US 9,810,145 B1
Ducted impeller
Philip C. Bannon, Marysville, WA (US)
Filed by Philip C. Bannon, Marysville, WA (US)
Filed on Jun. 11, 2014, as Appl. No. 14/302,012.
Claims priority of provisional application 61/833,752, filed on Jun. 11, 2013.
Int. Cl. F02K 3/06 (2006.01); F02C 3/107 (2006.01); F02C 3/04 (2006.01); B64D 29/06 (2006.01); F01D 5/14 (2006.01)
CPC F02C 3/107 (2013.01) [B64D 29/06 (2013.01); F01D 5/141 (2013.01); F01D 5/148 (2013.01); F02C 3/04 (2013.01); F02K 3/06 (2013.01)] 8 Claims
OG exemplary drawing
 
6. A ducted fan of an engine assembly, configured to direct air around a rotational device, the ducted fan comprising:
a casing mechanically coupled to a jet engine casing wherein the jet engine casing is further attached to a plurality of ducting panels including:
forward ducting panels,
a forward central ducting panel,
a rear central ducting panel and
rear ducting panels,
wherein each of the plurality of ducting panel extends radially outward from a root of each of the plurality of ducting panels to a tip of each of the plurality of ducting panels;
wherein the root of each of the plurality of ducting panels is attached to the jet engine casing,
wherein the tip of each of the plurality of ducting panels terminates at a free end of each of the plurality of ducting panels,
wherein the free end of each forward ducting panel is located within a flowpath between the jet engine casing and the casing and the root of each forward ducting panel is located forward of a combustion stage with respect to a longitudinal axis of the engine assembly,
wherein the ducted fan further comprises:
blades that are widest at a blade tip, narrowing down to a hub, while not over lapping and beginning with a rotation of at least 45 degrees measured from an axis of a shaft to a blade chord and of a smaller angle going toward the hub to create an even aft pressure along an entire length of each blade.