Turbine exhaust duct

1 . A turbine exhaust duct for a gas turbine engine, the turbine exhaust duct comprising:

an exhaust manifold that includes an annular inlet disposed at a first axial end of the exhaust manifold, a first exhaust port disposed on a first lateral side of the exhaust manifold, and a second exhaust port disposed on a second lateral side of the exhaust manifold;

an outer duct that includes a wall panel that extends axially between a first axial flange and a second axial flange, an axial end aperture disposed adjacent the first axial flange, a first lateral side aperture disposed in the wall panel, and a second lateral side aperture disposed in the wall panel;

a first connecting panel includes a first exhaust port connecting flange and a first lateral side outer duct flange, wherein the first exhaust port connecting flange is attached to the first exhaust port, and the first lateral side outer duct flange is attached to the outer duct wall panel;

a second connecting panel includes a second exhaust port connecting flange and a second lateral side outer duct flange, wherein the second exhaust port connecting flange is attached to the second exhaust port, and the second lateral side outer duct flange is attached to the outer duct wall panel;

at least one first stiffener panel (FSP) having a FSP periphery flange, wherein the FSP periphery flange is attached to the first connecting panel and to the outer duct wall panel; and

at least one second stiffener panel (SSP) having a SSP periphery flange, wherein the SSP periphery flange is attached to the first connecting panel and to the outer duct wall panel.

2 . The turbine exhaust duct of claim 1 , wherein the first exhaust port and the second exhaust port are disposed laterally opposite one another; and;

wherein the exhaust manifold is configured to direct gas flow received by the annular inlet into both the first exhaust port and the second exhaust port; and

wherein the annular inlet of the exhaust manifold is received within the axial end aperture, the first exhaust port is received within the first lateral side aperture, and the second exhaust port is received within the second lateral side aperture.

3 . The turbine exhaust duct of claim 1 , wherein the at least one first stiffener panel includes an upper first stiffener panel and a lower first stiffener panel, and the upper first stiffener panel and the lower first stiffener panel are disposed on opposite circumferential sides of the first exhaust port.

4 . The turbine exhaust duct of claim 3 , wherein the at least one second stiffener panel includes an upper second stiffener panel and a lower second stiffener panel, and the upper second stiffener panel and the lower second stiffener panel are disposed on opposite circumferential sides of the second exhaust port.

5 . The turbine exhaust duct of claim 1 , wherein the FSP periphery flange includes an axial segment, a side segment, and an exhaust port segment;

wherein the axial segment and the side segment are attached to the outer duct wall panel; and

wherein the exhaust port segment is attached to the first connecting panel.

6 . The turbine exhaust duct of claim 5 , wherein the axial segment and the side segment are disposed along a periphery of the at least one first stiffener panel.

7 . The turbine exhaust duct of claim 6 , wherein the at least one first stiffener panel further includes a fastener flange engaged with the second axial flange of the outer duct.

8 . The turbine exhaust duct of claim 6 , wherein the at least one first stiffener panel further includes a fastener flange engaged with the first axial flange of the outer duct.

9 . The turbine exhaust duct of claim 1 , wherein the FSP periphery flange includes an axial segment and an exhaust port segment, and the at least one first stiffener panel further includes a first fastener flange and a second fastener flange;

wherein the axial segment is attached to the outer duct wall panel; and

wherein the exhaust port segment is attached to the first connecting panel; and

wherein the first fastener flange is engaged with the first axial flange of the outer duct, and the second fastener flange is engaged with the second axial flange of the outer duct.

10 . The turbine exhaust duct of claim 1 , wherein the at least one first stiffener panel is configured such that an internal cavity is defined by the at least one first stiffener panel, the outer duct, and the first connecting panel.

