AVIATION GASOLINE ENGINE COOLANT INJECTION SYSTEM

Abstract

A set of apparatus to inject distilled-water in solution acting as an engine coolant into the combustion chamber of a high-compression air-cooled piston aircraft engine to mix with aviation gasoline, operating on a minimum 91 motor octane aviation gasoline (leaded or unleaded), thereby improving engine performance, and suppressing early detonation in prescribed operating situations. The apparatus incorporates 1) an ultra-light weight corrosion-resistant engine coolant storage compartment mounted inside the aircraft, 2) stainless steel pipe fittings, 3) controller activated fluid injectors with wide spray nozzles, 4) aircraft-approved wiring and stainless steel plumbing tied to the pump and combustion chamber, 5) a primary and back-up electric pump approved for aviation use, 6) a special formulation of water-based cooling fluid in solution with a non-toxic anti-freezing agent designed for high altitude aircraft use, 7) electric sensors for temperature, pressure and early detonation programmed to a sensory control unit that automatically activates the electric pump to inject coolant only on pre-configured conditions during periods of peak engine performance when early detonation is most likely to occur, 8) a is digital metering display for the pilot instrument panel capable to report cylinder-head temperature, manifold pressure, oxygen (air/fuel ratio) and an aviation approved knock-sensor, and 8) a test switch and automatic operation on-off switch.

Claims

1. An apparatus to inject distilled-water into the combustion chamber of a high-compression air-cooled piston aircraft engine, said apparatus including: an ultra-light weight corrosion-resistant engine coolant storage compartment; stainless steel pipe fittings; controller activated fluid injectors with wide spray nozzles; aircraft-approved wiring and stainless steel plumbing tied to the pump and combustion chamber; a primary and back-up electric pump; a water-based cooling fluid in solution with a non-toxic anti-freezing agent; electric sensors for temperature, pressure and early detonation detection; a digital metering display for the pilot instrument panel capable to report cylinder-head temperature, manifold pressure, oxygen (air/fuel ratio) and an aviation approved knock-sensor; and a test switch and on-off switch.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0036] FIG. 1 is a diagram of an exemplary apparatus.