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An anti-icing exhaust system for an inlet of a gas turbine engine is provided. The system includes a first housing portion that at least partially defines a chamber to receive an anti-icing fluid and includes a projection. A second housing portion includes a leading edge. The system includes a suppo

An anti-icing exhaust system for an inlet of a gas turbine engine is provided. The system includes a first housing portion that at least partially defines a chamber to receive an anti-icing fluid and includes a projection. A second housing portion includes a leading edge. The system includes a support structure that couples the first housing portion to the second housing portion such that the projection of the first housing portion is spaced apart from the leading edge of the second housing portion to define a gap. The gap is in fluid communication with a manifold. The support structure defines at least one flow passage in fluid communication with the chamber and the manifold to exhaust the fluid. The system includes an insulation strip having a first end received in the gap and coupled to the leading edge; and a second end coupled to the second housing portion.

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1. An anti-icing exhaust system for an inlet of a gas turbine engine, comprising: a first housing portion associated with the inlet, the first housing portion at least partially defining a chamber to receive an anti-icing fluid from a source and including a projection;a second housing portion associ

1. An anti-icing exhaust system for an inlet of a gas turbine engine, comprising: a first housing portion associated with the inlet, the first housing portion at least partially defining a chamber to receive an anti-icing fluid from a source and including a projection;a second housing portion associated with the inlet, the second housing portion including a leading edge;a support structure that couples the first housing portion to the second housing portion such that the projection of the first housing portion is spaced apart from the leading edge of the second housing portion to define a gap between the first housing portion and the second housing portion, the gap in fluid communication with a manifold defined between the projection of the first housing portion and the support structure, and the support structure defines at least one flow passage in fluid communication with the chamber and the manifold to exhaust the anti-icing fluid from the chamber through the manifold and the gap; andan insulation strip having a first end and a second end, with the first end received in the gap and coupled to the leading edge and the second end coupled to the second housing portion. 2. The anti-icing exhaust system of claim 1, wherein the support structure includes a first end coupled to the first housing portion, a second end coupled to the second housing portion and an intermediate body portion, and the at least one flow passage is defined through the intermediate body portion. 3. The anti-icing exhaust system of claim 2, wherein the manifold is defined between the projection of the first housing portion, the intermediate body portion and the first end of the insulation strip. 4. The anti-icing exhaust system of claim 1, wherein the support structure includes a first end coupled to the first housing portion, a second end coupled to the second housing portion and an intermediate body portion that spans the gap, and the at least one flow passage is defined between adjacent ones of a plurality of spacers, the plurality of spacers coupled between the first end and the first housing portion. 5. The anti-icing exhaust system of claim 4, wherein the plurality of spacers comprise a plurality of washers coupled about each bore of a plurality of bores defined through the first end of the support structure, and the at least one flow passage is defined between adjacent ones of the plurality of washers. 6. The anti-icing exhaust system of claim 4, wherein the plurality of spacers comprise a plurality of shims coupled about at least two bores of a plurality of bores defined through the first end of the support structure and the at least one flow passage is defined between adjacent ones of the plurality of shims. 7. The anti-icing exhaust system of claim 1, wherein the support structure includes a first end having a plurality of mounting flanges, each one of the plurality of mounting flanges coupled to the first housing portion and a second end coupled to the second housing portion, and the at least one flow passage is defined between adjacent ones of the plurality of mounting flanges. 8. The anti-icing exhaust system of claim 1, wherein the first housing portion is an inlet lip, the second housing portion is an outer barrel of an inlet cowl section of a nacelle of the gas turbine engine and the insulation strip protects the leading edge of the second housing portion from the anti-icing fluid. 