Turbine exhaust duct having shielding conduits
A turbine exhaust duct (TED) for an aircraft engine, has: an annular inlet conduit extending around a central axis for directing combustion gases generally in an axial direction; outlet conduits communicating with the inlet conduit and extending generally radially outward relative to the inlet conduit, the outlet conduits extending from inlet ends at intersections with the inlet conduit to outlet ends, the outlet conduits having transition areas transitioning from a mainly axial direction to a mainly radial direction; and shielding conduits received into the outlet conduits, the shielding conduits overlapping the transition areas of the outlet conduits.
1 . A turbine exhaust duct (TED) for an aircraft engine, comprising:
an annular inlet conduit extending around a central axis for directing combustion gases along a direction having an axial component;
outlet conduits communicating with the inlet conduit and extending away from the inlet conduit and from the central axis, the outlet conduits extending from inlet ends at intersections with the inlet conduit to outlet ends, the outlet conduits having transition areas upstream of the outlet ends relative to a flow of the combustion gases, the transition areas transitioning from a mainly axial direction to a mainly radial direction relative to the central axis and along the flow of the combustion gases; and
shielding conduits received into the outlet conduits, the shielding conduits overlapping the transition areas of the outlet conduits.
2 . The TED of claim 1 , comprising gaps defined between the shielding conduits and the outlet conduits, the gaps containing air.
3 . The TED of claim 2 , wherein the outlet conduits define recessed portions, the shielding conduits received into the recessed portions.
4 . The TED of claim 3 , wherein the shielding conduits extend from upstream ends to downstream ends along a direction of the combustion gases, the upstream ends of the shielding conduits secured to the outlet conduits.
5 . The TED of claim 4 , wherein the gaps are opened at the downstream ends.
6 . The TED of claim 1 , wherein the shielding conduits are made of a same material as that of the outlet conduits.
7 . The TED of claim 1 , wherein each of the shielding conduits extends annularly a full circumference but for a slot, the slot sized to allow contraction of a respective one of the shielding conduits during insertion inside a respective one of the outlet conduits.
8 . The TED of claim 7 , wherein the slot is located at a location being diametrically opposed to a respective one of the transition areas.
9 . 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 for receiving combustion gases, the turbine exhaust duct having:
an annular inlet conduit extending around the central axis; and
outlet conduits communicating with the inlet conduit and extending away from the inlet conduit and from the central axis, the outlet conduits extending from inlet ends at intersections with the inlet conduit to outlet ends, the outlet conduits having transition areas upstream of the outlet ends relative to a flow of the combustion gases, the transition areas transitioning from a mainly axial direction to a mainly radial direction relative to the central axis and along the flow of the combustion gases; and
shielding conduits received into the outlet conduits, the shielding conduits overlapping the transition areas of the outlet conduits.
10 . The reverse-flow gas turbine engine of claim 9 , comprising gaps defined between the shielding conduits and the outlet conduits, the gaps containing air.
11 . The reverse-flow gas turbine engine of claim 10 , wherein the outlet conduits define recessed portions, the shielding conduits received into the recessed portions.
12 . The reverse-flow gas turbine engine of claim 11 , wherein the shielding conduits extend from upstream ends to downstream ends along a direction of the combustion gases, the upstream ends of the shielding conduits secured to the outlet conduits.
13 . The reverse-flow gas turbine engine of claim 12 , wherein the gaps are opened at the downstream ends.
14 . The reverse-flow gas turbine engine of claim 9 , wherein the shielding conduits are made of a same material as that of the outlet conduits.
15 . The reverse-flow gas turbine engine of claim 9 , wherein each of the shielding conduits extends annularly a full circumference but for a slot, the slot sized to allow contraction of a respective one of the shielding conduits during insertion inside a respective one of the outlet conduits.
16 . The reverse-flow gas turbine engine of claim 15 , wherein the slot is located at a location being diametrically opposed to a respective one of the transition areas.