11 . A turbine exhaust duct for a gas turbine engine, the turbine exhaust duct comprising:

an exhaust manifold that includes an annular inlet, a first exhaust port disposed on a first lateral side of the exhaust manifold, and a second exhaust port disposed on a second lateral side of the exhaust manifold;

an outer duct that includes a wall panel that extends axially between a first axial flange and a second axial flange, wherein the wall panel defines an interior compartment of the outer duct;

wherein the exhaust manifold is disposed within the interior compartment of the outer duct so that the first exhaust port extends laterally outward from a first lateral side of the outer duct and the second exhaust port extends laterally outward from a second lateral side of the outer duct;

a first connecting panel extending between and attached to the first exhaust port and the outer duct wall panel;

a second connecting panel extending between and attached to the second exhaust port and the outer duct wall panel;

at least one first stiffener panel (FSP) having a FSP periphery flange, wherein the FSP periphery flange is attached to the first connecting panel and to the outer duct wall panel; and

at least one second stiffener panel (SSP) having a SSP periphery flange, wherein the SSP periphery flange is attached to the first connecting panel and to the outer duct wall panel.

12 . The turbine exhaust duct of claim 11 , wherein the at least one first stiffener panel includes an upper first stiffener panel and a lower first stiffener panel, and the upper first stiffener panel and the lower first stiffener panel are disposed on opposite circumferential sides of the first exhaust port.

13 . The turbine exhaust duct of claim 12 , wherein the at least one second stiffener panel includes an upper second stiffener panel and a lower second stiffener panel, and the upper second stiffener panel and the lower second stiffener panel are disposed on opposite circumferential sides of the second exhaust port.

14 . The turbine exhaust duct of claim 13 , wherein the FSP periphery flange includes an axial segment, a side segment, and an exhaust port segment disposed along a periphery of the at least one first stiffener panel;

wherein the axial segment and the side segment are attached to the outer duct wall panel; and

wherein the exhaust port segment is attached to the first connecting panel.

15 . The turbine exhaust duct of claim 14 , wherein the at least one first stiffener panel further includes a fastener flange engaged with the second axial flange of the outer duct.

16 . The turbine exhaust duct of claim 14 , wherein the at least one first stiffener panel further includes a fastener flange engaged with the first axial flange of the outer duct.

17 . The turbine exhaust duct of claim 13 , wherein the FSP periphery flange includes an axial segment and an exhaust port segment, and the at least one first stiffener panel further includes a first fastener flange and a second fastener flange;

wherein the axial segment is attached to the outer duct wall panel; and

wherein the exhaust port segment is attached to the first connecting panel; and

wherein the first fastener flange is engaged with the first axial flange of the outer duct, and the second fastener flange is engaged with the second axial flange of the outer duct.

18 . The turbine exhaust duct of claim 13 , wherein the at least one first stiffener panel is configured such that an internal cavity is defined by the at least one first stiffener panel, the outer duct, and the first connecting panel.

19 . A gas turbine engine, comprising:

a compressor;

a combustor;

a turbine in communication with the compressor; and

a turbine exhaust duct disposed downstream of the turbine, the turbine exhaust duct comprising:

an exhaust manifold that includes an annular inlet, a first exhaust port disposed on a first lateral side of the exhaust manifold, and a second exhaust port disposed on a second lateral side of the exhaust manifold;

an outer duct that includes a wall panel that extends axially between a first axial flange and a second axial flange, wherein the wall panel defines an interior compartment of the outer duct;

wherein the exhaust manifold is disposed within the interior compartment of the outer duct so that the first exhaust port extends laterally outward from a first lateral side of the outer duct and the second exhaust port extends laterally outward from a second lateral side of the outer duct;

a first connecting panel extending between and attached to the first exhaust port and the outer duct wall panel;

a second connecting panel extending between and attached to the second exhaust port and the outer duct wall panel;

at least one first stiffener panel (FSP) having a FSP periphery flange, wherein the FSP periphery flange is attached to the first connecting panel and to the outer duct wall panel; and

at least one second stiffener panel (SSP) having a SSP periphery flange, wherein the SSP periphery flange is attached to the first connecting panel and to the outer duct wall panel.

20 . The gas turbine engine of claim 19 , wherein the at least one first stiffener panel includes an upper first stiffener panel and a lower first stiffener panel, and the upper first stiffener panel and the lower first stiffener panel are disposed on opposite circumferential sides of the first exhaust port; and

wherein the at least one second stiffener panel includes an upper second stiffener panel and a lower second stiffener panel, and the upper second stiffener panel and the lower second stiffener panel are disposed on opposite circumferential sides of the second exhaust port.