9. The anti-icing exhaust system of claim 1, wherein the projection of the first housing portion extends over the at least one flow passage such that the at least one flow passage is hidden from an exterior of a nacelle of the gas turbine engine by the projection. 10. The anti-icing exhaust system of claim 1, wherein the gap is defined to exhaust the anti-icing fluid in a radial direction into an environment surrounding the gas turbine engine. 11. The anti-icing exhaust system of claim 1, wherein the first housing portion and the second housing portion have an inboard side and an outboard side, and the at least one flow passage cooperates with the gap to exhaust the anti-icing fluid along the outboard side of the second housing portion. 12. The anti-icing exhaust system of claim 1, wherein the at least one flow passage comprises a plurality of flow passages defined about a perimeter of the support structure, and the gap extends continuously about the inlet to exhaust the anti-icing fluid from the plurality of flow passages about a circumference of the inlet. 13. An anti-icing exhaust system for an inlet of a gas turbine engine, comprising: an inlet lip at least partially defining a chamber to receive an anti-icing fluid from a source associated with the gas turbine engine and including a projection;an outer barrel having a leading edge;a support structure that couples the inlet lip to the outer barrel such that the projection of the inlet lip is spaced apart from the leading edge of the outer barrel to define a gap between the inlet lip and the outer barrel, the gap in fluid communication with a manifold defined between the projection of the inlet lip and the support structure, and the support structure defines at least one flow passage in fluid communication with the chamber and the manifold to exhaust the anti-icing fluid from the chamber through the manifold and the gap in a radial direction, and the projection of the inlet lip extends over the at least one flow passage; andan insulation strip having a first end and a second end, with the first end received in the gap and coupled to the leading edge to protect the leading edge from the anti-icing fluid and the second end coupled to the outer barrel. 14. The anti-icing exhaust system of claim 13, wherein the support structure includes a first end coupled to the inlet lip, a second end coupled to the outer barrel and an intermediate body portion, and the at least one flow passage is defined through the intermediate body portion. 15. The anti-icing exhaust system of claim 14, wherein the manifold is defined between the projection of the inlet lip, the intermediate body portion and the first end of the insulation strip. 16. The anti-icing exhaust system of claim 13, wherein the support structure includes a first end coupled to the inlet lip, a second end coupled to the outer barrel and an intermediate body portion that spans the gap, and the at least one flow passage is defined between adjacent ones of a plurality of spacers, the plurality of spacers coupled between the first end and the inlet lip. 17. The anti-icing exhaust system of claim 16, wherein the plurality of spacers comprise a plurality of washers coupled about each bore of a plurality of bores defined through the first end of the support structure, and the at least one flow passage is defined between adjacent ones of the plurality of washers. 18. The anti-icing exhaust system of claim 16, wherein the plurality of spacers comprise a plurality of shims coupled about at least two bores of a plurality of bores defined through the first end of the support structure and the at least one flow passage is defined between adjacent ones of the plurality of shims. 19. The anti-icing exhaust system of claim 13, wherein the support structure includes a first end having a plurality of mounting flanges, each one of the plurality of mounting flanges coupled to the inlet lip and a second end coupled to the outer barrel, and the at least one flow passage is defined between adjacent ones of the plurality of mounting flanges. 20. An anti-icing exhaust system for an inlet of a gas turbine engine, comprising: an inlet lip at least partially defining a chamber to receive an anti-icing fluid from a source associated with the gas turbine engine and including a projection;an outer barrel having a leading edge;a support structure having a first end coupled to the inlet lip, a second end coupled to the outer barrel and an intermediate body portion that spaces the projection of the inlet lip apart from the leading edge of the outer barrel to define a gap between the inlet lip and the outer barrel, the gap in fluid communication with a manifold defined between the projection of the inlet lip and the support structure, and the intermediate body portion defines a plurality of flow passages in fluid communication with the chamber and the manifold to exhaust the anti-icing fluid from the chamber through the manifold and the gap in a radial direction; andan insulation strip having a first end and a second end, with the first end received in the gap and coupled to the leading edge to protect the leading edge from the anti-icing fluid and the second end coupled to the outer barrel.