Multiple turn reverser with side turning vanes

Patent metadata

Field	Value
Publication number	US-12276238-B2
Application number	US-202318161670-A
Country	US
Kind code	B2
Filing date	Jan 30, 2023
Priority date	Jan 30, 2023
Publication date	Apr 15, 2025
Grant date	Apr 15, 2025

Abstract

A thrust reverser in an engine includes a first reverser portion configured to direct a gas in a first direction to create reverse thrust. The thrust reverser also includes a second reverser portion configured to direct the gas in a second direction that is different than the first direction. The second reverser portion is upstream or downstream from the first reverser portion.

First claim

What is claimed is:

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.

2. 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 third reverser portion, wherein the first reverser portion is positioned radially-between the second and third reverser portions, wherein the air flows through the third reverser portion when the thrust reverser is in the deployed state, and wherein the third 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 the fuselage and the wings of the airplane.

3. The engine of claim 2 , wherein a radial thickness of the second reverser portion increases as the thrust reverser actuates into the deployed state, and wherein circumferential gaps between each two adjacent louvers of the plurality of louvers increase as the thrust reverser actuates into the deployed state.

4. The engine of claim 2 , wherein the thrust reverser further comprises 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.

5. The engine of claim 2 , wherein a length of the first reverser portion, the second reverser portion, or both is from 10% to 30% of a length of the engine.

6. A method for actuating a thrust reverser in an engine into a deployed state, the method comprising:
actuating the thrust reverser from a stowed state into a deployed state, wherein the thrust reverser is in the stowed state when an 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 flow 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; and
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 wherei

Assignees

• Boeing Co

Inventors

• Chuck Chen
• Kornegay Brian S

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K1/68

  Reversers mounted on the engine housing downstream of the fan exhaust section · CPC title

• F02K1/72 Primary

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• F02K1/763

  with actuating systems or actuating devices; Arrangement of actuators for thrust reversers · CPC title

• F02K1/64 Primary

  Reversing fan flow · CPC title