Reflex annular vent nozzle
A gas turbine engine includes a core defining an engine central longitudinal axis. An inner-fixed structure is radially outward of the core. A core cowl extends from the inner-fixed structure to a trailing edge. A thrust reverser is spaced radially outward of the core cowl to define a fan flow path. A vent has a core cowl inner surface formed as part of the core cowl and a vent inner surface that is spaced radially inward of the core cowl inner surface to define a vent flow path. A reflex member extends from a trailing edge of the core nacelle to impede mixing of the fan flow path and the vent flow path.
1. A nacelle assembly for a gas turbine engine comprising:
a core defining an engine central longitudinal axis;
an inner-fixed structure radially outward of the core and having a core cowl that extends from the inner-fixed structure to a trailing edge;
a thrust reverser spaced radially outward of the inner-fixed structure to define a fan flow path;
a vent having a core cowl internal surface formed as part of the core cowl and a vent inner surface spaced radially inward of the core cowl internal surface to define a vent flow path; and
a reflex member extending from the trailing edge to impede mixing of the fan flow path and the vent flow path, wherein the reflex member includes a curved portion that is formed as part of a radially outer surface of the reflex member.
2. The nacelle assembly for the gas turbine engine according to claim 1 , wherein the vent inner surface has a portion that converges toward the reflex member to define a vent height.
3. The nacelle assembly for the gas turbine engine according to claim 2 , wherein the reflex member extends from a fore edge fixed to the trailing edge to an aft edge that defines the vent height, and wherein a portion of the reflex member that is between the fore and aft edges extends radially inwardly toward the engine central longitudinal axis.
4. The nacelle assembly for the gas turbine engine according to claim 1 , wherein vent air flow is extracted from the fan flow path into a vent plenum within the inner-fixed structure.
5. The nacelle assembly for the gas turbine engine according to claim 4 , wherein a core inner nozzle surface is spaced radially inwardly of an inner peripheral surface of the core cowl to define a portion of a core flow path that is radially inward of the vent air flow.
6. The nacelle assembly for the gas turbine engine according to claim 1 , wherein the radially outer surface includes a concave surface portion.
7. A nacelle assembly for the gas turbine engine comprising:
a core defining an engine central longitudinal axis;
an inner-fixed structure radially outward of the core and having a core cowl that extends from the inner-fixed structure to a trailing edge;
a thrust reverser spaced radially outward of the inner-fixed structure to define a fan flow path;
a vent having a core cowl internal surface formed as part of the core cowl and a vent inner surface spaced radially inward of the core cowl internal surface to define a vent flow path; and
a reflex member extending from the trailing edge to impede mixing of the fan flow path and the vent flow path, wherein the reflex member includes a curved portion, and wherein the reflex member comprises an annular strip that is fixed to the trailing edge.
8. The nacelle assembly for the gas turbine engine according to claim 7 , wherein the annular strip is comprised of a rigid material.
9. A nacelle assembly for a gas turbine engine comprising:
a core defining an engine central longitudinal axis;
an inner-fixed structure radially outward of the core and having a core cowl that extends from the inner-fixed structure to a trailing edge;
a thrust reverser spaced radially outward of the inner-fixed structure to define a fan flow path;
a vent having a core cowl internal surface formed as part of the core cowl and a vent inner surface spaced radially inward of the core cowl internal surface to define a vent flow path; and
a reflex member extending from the trailing edge to impede mixing of the fan flow path and the vent flow path, and wherein the reflex member comprises a reflex inner surface that faces the vent inner surface and a reflex outer surface that faces opposite the reflex inner surface, and wherein the reflex outer surface comprises a concave surface.
10. A nacelle assembly for the gas turbine engine comprising:
a core defining an engine central longitudinal axis;
an inner-fixed structure radially outward of the core and having a core cowl that extends from the inner-fixed structure to a trailing edge;
a thrust reverser spaced radially outward of the inner-fixed structure to define a fan flow path;
a vent having a core cowl internal surface formed as part of the core cowl and a vent inner surface spaced radially inward of the core cowl internal surface to define a vent flow path; and
a reflex member extending from the trailing edge to impede mixing of the fan flow path and the vent flow path, wherein the reflex member includes a curved portion, and wherein the reflex member has a curved profile extending from a fore edge of the reflex member to an aft edge of the reflex member.
11. The nacelle assembly for the gas turbine engine according to claim 10 , wherein the curved profile includes the curved portion that extends radially inwardly toward the vent inner surface.
12. The nacelle assembly for the gas turbine engine according to claim 11 , wherein the vent inner surface has a portion that converges toward the reflex member to define a vent height.
