Granted Patent B2

US 12,742,401 · App. 18/987,175 · Granted Sep 22, 2026

Inventors: Guy Lefebvre (St-Bruno-de-Montarville, CA); Francois Doyon (Ste-Julie, CA)

Assignee: PRATT & WHITNEY CANADA CORP.

F01D25/30F01D9/06F01D25/24F05D2220/323F05D2240/12F05D2240/14F05D2260/60

Abstract

Claims (27)

1 . A turbine exhaust duct (TED) for an aircraft engine, comprising:

an annular inlet conduit extending around a central axis for directing combustion gases generally in an axial direction;

outlet conduits communicating with the annular inlet conduit and extending generally radially outward relative to the annular inlet conduit, the outlet conduits extending from inlet ends at intersections with the annular inlet conduit to outlet ends, an outlet conduit of the outlet conduits surrounding a flow passage for receiving the combustion gases from the annular inlet conduit, the outlet conduit having a conduit axis being transverse to the central axis, the outlet conduit having:

a forward section facing an axially forward direction and a rearward section opposite the forward section, the forward section and the rearward section conjointly defining an outlet end of the outlet ends; and

a reinforcement plate secured to the forward section, the reinforcement plate having a thickness greater than a baseline thickness of the outlet conduit outside the reinforcement plate, the reinforcement plate having an inner face facing the flow passage and being exposed to the combustion gases, the inner face oriented radially towards the conduit axis.

2 . The TED of claim 1 , wherein the reinforcement plate is received within a cut-out defined in the outlet conduit.

3 . The TED of claim 2 , wherein the cut-out has a cut-out edge and the reinforcement plate has a peripheral edge bonded to the cut-out edge.

4 . The TED of claim 3 , wherein a weld joint is located at an intersection between the cut-out edge and the peripheral edge of the reinforcement plate.

5 . The TED of claim 4 , wherein the reinforcement plate is devoid of weld joint but for at the peripheral edge.

6 . The TED of claim 1 , wherein the reinforcement plate overlaps a high-stress area of the outlet conduit.

7 . The TED of claim 1 , wherein the outlet conduit defines an outlet edge, an annular member being mounted to the outlet edge and extending a full periphery of the outlet end, the outlet end defined by the annular member, the annular member having a thickness greater than the baseline thickness.

8 . The TED of claim 7 , wherein the reinforcement plate and the annular member are joined via a weld joint.

9 . The TED of claim 1 , wherein a ratio of the thickness of the reinforcement plate to the baseline thickness is greater than 1.

10 . The TED of claim 1 , further comprising exhaust rings mounted to the outlet ends of the outlet conduits, the exhaust rings having peripheral flanges securable to a case of the aircraft engine.

11 . A reverse-flow gas turbine engine, comprising:

an outer case assembly extending around a central axis and enclosing a core, the core including a compressor section, a combustor, and a turbine section, the turbine section located forward of the combustor and of the compressor section relative to a direction of travel of the reverse-flow gas turbine engine, the outer case assembly including an exhaust case defining openings;

a turbine exhaust duct fluidly communicating with the turbine section, the turbine exhaust duct having:

an annular inlet conduit extending around the central axis;

outlet conduits communicating with the annular inlet conduit and extending through the openings of the exhaust case, the outlet conduits extending from inlet ends at intersections with the annular inlet conduit to outlet ends, an outlet conduit of the outlet conduits having a redirecting section that curves from a substantially axial orientation to a substantially radial orientation, the outlet conduit having a conduit axis, the redirecting section configured to be impinged by combustion gases exiting the turbine section and to divert the combustion gases radially outwardly, the redirecting section having a thickness greater than a baseline thickness of the outlet conduit outside the redirecting section, the redirecting section defining part of a flow passage of the outlet conduit, the redirecting section having an inner face facing the flow passage and being exposed to the combustion gases, the Inner face facing the conduit axis.

12 . The reverse-flow gas turbine engine of claim 11 , wherein the redirecting section is at least partially defined by a reinforcement plate received within a cut-out defined in the outlet conduit.

13 . The reverse-flow gas turbine engine of claim 12 , wherein the cut-out has a cut-out edge and the reinforcement plate has a peripheral edge bonded to the cut-out edge.

14 . The reverse-flow gas turbine engine of claim 13 , wherein a weld joint is located at an intersection between the cut-out edge and the peripheral edge of the reinforcement plate.

15 . The reverse-flow gas turbine engine of claim 14 , wherein the reinforcement plate is devoid of weld joint.

16 . The reverse-flow gas turbine engine of claim 11 , wherein the redirecting section overlaps a high-stress area of the outlet conduit.

17 . The reverse-flow gas turbine engine of claim 11 , wherein the outlet conduit defines an outlet edge, an annular member being mounted to the outlet edge and extending a full periphery of the outlet end, the outlet end defined by the annular member, the annular member having a thickness greater than the baseline thickness.

18 . The reverse-flow gas turbine engine of claim 17 , wherein a reinforcement plate defines the redirection section, the reinforcement plate and the annular member are joined via a weld joint.

19 . The reverse-flow gas turbine engine of claim 11 , wherein a ratio of the thickness to the baseline thickness being greater than 1.

Assignments (1)

Continuity (1)

References Cited (28)