US 10,309,341 B2Granted

Thrust reverser cascade systems and methods

AssigneeThe Boeing Company

InventorsNaimishkumar B. Harpal, Chen Chuck

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Abstract

Systems and methods are provided for a formed thrust reverser cascade. The formed thrust reverser cascade may be coupled to an aircraft propulsor and may include a first portion disposed at a first angle to a portion of the aircraft propulsor and a second portion disposed at a second angle to the first portion. The formed thrust reverser cascade may be circumferentially disposed around a core engine of the aircraft propulsor. The formed thrust reverser cascades may be retrofitted to aircraft propulsors using linear thrust reverser cascade and may increase airflow through the formed thrust reverser cascade due to a greater throat area as compared to the linear thrust reverser cascade. Alternatively, the formed thrust reverser cascades may allow for shorter cascades while retaining the same performance, thus resulting in shorter nacelles.

Claims20

Dependent claims

An aircraft propulsor comprising:

a nacelle comprising a thrust reverser aperture;
a thrust reverser door configured to selectively move between an open position and a closed position to selectively block the thrust reverser aperture;
a core engine circumscribed by the nacelle, wherein the nacelle and the core engine define, at least in part, a bypass flow path;
and
a thrust reverser cascade comprising:
a plurality of cascade vanes arranged in a ramp shaped cross-section, disposed circumferentially around the core engine, and configured to couple to a portion of the nacelle and permit airflow from the bypass flow path through the plurality of cascade vanes, wherein the ramp shaped cross-section comprises:
a first section comprising a first section first end and a first section second end, wherein the first section first end is disposed closer to the core engine than the first section second end;
and
a second section disposed at a first angle to the first section and comprising a second section first end and a second section second end, wherein the second section first end connects to the first section second end;
and
a third section disposed at a second angle to the second section and comprising a third section first end and a third section second end, wherein the third section first end connects to the second section second end, and wherein the third section second end is disposed closer to the core engine than the third section first end;
and
a support structure coupled to at least two of the plurality of cascade vanes.

10 more elements

A method comprising:

energizing airflow with a core engine of an aircraft propulsor such that the energized airflow flows within a bypass flow path of the aircraft propulsor defined, at least in part, by the core engine and a nacelle of the aircraft propulsor;
moving a thrust reverser door of the aircraft propulsor to an open position, wherein the thrust reverser door is configured to selectively move between the open position and a closed position to selectively block a thrust reverser aperture disposed within the nacelle;
and
diverting at least a portion of the airflow through a thrust reverser cascade, wherein the thrust reverser cascade comprises:
a plurality of cascade vanes arranged in a ramp shaped cross-section, disposed circumferentially around the core engine, and configured to couple to a portion of the nacelle and permit airflow from the bypass flow path through the plurality of cascade vanes, wherein the ramp shaped cross-section comprises:
a first section comprising a first section first end and a first section second end, wherein the first section first end is disposed closer to the core engine than the first section second end;
and
a second section disposed at a first angle to the first section and comprising a second section first end and a second section second end, wherein the second section first end connects to the first section second end;
and
a third section disposed at a second angle to the second section and comprising a third section first end and a third section second end, wherein the third section first end connects to the second section second end, and wherein the third section second end is disposed closer to the core engine than the third section first end;
and
a support structure coupled to at least two of the plurality of cascade vanes.

9 more elements

Dependencies are inferred from the claim text.

Facts

Application: 14/997,295Filed 15 Jan 2016
Published: US 2017/0204810 A120 Jul 2017
Granted: 4 Jun 2019
Term ends: Not estimatedThe source records don’t support an estimate.

Classification12 codes

F02K 1/72
Using thrust reverser flaps or doors mounted on the fan housing: the aft end of the fan housing being movable to uncover openings in the fan…
B64D 29/02
Power-plant nacelles, fairings or cowlings: associated with wings
B64D 29/04
Power-plant nacelles, fairings or cowlings: associated with fuselages
B64D 33/04
Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for: of exhaust outlets or jet pipes

Family

US 2017/0204810 A1Pre-grant publication · published 20 Jul 2017
US 10,309,341 B2This patent

From the US filing history. Foreign family members aren’t listed.

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