Static take-off port

1. A duct for a gas turbine engine, the duct with a wall defining a flow passage for an airflow, the wall defining a baseline surface, the duct comprising an off-take port for drawing a portion of the airflow out of the duct, the off-take port including a projected portion projecting away from the baseline surface into the flow passage, a conduit opening defined within the projected portion for receiving the portion of the airflow, and an off-take conduit communicating with the conduit opening for directing the portion of the airflow away from the duct, the projected portion having a hump upstream of the conduit opening relative to a direction of the airflow, an apex of the hump located upstream of the conduit opening, and a scoop downstream of the conduit opening relative to the direction of the airflow, the scoop projecting into the duct beyond the hump.

2. The duct of claim 1 , wherein the projected portion further includes a fairing extending downstream from the scoop in the direction of the airflow.

3. The duct of claim 1 , wherein a distance in a direction transverse to the baseline surface and extending between the projected portion at the hump and the baseline surface increases continuously from an upstream end of the projected portion to the apex of the hump.

4. The duct of claim 3 , wherein the apex is located within a plane containing a central axis of the off-take conduit, the plane being parallel to the direction of the airflow.

5. The duct of claim 1 , wherein the hump defines an apex line, the apex being one of a plurality of local apexes circumferentially distributed around the conduit opening on the apex line, a central one of the plurality of local apexes located within a plane containing a central axis of the off-take conduit, the plane being parallel to the direction of the airflow.

6. The duct of claim 5 , wherein a distance between the baseline surface and the plurality of local apexes decreases away from the central one of the plurality of local apexes.

7. The duct of claim 1 , wherein the projected portion is tangent to a remainder of the wall.

8. The duct of claim 1 , wherein an upstream end of the scoop defines a leading edge.

9. The duct of claim 1 , wherein the hump is a single hump.

10. The duct of claim 1 , wherein first and second derivatives of the projected portion at an intersection between the projected portion and a remainder of the wall equal first and second derivatives of the remainder of the wall at the intersection.

11. A duct for a gas turbine engine, the duct having a wall defining a boundary of an airflow flowing through the duct, the wall defining a baseline surface, the duct comprising an off-take port for drawing a portion of the airflow out of the duct, the off-take port including: a conduit opening; an off-take conduit communicating with the conduit opening for directing the portion of the airflow away from the duct; an upstream surface of the wall of the duct defining a hump located upstream of the conduit opening relative to a direction of the airflow, an apex of the hump located upstream of the conduit opening; and a downstream surface of the wall of the duct defining a scoop located downstream of the conduit opening relative to the direction of the airflow, the hump and the scoop protruding away from the baseline surface into a passage of the duct, the scoop projecting into the duct beyond the hump.

12. The duct of claim 11 , wherein the downstream surface further has a fairing downstream of the conduit opening, the fairing extending from the scoop in the direction of the airflow.

13. The duct of claim 11 , wherein a distance in a direction transverse to the baseline surface and extending between the upstream surface of the wall of the duct at the hump and the baseline surface increases continuously toward the apex of the hump.

14. The duct of claim 13 , wherein the apex is located within a plane containing a central axis of the off-take conduit, the plane being parallel to the direction of the airflow.

15. The duct of claim 11 , wherein the hump defines an apex line, the apex being one of a plurality of local apexes circumferentially distributed around an upstream half of the conduit opening on the apex line, a central one of the plurality of local apexes located within a plane containing a central axis of the off-take conduit, the plane being parallel to the direction of the airflow.

16. The duct of claim 11 , wherein the upstream surface and the downstream surface are tangent to the baseline surface.

17. The duct of claim 11 , wherein an upstream end of the scoop defines a leading edge.

18. The duct of claim 11 , wherein the hump is a single hump.

19. A method of withdrawing an extracted airflow from an airflow within a duct of a gas turbine engine, the duct having a wall defining a baseline surface, the method comprising: using a hump of a projected portion of the wall to deflect a portion of the airflow away from the baseline surface and to turn said portion of the airflow toward a conduit opening in the wall, the hump located upstream of the conduit opening and having an apex located upstream of the conduit opening, and separating the extracted airflow from said portion of the airflow using a scoop of the projected portion, the scoop located downstream of the conduit opening and projecting into the duct beyond the hump, and directing the extracted airflow into an off-take conduit, the off-take conduit in communication with the conduit opening and extending away from the wall of the duct.

20. The method of claim 19 , further comprising reattaching a remainder of said portion of the airflow using a fairing of the projected portion extending downstream from the scoop.