Exhaust duct for gas turbine engine

Patent metadata

Field	Value
Publication number	US-12372044-B2
Application number	US-202418593232-A
Country	US
Kind code	B2
Filing date	Mar 1, 2024
Priority date	Jan 31, 2023
Publication date	Jul 29, 2025
Grant date	Jul 29, 2025

Abstract

An exhaust duct of an aircraft engine includes 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 are located non-parallel to the inlet central axis. Each of the at least two outlet conduits include an outlet port defining a distal end of each of the two outlet conduits. At least one of the outlet ports is non-circular in cross-sectional shape.

First claim

What is claimed is:

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.

Assignees

• Pratt & Whitney Canada

Inventors

• Akcayoz Eray
• Cunningham Mark

Classifications

• F05D2250/51

  Inlet · CPC title

• F05D2250/73

  asymmetric · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2250/71

  curved · CPC title

• F05D2250/52

  Outlet · CPC title