Translating outer cowl flow modulation device and method
A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.
1. A method for modifying exhaust flow of a gas turbine engine, the method comprising:
providing a core flow path, wherein the core flow path is defined by a core flow path liner;
providing a bypass flow path radially offset from the core flow path, wherein the bypass flow path is defined between the core flow path liner and an inner liner containing a first axially extending flow control surface opposite the bypass flow path;
providing a third stream flow path radially offset from the core flow path and the bypass flow path wherein the third streamflow path is defined by:
the first axially extending flow control surface having a first upstream end and a first downstream end;
a second axially extending flow control surface having a second upstream end and a second downstream end, the second axially extending flow control surface radially offset from the first axially extending flow control surface wherein the second downstream end of the second axially extending flow control surface is upstream of the first downstream end of the first axially extending flow control surface; and
a third axially extending flow control surface comprising a third upstream end and a third downstream end, wherein the third upstream end is downstream of the first upstream end of the first axially extending flow control surface, the third axially extending surface is sealingly engaged with and extending from the second axially extending flow control surface at the third upstream end of the third axially extending flow control surface and the second downstream end of the second axially extending flow control surface;
delivering an airflow to an annular movable cowl with a fan; and
adjusting the annular movable cowl within the third stream flow path between an upstream closed position and a downstream fully open position for dynamically regulating the airflow within the third stream flow path, wherein positioning of the annular movable cowl determines an amount of the airflow through the third stream flow path and along an outer portion of an exhaust nozzle and an amount of flow through the core flow path and wherein the annular moveable cowl dynamically selectively allows closing of the third stream flow path to prevent the airflow by translating the third axially extending flow control surface, the third axially extending flow control surface translatable between the upstream closed position where the downstream end of the third axially extending flow control surface contacts the first axially extending flow control surface, and the downstream fully open position where the downstream end of the third axially extending flow control surface is spaced from the downstream end of the first axially extending flow control surface.
2. The method of claim 1 , wherein moving the annular movable cowl upstream increases the amount of the flow through the core flow path.
3. The method of claim 2 , wherein moving the annular movable cowl downstream increases the airflow through the third stream flow path.
4. The method of claim 1 , wherein the airflow through the third stream flow path produces thrust.
5. The method of claim 1 , wherein the airflow through the third stream flow path reduces afterbody drag.
6. The method of claim 1 , wherein the core flow path is located centrally in the gas turbine engine.
7. The method of claim 1 , wherein the bypass flow path is located circumferentially outward from the core flow path.
8. The method of claim 1 , wherein the third stream flow path is located circumferentially outward from the bypass flow path.
9. The method of claim 1 , wherein adjusting the annular moveable cowl comprises actuating one or more actuators located circumferentially around the annular moveable cowl for controlling movement of the annular moveable cowl.
10. The method of claim 1 , wherein the third stream flow path is axisymmetric.
11. The method of claim 1 , wherein the first axially extending flow control surface comprises a convex portion that is convex relative to the third stream flow path, and the third axially extending flow control surface comprises a concave portion that is concave relative to the third stream flow path.
12. The method of claim 11 , wherein the convex portion of the first axially extending flow control surface and the concave portion of the third axially extending flow control surface have substantially complementary shapes.
13. The method of claim 12 , wherein the convex portion of the first axially extending flow control surface and the concave portion of the third axially extending flow control surface are shaped so that the third stream flow path converges at a first location and diverges at a second location downstream from the first location.