Brian J Birch

US Patent:

20180202893, Jul 19, 2018

Filed:

Nov 17, 2017

Appl. No.:

15/816573

Inventors:

Brian Jeffrey Birch - Dowell MD, US

International Classification:

G01M 9/04
G01M 9/06

Abstract:

An apparatus for a unique wind tunnel useable for testing various aerospace specific sensors and probes is presented. The wind tunnel apparatus as presented utilizes an effective variable nozzle and thus allows for the testing of such aerospace devices over a near infinite Mach and Reynolds numbers in subsonic flow. The variable nozzle allows for quick and easy adjustment over a minimum 1×107 range of Reynolds number conditions from flow velocity of Mach 0.01 to 0.99. The optimal design of the wind tunnel also allows for adaptation to different size test tunnels, using existing facilities to reduce cost, thus enabling various aerospace design applications. The apparatus of the present invention, the variable nozzle test wind tunnel, provides a highly variable test environment in order to improve the development of advanced aerospace sensors, including benefits such as: development of flow sensors to prevent compressor stall; development of optical sensors to optimize turbine and compressor airflow; and, development of temperature sensors to increase efficiency of turbine engine operation.