# US 10,309,341 B2 · Thrust reverser cascade systems and methods

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- Number: US 10,309,341 B2
- Document ID: US10309341B2
- Status: Granted
- Kind: B2
- Application number: 14/997,295
- Filed: 2016-01-15
- Published: 2017-07-20
- Granted: 2019-06-04
- Earliest claimed: 2016-01-15
- Assignees: The Boeing Company
- Applicants: The Boeing Company
- Inventors: Naimishkumar B. Harpal; Chen Chuck
- Web page: https://patentgrep.com/patent/US10309341B2

## CPC

- F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
- B64D 29/02: associated with wings
- B64D 29/04: associated with fuselages
- B64D 33/04: of exhaust outlets or jet pipes
- F02K 1/625: {the aft end of the engine cowling being movable to uncover openings for the reversed flow}
- F02K 1/70: using thrust reverser flaps or doors mounted on the fan housing
- F05D 2240/129: Cascades, i.e. assemblies of similar profiles acting in parallel
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## 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.

## Claims

### Claim 1

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.

### Claim 2 (depends on 1)

The aircraft propulsor of claim 1, wherein at least one of the plurality of cascade vanes comprises an angled cross-sectional shape.

### Claim 3 (depends on 2)

The aircraft propulsor of claim 2, wherein the plurality of cascade vanes comprise angled cross-sectional shapes.

### Claim 4 (depends on 2)

The aircraft propulsor of claim 2, wherein the plurality of cascade vanes are configured to redirect airflow to provide thrust to slow an aircraft.

### Claim 5 (depends on 1)

The aircraft propulsor of claim 1, wherein the second section is disposed within two feet of the thrust reverser door.

### Claim 6 (depends on 1)

The aircraft propulsor of claim 1, wherein at least a portion of the second section is disposed closer to a portion of the thrust reverser door than at least a portion of the first section when the thrust reverser door is in the closed position.

### Claim 7 (depends on 1)

The aircraft propulsor of claim 1, wherein at least a portion of the second section is disposed farther from a centerline of the core engine than at least a portion of the first section.

### Claim 8 (depends on 1)

The aircraft propulsor of claim 1, wherein the thrust reverser cascade is coupled to a bullnose of the nacelle at a cascade first end and coupled to a cascade support ring at a cascade second end.

### Claim 9 (depends on 1)

The aircraft propulsor of claim 1, further comprising a blocker door, the blocker door configured to move to at least a deployed position to divert at least a portion of the airflow within the bypass flow path through the plurality of cascade vanes.

### Claim 10 (depends on 1)

An aircraft comprising the aircraft propulsor of claim 1, the aircraft comprising:
a fuselage; and
a wing, wherein the aircraft propulsor is coupled to the fuselage and/or the wing.

### Claim 11

A thrust reverser cascade comprising:
a plurality of cascade vanes arranged in a ramp shaped cross-section and configured to couple to a portion of an aircraft propulsor nacelle and permit airflow 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 second end is configured to be disposed closer to at least a portion of a surface of the aircraft propulsor nacelle than the first section first end;
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 first end is configured to be disposed closer to at least a portion of the surface of the aircraft propulsor nacelle than the third section second end; and
a support structure coupled to at least two of the plurality of cascade vanes.

### Claim 12 (depends on 11)

The thrust reverser cascade of claim 11, wherein the plurality of cascade vanes are configured to be disposed circumferentially around a core engine of an aircraft propulsor.

### Claim 13 (depends on 11)

The thrust reverser cascade of claim 11, wherein at least one of the plurality of cascade vanes comprises an angled cross-sectional shape.

### Claim 14 (depends on 13)

The thrust reverser cascade of claim 13, wherein the plurality of cascade vanes comprise angled cross-sectional shapes.

### Claim 15 (depends on 11)

The thrust reverser cascade of claim 11, wherein the second section is configured to be disposed within two feet of a thrust reverser door of the aircraft propulsor.

### Claim 16 (depends on 11)

The thrust reverser cascade of claim 11, wherein at least a portion of the second section is configured to be disposed closer to a portion of a thrust reverser door of the aircraft propulsor than at least a portion of the first section.

### Claim 17 (depends on 11)

The thrust reverser cascade of claim 11, wherein a cascade first end of the thrust reverser cascade is configured to couple to a bullnose of the aircraft propulsor nacelle and a cascade second end of the thrust reverser cascade is configured to couple to a cascade support ring.

### Claim 18

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.

### Claim 19 (depends on 18)

The method of claim 18, wherein diverting at least the portion of the airflow through the thrust reverser cascade comprises diverting at least the portion of the airflow with a blocker door in a deployed position.

### Claim 20 (depends on 18)

The method of claim 18, wherein the airflow is diverted to provide reverse thrust to slow an aircraft.