine central axis.

7. The propulsion system of claim 6 , wherein an aspect ratio of the major axis to a minor axis of the elliptical cross-sectional shape is between 1 and 2.

8. The propulsion system of claim 6 , wherein each of the outlet conduits extend curvilinearly from an intersection of the outlet conduits and the inlet conduit.

9. The propulsion system of claim 6 , wherein the inlet conduit includes a central bore to accommodate a shaft of the gas turbine engine therein.

10. The propulsion system of claim 9 , wherein the shaft drives a propeller of the aircraft.

11. The propulsion system of claim 10 , wherein the exhaust duct is located between the propeller and the turbine, relative to the engine central axis.

12. The exhaust duct of claim 6 , wherein the at least two outlet conduits are two outlet conduits located 180 degrees apart relative to the engine central axis.

Assignments (1)

Continuity (2)

References Cited (29)