Turbine exhaust duct with probe interface
An exhaust system for an aircraft engine, has: a turbine exhaust duct (TED) having an annular inlet conduit extending around a central axis for directing combustion gases generally in an axial direction, and outlet conduits branching off from the annular inlet conduit; and an exhaust case surrounding the TED, the exhaust case being frustoconical and having outlet openings each communicating with a respective one of the outlet conduits, a probe opening extending through the exhaust case and bounded by a periphery, and a probe interface mounted to the periphery of the probe opening, the probe interface including an interfacing plate secured to the periphery of the probe opening and defining an aperture sized to receive a probe therethrough, the aperture located radially inwardly of the probe opening.
1 . An exhaust system for an aircraft engine, comprising:
a turbine exhaust duct (TED) having an annular inlet conduit extending around a central axis for directing combustion gases in an axial direction, and outlet conduits branching off from the annular inlet conduit; and
an exhaust case surrounding the TED, the exhaust case being frustoconical and having outlet openings each communicating with a respective one of the outlet conduits, a probe opening extending through the exhaust case and bounded by a periphery on an outer side of the exhaust case, and a probe interface mounted to the periphery of the probe opening, the probe interface including an interfacing plate secured to the periphery of the probe opening and defining an aperture sized to receive a probe therethrough, the aperture located radially inwardly of the probe opening.
2 . The exhaust system of claim 1 , wherein the interfacing plate includes:
a base defining the aperture; and
a flange extending peripherally around the base, the flange being secured to the periphery of the probe opening.
3 . The exhaust system of claim 2 , wherein a radial distance from the base to the central axis is constant along an axial length of the base.
4 . The exhaust system of claim 2 , wherein the flange has a first flange section extending transversally to the base and a second flange section extending transversally to the first flange section and parallel to the outer side of the exhaust case, the first flange section has a radial height relative to the central axis, the radial height increasing along an axial direction relative to the central axis.
5 . The exhaust system of claim 1 , further comprising a stiffener secured to the interfacing plate.
6 . The exhaust system of claim 5 , wherein the stiffener is secured to an inner side of the interfacing plate, the inner side facing the central axis.
7 . The exhaust system of claim 6 , wherein the stiffener has a U-shape and includes a flange contacting the inner side of the interfacing plate and a rib protruding transversally from the flange towards the central axis.
8 . The exhaust system of claim 6 , wherein the stiffener is secured to the interfacing plate via a braze joint or a weld joint.
9 . The exhaust system of claim 1 , wherein the probe opening extends axially up to a mounting flange of the exhaust case.
10 . The exhaust system of claim 1 , comprising a collar secured to the interfacing plate at the aperture, the collar sized to receive the probe therethrough.
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 outlet openings and having a probe opening extending through the exhaust case and bounded by a periphery on the outer side of the exhaust case;
a turbine exhaust duct (TED) surrounded by the exhaust case and having an annular inlet conduit extending around the central axis for directing combustion gases in an axial direction, and outlet conduits fluidly communicating with the annular inlet conduit and extending radially outward relative to the annular inlet conduit, each of the outlet conduits communicating with a respective one of the outlet openings of the outer case; and
a probe interface mounted to the periphery of the probe opening, the probe interface including an interfacing plate mounted to the periphery and having a portion being recessed radially inwardly relative to the exhaust case and defining an aperture sized to receive a probe therethrough.
12 . The reverse-flow gas turbine engine of claim 11 , wherein the portion is defined by a base of the interfacing plate, the interfacing plate further including a flange extending peripherally around the base, the flange being secured to the periphery of the probe opening.
13 . The reverse-flow gas turbine engine of claim 12 , wherein a radial distance from the base to the central axis is constant along an axial length of the base.
14 . The reverse-flow gas turbine engine of claim 12 , wherein the flange has a first flange section extending transversally to the base and a second flange section extending transversally to the first flange section and parallel to the outer side of the exhaust case, the first flange section has a radial height relative to the central axis, the radial height increasing along an axial direction relative to the central axis.
15 . The reverse-flow gas turbine engine of claim 11 , further comprising a stiffener secured to the interfacing plate.
16 . The reverse-flow gas turbine engine of claim 15 , wherein the stiffener is secured to an inner side of the interfacing plate, the inner side facing the central axis.
17 . The reverse-flow gas turbine engine of claim 16 , wherein the stiffener has a U-shape and includes a flange contacting the inner side of the interfacing plate and a rib protruding transversally from the flange towards the central axis.
18 . The reverse-flow gas turbine engine of claim 16 , wherein the stiffener is secured to the interfacing plate via a braze joint or a weld joint.
19 . The reverse-flow gas turbine engine of claim 11 , wherein the probe opening extends axially up to a mounting flange of the exhaust case.
20 . The reverse-flow gas turbine engine of claim 11 , comprising a collar secured to the interfacing plate at the aperture, the collar sized to receive the probe therethrough.