# US 2023/0067232 A1 · Thrust reverser comprising doors forming an upward air deflection opening in the open position

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- Number: US 2023/0067232 A1
- Document ID: US20230067232A1
- Status: Published application
- Kind: A1
- Application number: 17/790,661
- Filed: 2020-12-18
- Published: 2023-03-02
- Earliest claimed: 2020-01-02
- Assignees: Safran Nacelles
- Applicants: Safran Nacelles
- Inventors: Sebastien Laurent Marie PASCAL
- Web page: https://patentgrep.com/patent/US20230067232A1

## CPC

- F02K 1/60: by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
- F02K 1/62: by blocking the rearward discharge by means of flaps
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- 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)
- 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

A thrust reverser for an aircraft propulsion assembly, this reverser including a lower door and an upper door defining, in thrust reversal configuration, a deflection opening, through which a portion of the fluid not serving to produce the thrust reversal of the aircraft can exit the reverser downstream. The downstream edge of the lower door is offset towards the rear with respect to the downstream edge of the upper door so as to orient the fluid flow passing through the deflection opening vertically upwards. When the propulsion assembly is mounted at the rear portion of the fuselage of the aircraft, this makes it possible in particular to improve the supply of the control surface of the aircraft in the landing phase, in particular in crosswind conditions.

## Claims

### Claim 1

A thrust reverser for an aircraft propulsion assembly, said reverser having a central longitudinal axis and comprising a fixed structure, a lower door and an upper door, the lower door and the upper door each comprising a downstream edge and each being movable with respect to the fixed structure, around a respective axis of rotation, between:
a closed position wherein the lower and upper doors delimit with the fixed structure a flow conduit, the flow conduit comprising an ejection outlet delimited at least partly by a rear end of the fixed structure, the lower and upper doors in the closed position being configured to be able to guide a fluid flowing in the conduit to its ejection outlet to generate a thrust, and
an open position wherein the lower and upper doors each release a reversal opening so as to be able to evacuate from the flow conduit a first portion of said fluid, via these reversal openings, and redirect at least a fraction of the fluid thus evacuated towards a front end of the fixed structure in order to generate counter-thrust,
the downstream edge of the lower door and the downstream edge of the upper door defining, when the lower and upper doors are in the open position, a deflection opening configured to allow a second portion of said fluid to exit the reverser through said deflection opening, said reverser comprising, when the lower and upper doors are in the open position:
a midpoint of the downstream edge of the lower door is offset along the central longitudinal axis towards the rear by a first distance with respect to a midpoint of the downstream edge of the upper door, these midpoints intersecting a median longitudinal plane perpendicular to said axis of rotation of the lower and upper doors,
said midpoint of the downstream edge of the lower door is offset in a vertical direction, with respect to said midpoint of the downstream edge of the upper door, towards a distal end of the lower door by a second distance, the vertical direction being perpendicular to the central longitudinal axis and to the axis of rotation of the lower and upper doors,
the ratio of said second distance and said first distance is comprised between 0.2 and 2.

### Claim 2 (depends on 1)

The reverser according to claim 1, wherein said first distance is comprised between five percent and thirty percent of a radius of a section of said ejection outlet when the lower and upper doors are in the closed position.

### Claim 3 (depends on 1)

The reverser according to claim 1, wherein the deflection opening has a surface projected onto a projection plane perpendicular to the central longitudinal axis comprised between two percent and ten percent of an ejection surface formed by a section of said ejection outlet when the lower and upper doors are in the closed position.

### Claim 4 (depends on 1)

The reverser according to claim 1, wherein the axis of rotation of the lower door is offset along the central longitudinal axis with respect to the axis rotation of the upper door.

### Claim 5 (depends on 1)

The reverser according to claim 1, wherein each of the lower and upper doors forms with respect to the central longitudinal axis, when said doors are in the open position, an opening angle comprised between 55° and 65°.

### Claim 6 (depends on 1)

The reverser according to claim 1, wherein the fixed structure comprises an annular ejection shroud, said ejection shroud comprising a trailing edge forming said rear end of the fixed structure.

### Claim 7 (depends on 1)

The reverser according to claim 1, wherein the downstream edge of the lower door and the downstream edge of the upper door delimit a respective portion of said ejection outlet when the lower and upper doors are in the closed position.

### Claim 8 (depends on 1)

The reverser according to claim 1, wherein the deflection opening has an ovoid surface, projected onto a projection plane perpendicular to the central longitudinal axis.

### Claim 9 (depends on 1)

A propulsion assembly for an aircraft, said propulsion assembly comprising a nacelle comprising a reverser according to claim 1.

### Claim 10 (depends on 9)

An aircraft comprising a fuselage, a vertical tail and a propulsion assembly according to claim 9, the propulsion assembly being connected to the fuselage so that, in said vertical direction, said midpoint of the downstream edge of the upper door is located between said midpoint of the downstream edge of the lower door and the vertical tail.