US 12,276,238 B2
Multiple turn reverser with side turning vanes
Chen Chuck, Mercer Island, WA (US); and Brian S. Kornegay, Snohomish, WA (US)
Assigned to THE BOEING COMPANY, Arlington, VA (US)
Filed by The Boeing Company, Arlington, VA (US)
Filed on Jan. 30, 2023, as Appl. No. 18/161,670.
Prior Publication US 2024/0254943 A1, Aug. 1, 2024
Int. Cl. F02K 1/72 (2006.01); F02K 1/68 (2006.01)
CPC F02K 1/72 (2013.01) [F02K 1/68 (2013.01); F05D 2220/323 (2013.01)] 6 Claims
OG exemplary drawing
 
1. An engine on an airplane, the engine comprising:
a thrust reverser configured to actuate from a stowed state into a deployed state, wherein the thrust reverser is in the stowed state when the airplane is in flight, wherein the thrust reverser actuates into the deployed state after the airplane lands, and wherein the thrust reverser comprises:
a first reverser portion, wherein air flows through the first reverser portion when the thrust reverser is in the deployed state, wherein the first reverser portion turns the air at least partially in a forward direction to create reverse thrust, wherein the first reverser portion does not turn the air in a circumferential direction with respect to a central engine axis, and wherein the first reverser portion remains stationary as the thrust reverser actuates into the deployed state;
a second reverser portion positioned radially-outward from the first reverser portion, wherein the air flows through the second reverser portion when the thrust reverser is in the deployed state, wherein the second reverser portion turns the air at least partially in the circumferential direction with respect to the central engine axis such that the air is directed away from a fuselage and a wing of the airplane, wherein the second reverser portion does not turn the air in the forward direction, wherein the second reverser portion remains axially-stationary as the thrust reverser actuates into the deployed state, wherein the second reverser portion comprises a plurality of louvers that are circumferentially-offset from one another around the central engine axis, wherein the plurality of louvers each have a central louver axis extending therethrough, and wherein the plurality of louvers each rotate around their respective central louver axes as the thrust reverser actuates into the deployed state; and
a blocker door configured to actuate from a first position to a second position, wherein the first position is radially-outward from the second position, wherein the blocker door is in the first position when the thrust reverser is in the stowed state, wherein the blocker door actuates into the second position when the thrust reverser actuates into the deployed state, wherein the blocker door in the first position allows the air to flow out of the engine via a first outlet, wherein the blocker door in the second position diverts at least a portion of the air so that the air flows out of the engine via a second outlet, and wherein the first outlet is aft of the second outlet.