13. The nacelle assembly for the gas turbine engine according to claim 12 , wherein the vent height is less than about 0.50 inches (1.27 cm).
14. A nacelle assembly for the gas turbine engine comprising:
a core defining an engine central longitudinal axis;
an inner-fixed structure radially outward of the core and having a core cowl that extends from the inner-fixed structure to a trailing edge;
a thrust reverser spaced radially outward of the inner-fixed structure to define a fan flow path;
a vent having a core cowl internal surface formed as part of the core cowl and a vent inner surface spaced radially inward of the core cowl internal surface to define a vent flow path; and
a reflex member extending from the trailing edge to impede mixing of the fan flow path and the vent flow path, wherein the reflex member includes a curved portion, and wherein the vent inner surface has a portion that converges toward the reflex member to define a vent height, and, wherein the reflex member extends from a fore edge fixed to the trailing edge to an aft edge that defines the vent height, and wherein a portion of the reflex member that is between the fore and aft edges extends radially inwardly toward the engine central longitudinal axis, and wherein the reflex member is integrally formed as one piece with the core cowl.
15. A gas turbine engine comprising:
a core defining an engine central longitudinal axis;
an inner-fixed structure radially outward of the core;
a fan having a thrust reverser unit spaced radially outward of the inner-fixed structure to define a fan flow path;
a first shaft rotatable about the engine central longitudinal axis and connected to the fan;
a first compressor and a first turbine section interconnected by the first shaft;
a second shaft spaced radially outwardly of the first shaft and rotatable about the engine central longitudinal axis;
a second compressor and a second turbine section interconnected by the second shaft;
a core cowl that extends from the inner-fixed structure to a trailing edge, an inner peripheral surface of a core OML being spaced radially outward of a core nozzle inner surface to define a core flow path;
a vent having a core cowl internal surface formed as part of the core cowl and a vent inner surface spaced radially inward of the core cowl internal surface to define a vent flow path; and
a reflex member extending from the trailing edge to impede mixing of the fan flow path and the vent flow path, and wherein the reflex member has a curved profile extending from a fore edge of the reflex member to an aft edge of the reflex member, and wherein the curved profile has a portion that extends radially inwardly toward the vent inner surface.
16. The gas turbine engine according to claim 15 , wherein the first shaft is connected to the fan through a geared architecture.
17. The gas turbine engine according to claim 15 , wherein the reflex member is integrally formed as one piece with the core cowl.
18. A gas turbine engine comprising:
a core defining an engine central longitudinal axis;
an inner-fixed structure radially outward of the core;
a fan having a thrust reverser unit spaced radially outward of the inner-fixed structure to define a fan flow path;
a first shaft rotatable about the engine central longitudinal axis and connected to the fan through a geared architecture;
a first compressor and a first turbine section interconnected by the first shaft;
a second shaft spaced radially outwardly of the first shaft and rotatable about the engine central longitudinal axis;
a second compressor and a second turbine section interconnected by the second shaft;
a core cowl that extends from the inner-fixed structure to a trailing edge, an inner peripheral surface of a core OML being spaced radially outward of a core nozzle inner surface to define a core flow path;
a vent having a core cowl internal surface formed as part of the core cowl and a vent inner surface spaced radially inward of the core cowl internal surface to define a vent flow path; and
a reflex member extending from the trailing edge to impede mixing of the fan flow path and the vent flow path, and wherein the reflex member comprises an annular strip that is fixed to extend aft of the trailing edge.
19. The gas turbine engine according to claim 18 , wherein the reflex member extends from a fore edge fixed to the trailing edge en an aft edge, and wherein the reflex member defines a vent height relative to the vent inner surface.
20. The gas turbine engine according to claim 19 , wherein a portion of the reflex member that is between the fore and aft edges extends radially inwardly toward the engine central longitudinal axis.
21. The gas turbine engine according to claim 20 , wherein the vent inner surface includes a portion that converges toward the reflex member to define the vent height.
22. The gas turbine engine according to claim 21 , wherein the vent height is less than about 0.50 inches (1.27 cm).
23. A nacelle assembly for the gas turbine engine comprising:
a core defining an engine central longitudinal axis;
an inner-fixed structure radially outward of the core and having a core cowl that extends from the inner-fixed structure to a trailing edge;
a thrust reverser spaced radially outward of the inner-fixed structure to define a fan flow path;
a vent having a core cowl internal surface formed as part of the core cowl and a vent inner surface spaced radially inward of the core cowl internal surface to define a vent flow path; and
a reflex member extending from the trailing edge to impede mixing of the fan flow path and the vent flow path, wherein the reflex member includes a curved portion, and wherein an aft edge of the reflex member extends in a direction away from the engine central longitudinal axis.