Distributed exhaust system
View Patent ↗An exhaust system includes a multiple of distribution risers which extend transverse to a plenum, each of the multiple of distribution risers includes at least one downstream directed aperture.
1. An exhaust system comprising:
a manifold including an arcuate shape, said arcuate shape having a radially outer wall, a radially inner wall, an upstream portion, a downstream portion, a first circumferential end, and a second circumferential end, wherein said radially inner wall and said radially outer wall at least partially define a cavity and said radially inner wall is in register with said radially outer wall to define said arcuate shape beginning at said first circumferential end and extending towards said second circumferential end; and
a multiple of distribution risers extending transversely from said radially outer wall of said manifold, each of said multiple of distribution risers are circumferentially spaced from an adjacent distribution riser and includes at least one downstream directed aperture directed toward said downstream portion, wherein each of said multiple of distribution risers includes a multiple of downstream directed apertures.
2. The exhaust system as recited in claim 1 , wherein each of said multiple of downstream directed apertures defines an approximately 180 degree arc around a perimeter of each of said multiple of distribution risers.
3. The exhaust system as recited in claim 1 , wherein each of said multiple of distribution risers are tubular.
4. The exhaust system as recited in claim 1 , wherein said manifold extends over an approximately 90 degree arc and said multiple of distribution risers are arranged on said manifold along said approximately 90 degree arc.
5. The exhaust system as recited in claim 1 , wherein said at least one downstream directed aperture defines an approximately 180 degree arc around a perimeter of each of said multiple of distribution risers.
6. The exhaust system as recited in claim 1 , wherein each of said multiple of distribution risers are arranged transverse to an airflow.
7. The exhaust system as recited in claim 1 , wherein said manifold is located radially inward relative to an axis of rotation of a propeller from a radiator and said radially outer wall of said manifold is circumferentially aligned with said radiator.
8. The exhaust system as recited in claim 1 , wherein a distal end of said multiple of distribution risers is sealed from fluid flow.
9. An engine comprising:
a manifold including an arcuate shape having a radially outer surface, wherein said arcuate shape extends from a first circumferential end towards a second circumferential end and defines a cavity there between; and
an exhaust system including a multiple of distribution risers extending transversely from said radially outer surface of said manifold, each of said multiple of distribution risers includes at least one downstream directed aperture directed toward a downstream portion, wherein said multiple of distribution risers are oriented in series extending in a direction from said first circumferential end towards side second circumferential end and said engine is a Wankel rotary engine.
10. The engine as recited in claim 9 , wherein said manifold extends over an approximately 90 degree arc and said multiple of distribution risers are arranged on said manifold along said approximately 90 degree arc.
11. The engine as recited in claim 9 , wherein said at least one downstream directed aperture defines an approximately 180 degree arc around a perimeter of each of said multiple of distribution risers.
12. The engine as recited in claim 9 , wherein said multiple of distribution risers are configured to be located downstream of an engine mounted radiator and upstream of a propeller.
13. The engine as recited in claim 9 , wherein said manifold is located radially inward relative to an axis of rotation of a propeller from an engine cowl, said engine cowl completely encircling an axis of rotation of said engine.
14. The engine of claim 9 , wherein said arcuate shape includes a radially outer wall, a radially inner wall, said first circumferential end, and said second circumferential end, wherein said radially inner wall and said radially outer wall at least partially define said cavity and said radially inner wall is in register with said radially outer wall to define said arcuate shape.
15. A pusher prop propulsion system comprising:
an engine defined along an axis of rotation of a propeller, wherein said engine is a pusher prop propulsion engine;
a manifold including an arcuate shape having a radially outer surface to receive cooling air of said engine, wherein the arcuate shape extends in a radial direction about said axis of rotation of said propeller; and
a multiple of distribution risers extending transversely from said radially outer surface of said manifold, each of said multiple of distribution risers includes at least one downstream directed aperture, wherein said multiple of distribution risers are located upstream of said propeller.
16. The pusher prop propulsion system as recited in claim 15 , wherein said engine is a Wankel rotary engine.
17. The pusher prop propulsion system as recited in claim 15 , further comprising an engine mounted radiator, said multiple of distribution risers adjacent to said radiator.
18. The pusher prop propulsion system as recited in claim 17 , wherein said engine mounted radiator is located radially outward from said manifold relative to said axis and is circumferentially aligned with said manifold.
19. The pusher prop propulsion system as recited in claim 15 , further comprising a fan on an upstream side of said propeller adjacent said manifold.
20. The pusher prop propulsion system as recited in claim 15 , wherein said manifold extends over an approximately 90 degree arc and said multiple of distribution risers are arranged on said manifold along said approximately 90 degree arc.
21. The pusher prop propulsion system as recited in claim 15 , wherein said multiple of distribution risers extend in a generally radial direction relative to said axis of rotation.
22. The pusher prop propulsion system as recited in claim 15 , wherein said propeller is configured to provide propulsion to an aircraft.