And manufacture of generalized flow profile-producing devices
The present invention provides a process for making a flow conditioning device that transforms an input flow into a desired output flow. The process includes the steps of inputting into a computer program a set of design constraints representative of the input flow and the output flow. The computer program generates a design representative of a flow-conditioning device that transforms the input flow into the output flow. The process then provides the output design to an additive manufacturing or other suitable production system adapted to form a solid representation of the flow-conditioning device.
1. A process for making a fluid flow guide vane that transforms an input flow into a desired output flow in a flow field of an aircraft, the process comprising the steps of:
obtaining an array of desired velocity vectors within a desired flow profile at an aerodynamic interface plane (AIP) of the flow field;
creating lines on a plot representing lines parallel to said desired flow profile based, at least in part, upon the array of desired velocity vectors;
creating vane lines on said plot represented by lines perpendicular to said parallel lines;
querying an input vector field to determine a turning angle that transforms said input flow into said desired output flow along the vane lines;
using said turning angle to determine a vane geometry that transforms said input flow into an output flow at said vane lines, wherein said vane geometry is outputted to a manufacturing system adapted to form a solid representation of the vane geometry;
manufacturing the fluid flow guide vane comprising the solid representation of the vane geometry, wherein the fabrication of the fluid flow guide vane by the manufacturing system is based upon the outputted vane geometry; and
installing the fluid flow guide vane comprising the solid representation of the vane geometry at the AIP of the flow field of the aircraft, wherein the fluid flow guide vane produces the desired flow profile within the flow field during operation of the aircraft.
2. The method of claim 1 wherein said perpendicular lines are spaced at regular intervals.
3. The method of claim 1 wherein a seed line is used to create a first parallel line and said vane lines are created at predetermined intervals along said seed line.
4. The method of claim 1 wherein a vane model creates the vane geometry for said vane lines by using parameters including a distance to at least one adjacent vane line.
5. The method of claim 4 wherein the vane model creates the vane geometry for said vane lines by using parameters including the distance to the nearest two adjacent vane lines and a desired vane thickness and solidity.
6. The method of claim 1 wherein the array of desired velocity vectors is obtained from computational fluid dynamics or measurements from an experiment within the input flow.
7. The method of claim 1 , wherein the vane geometry comprises one or more of change in angle, chord length or thickness of one or more vanes.
8. The method of claim 1 , wherein the fluid flow guide vane comprises a mounting flange.
9. The method of claim 1 , wherein the fluid flow guide vane is configured for use with an aircraft engine.
10. The method of claim 1 , wherein the manufacturing system is an additive manufacturing system, and the fabrication of the fluid flow guide vane by the additive manufacturing system is controlled in response to the outputted vane geometry.