US 12,435,689 B2
Engine with diverter for heavy fuel injection
Chris Harris, McMinnville, OR (US); and Greg Stadeli, McMinnville, OR (US)
Assigned to NORTHWEST ULD, INC., McMinnville, OR (US)
Filed by Northwest ULD, Inc., McMinnville, OR (US)
Filed on Jan. 12, 2024, as Appl. No. 18/412,001.
Claims priority of provisional application 63/440,002, filed on Jan. 19, 2023.
Prior Publication US 2024/0247626 A1, Jul. 25, 2024
Int. Cl. F02M 37/00 (2006.01); F02B 61/04 (2006.01); F02B 75/02 (2006.01); F02M 61/14 (2006.01)
CPC F02M 37/0047 (2013.01) [F02B 61/04 (2013.01); F02B 75/02 (2013.01); F02M 61/14 (2013.01); F02B 2075/025 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A crankcase for a UAV internal combustion engine, comprising: a crankcase housing comprising a crankcase chamber; a fuel injection port extending through said crankcase housing to said crankcase chamber; a fuel diverter comprising a diverting surface disposed within said crankcase chamber and aligned with said fuel injection port; wherein the fuel diverter is configured to direct all the fuel in a single direction, wherein during operation fuel is injected into said crankcase chamber in a first direction that corresponds with a first vector, wherein the fuel is diverted, by said diverting surface, in a second direction that corresponds with a second vector, wherein the fuel diverter is fixed such that the second direction is fixed, wherein said second direction is different from said first direction, and a propellor hub mounted to a crankshaft an adapted to receive a propellor.