# US 8,769,926 B2 · Thrust reverser having an aerodynamic coupling for a front frame

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- Number: US 8,769,926 B2
- Document ID: US8769926B2
- Status: Granted
- Kind: B2
- Application number: 13/735,096
- Filed: 2013-01-07
- Published: 2013-05-23
- Granted: 2014-07-08
- Earliest claimed: 2010-07-07
- Assignees: Aircelle
- Applicants: Aircelle
- Inventors: Guy Bernard Vauchel; Jean-Philippe Joret
- Web page: https://patentgrep.com/patent/US8769926B2

## CPC

- F02K 1/62: by blocking the rearward discharge by means of flaps
- F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
- F02K 1/805: {Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps}
- 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)

## Abstract

A thrust reversal device for a turbojet engine nacelle is provided that includes a deflection means and at least one cowl moveable relative to at least one fixed structure including at least one at least partly peripheral front frame and equipped with means for connection to a corresponding upstream portion. The front frame has a deflection edge having an upstream extension forming a deformable flap intended to become an aerodynamic interface with the corresponding upstream portion to which is attached the front frame, and in that a portion of the moveable cowl is conformed so as to, in the closing position, interface with said upstream attachment portion by forcing withdrawal of the deformable flap.

## Claims

### Claim 1

A thrust reversal device for a turbojet engine nacelle comprising deflection grids and at least one cowl moveable relatively to at least one fixed structure including at least one at least partly peripheral front frame and equipped with means for connecting to a corresponding upstream portion, said at least one cowl being moveably mounted between a closing position in which the at least one cowl provides aerodynamic continuity of the turbojet engine nacelle and deactivates the deflection grids, an opening position in which the at least one cowl opens a passage in the turbojet engine nacelle and actuates the deflection grids, wherein the front frame has a deflection edge comprising an upstream extension forming a deformable flap to become an aerodynamic interface with the corresponding upstream portion to which is attached the front frame, and in that a portion of the at least one cowl is conformed so as to, in the closing position, interface with the corresponding upstream portion by forcing withdrawal of the deformable flap.

### Claim 2 (depends on 1)

The thrust reversal device according to claim 1, wherein the corresponding upstream portion of the front frame is a fan case.

### Claim 3 (depends on 1)

The thrust reversal device according to claim 1, wherein the means for connecting the front frame to the corresponding upstream portion are of a knife/groove type.

### Claim 4 (depends on 1)

The thrust reversal device according to claim 1, wherein the at least one cowl is translationally moveable along a substantially longitudinal axis of the turbojet engine nacelle, covering and uncovering the deflection grids in the closing and opening positions respectively.

### Claim 5 (depends on 4)

The thrust reversal device according to claim 4, wherein the deflection grids are mounted on the front frame.

### Claim 6 (depends on 1)

The thrust reversal device according to claim 1, wherein a portion of the at least one cowl conformed so as to force the deformable flap, is a blocking foil flap, notably pivotally mounted through an upstream end of the at least one cowl.

### Claim 7 (depends on 1)

The thrust reversal device according to claim 1, wherein the deformable flap is sector based.

### Claim 8 (depends on 1)

The thrust reversal device according to claim 1, wherein the deformable flap is made from at least one elastomeric material.

### Claim 9 (depends on 8)

The thrust reversal device according to claim 8, wherein the deformable flap comprises a lamellar core.

### Claim 10 (depends on 9)

The thrust reversal device according to claim 9, wherein the lamellar core is covered with a flexible coating.

### Claim 11 (depends on 1)

The thrust reversal device according to claim 1, wherein the deformable flap appears as a pivoting foil flap mounted against a spring returning the deformable flap towards the deformable flap's interface position in a forward thrust mode.

### Claim 12 (depends on 1)

The thrust reversal device according to claim 1, wherein the thrust reversal device comprises an abutment limiting a return of the deformable flap towards the deformable flap's interface position in a forward thrust mode.