Low noise exhaust ducting system

Abstract

An exhaust duct system for a gas turbine engine that mounts within a tail cone of an aircraft, comprises an exhaust exit that exits one side of the tail cone offset from the axial centreline of the tail cone and an exhaust duct that couples the engine to the offset exhaust exit, with a straight section of the exhaust duct extending from the exhaust exit for a length that corresponds to at least one diameter of the exhaust duct.

Description

DESCRIPTION OF THE DRAWINGS

FIG. 1 is a cut-away top view of a prior art exhaust duct system for a gas turbine engine mounted in a tail section of an aircraft that has an exhaust exit that is along a centreline of a tail cone for the aircraft.

FIG. 2 is a cut-away top view of a prior art exhaust duct system for a gas turbine engine with an exhaust silencer mounted in a tail section of an aircraft that has an exhaust exit that is along a centreline of a tail cone for the aircraft.

FIG. 3 is a cut-away top view of a prior art exhaust duct system for a gas turbine engine mounted in a tail section of an aircraft that has an exhaust exit that is offset from a centreline of a tail cone for the aircraft.

FIG. 4 is a cut-away top view of a prior art exhaust duct system for a gas turbine engine with an exhaust silencer mounted in a tail section of an aircraft that has an exhaust exit that is offset from a centreline of a tail cone for the aircraft.

FIG. 5 is a cut-away top view of an exhaust duct system for a gas turbine engine mounted in a tail section of an aircraft according to a first possible embodiment of the invention that has a straight exhaust duct that couples the gas turbine engine to an exhaust exit that is offset from a centreline of a tail cone for the aircraft.

FIG. 6 is a cut-away top view of an exhaust duct system for a gas turbine engine with an exhaust silencer mounted in a tail section of an aircraft according to a second possible embodiment of the invention that has a straight exhaust duct that couples the gas turbine engine to exhaust exits that are offset from a centreline of a tail cone for the aircraft.

FIG. 7 is a cut-away top view of an exhaust duct system for a gas turbine engine mounted in a tail section of an aircraft according to a third embodiment the invention that has an exhaust duct that couples the gas turbine engine to an exhaust exit that is offset from a centreline of a tail cone for the aircraft with a bend in the exhaust duct upstream of a straight exhaust section that couples to the exhaust exit.

FIG. 8 is a cut-away top view of an exhaust duct system for a gas turbine engine with an exhaust silencer mounted in a tail section of an aircraft according to a fourth embodiment the invention that has an exhaust duct that couples the gas turbine engine to an exhaust exit that is offset from a centreline of a tail cone for the aircraft with a bend in the exhaust duct upstream of a straight exhaust section that couples to the exhaust exit.

FIG. 9 is a cut-away top view of an exhaust duct system for a gas turbine engine mounted in a tail section of an aircraft according to a fifth embodiment the invention that has an exhaust duct that couples the gas turbine engine to an exhaust exit that is offset from a centreline of a tail cone for the aircraft with a bend in the exhaust duct upstream of a straight exhaust section that couples to the exhaust exit.

FIG. 10 is a cut-away top view of an exhaust duct system for a gas turbine engine with an exhaust silencer mounted in a tail section of an aircraft according to a sixth embodiment the invention that has an exhaust duct that couples the gas turbine engine to an exhaust exit that is offset from a centreline of a tail cone for the aircraft with a bend in the exhaust duct upstream of a straight exhaust section that couples to the exhaust exit.

Claims

1. An exhaust duct system for a gas turbine engine that mounts within a tail cone of an aircraft, comprising: an exhaust exit that exits one side of the tail cone offset from the axial centreline of the tail cone; andan exhaust duct that couples the engine to the offset exhaust exit, with a straight section of the exhaust duct extending from the exhaust exit for a length that corresponds to at least one diameter of the exhaust duct.

2. The exhaust duct system of claim 1, wherein the straight section of the exhaust duct extends for a length that corresponds to at least three diameters of the exhaust duct.

3. The exhaust duct system of claim 1, wherein the entire length of the exhaust duct is generally straight.

4. The exhaust duct system of claim 3, wherein the gas turbine engine mounts at an angle with the axial centreline of the tail cone in line with the straight exhaust duct.

5. The exhaust duct system of claim 1, wherein the exhaust duct has a bend upstream of its straight section near the engine.

6. The exhaust duct system of claim 5, wherein the gas turbine engine mounts in general axial alignment with the axial centreline of the tail cone.

7. The exhaust duct system of claim 1, wherein the exhaust duct couples to the engine by way of an eductor.

8. The exhaust duct system of claim 1, wherein the exhaust duct couples directly to the engine with no eductor.

9. The exhaust duct system of claim 1, further comprising an exhaust silencer mounted along the straight section of the exhaust duct.

10. The exhaust duct system of claim 1, further comprising an aircraft tail cone that encases the exhaust duct system.

11. An exhaust duct system for a gas turbine engine that mounts within a tail cone of an aircraft, comprising: an exhaust exit that exits one side of the tail cone offset from the axial centreline of the tail cone; anda generally straight exhaust duct that couples the engine to the offset exhaust exit such that the engine mounts within the tail cone offset from the axial centreline of the tail cone.

12. The exhaust duct system of claim 11, wherein the exhaust duct couples to the engine by way of an eductor.

13. The exhaust duct system of claim 11, wherein the exhaust duct couples directly to the engine with no eductor.

14. An exhaust duct system for a gas turbine engine that mounts within a tail cone of an aircraft, comprising: an exhaust exit that exits one side of the tail cone offset from the axial centreline of the tail cone; andan exhaust duct that couples the engine to the offset exhaust exit, with a straight section of the exhaust duct extending from the exhaust exit for a length that corresponds to at least one diameter of the exhaust duct and a bend upstream of its straight section near the engine such that the engine mounts in general axial alignment with the axial centreline of the tail cone.

15. The exhaust duct system of claim 14, wherein the straight section of the exhaust duct extends for a length that corresponds to at least three diameters of the exhaust duct.

16. The exhaust duct system of claim 14, wherein the exhaust duct couples to the engine by way of an eductor.

17. The exhaust duct system of claim 14, wherein the exhaust duct couples directly to the engine with no eductor.

18. The exhaust duct system of claim 14, further comprising an aircraft tail cone that encases the exhaust duct system.

19. A gas turbine engine that mounts within a tail cone of an aircraft with an exhaust duct system comprising: an exhaust exit that exits one side of the tail cone offset from the axial centreline of the tail cone; andan exhaust duct that couples the engine to the offset exhaust exit, with a straight section of the exhaust duct extending from the exhaust exit for a length that corresponds to at least one diameter of the exhaust duct.

20. The gas turbine engine of claim 19, wherein the exhaust duct couples to the engine by way of an eductor.

21. The gas turbine engine of claim 19, wherein the exhaust duct couples directly to the engine with no eductor.

22. The gas turbine engine of claim 19, further comprising an exhaust silencer mounted along the straight section of the exhaust duct.

23. The gas turbine engine of claim 19, further comprising an aircraft tail cone that encases the exhaust duct system.