U.S. Patent Specifications

Abstract

A temperature control for aircraft instruments comprising in combination an aircraft engine having a hot oil sump and a relatively cool oil sump, conduits from said sumps, a mixing valve having intakes connected individually to said conduits, a discharge conduit from said mixing valve, and a thermostatically controlled balanced valve for varying the openings respectively from said hot and cold conduits to said discharge conduit, said thermostat control being housed within said discharge conduit and said discharge conduit extending to an instrument panel board.

Citation

(1945), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 17 No. 10, pp. 309-310. https://doi.org/10.1108/eb031301