# US 2014/0150404 A1 · Thrust reverser device for compact jet pipe

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- Number: US 2014/0150404 A1
- Document ID: US20140150404A1
- Status: Published application
- Kind: A1
- Application number: 14/236,498
- Filed: 2012-08-08
- Published: 2014-06-05
- Earliest claimed: 2011-08-08
- Assignees: Snecma
- Inventors: Francois Gallet
- Web page: https://patentgrep.com/patent/US20140150404A1

## CPC

- F02K 1/70: using thrust reverser flaps or doors mounted on the fan housing
- F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
- 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 bypass turbojet engine nacelle that forms a fan casing includes a first, upstream, streamlining element and a second streamlining element that forms a jet pipe. The second element can move translationally between a position ensuring aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings. A thrust reverser device is housed in the nacelle and includes flow reverser flaps and cascades of vanes providing radial guidance for the flow. The cascades of vanes providing radial guidance for the flow can move in translation along the axis of the nacelle between a retracted position into the first steamlining element and an active flow-guidance position, the second streamlining element being secured to the cascades of vanes, the reverser flaps being mounted to rotate about axes that are transverse with respect to the axis of the nacelle and secured to the cascades of vanes.

## Claims

### Claim at position 1

1-9. (canceled)

### Claim 10

A nacelle for a bypass turbojet engine, forming an envelope of a fan, comprising:
a first streamlining element, upstream, and a second streamlining element forming a pipe, the second element being movable in translation between a position in which it ensures aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings;
a thrust reverser device accommodated in the nacelle and comprising bypass flow reverser flaps and cascades for radial guidance of flow,
wherein the cascades for radial guidance of flow are movable in translation along a length of the axis of the nacelle between a position in which they are retracted into the first streamlining element and an active flow guidance position, the second streamlining element being integral with the cascades, and
reverser flaps fitted to be movable in rotation around axes that are transverse relative to the axis of the nacelle and integral with the cascades.

### Claim 11 (depends on 10)

A nacelle according to claim 10, wherein the first streamlining element comprises rails for guiding the cascades, extending in a downstream direction from an upstream edge of the first streamlining element.

### Claim 12 (depends on 10)

A nacelle according to claim 10, wherein the cascades are integral with a synchronizing ring perpendicular to the axis of the engine.

### Claim 13 (depends on 10)

A nacelle according to claim 10, wherein the cascades are set in movement in translation by a motor unit accommodated in the first streamlining element.

### Claim 14 (depends on 10)

A nacelle according to claim 10, wherein the reverser flaps are controlled in rotation around the transverse axes by connecting rods.

### Claim 15 (depends on 14)

A nacelle according to claim 14, wherein the connecting rods are fitted slideably parallel to the axis of the nacelle, a first extremity of the connecting rods being articulated on the reverser flaps and a second extremity sliding in a housing of the first streamlining element.

### Claim 16 (depends on 15)

A nacelle according to claim 15, wherein the first streamlining element comprises rails for guiding the cascades, extending in a downstream direction from an upstream edge of the first element, and wherein the connecting rods are guided along a length of guide rails with an arrangement driving pivoting of the connecting rods around an axis perpendicular to the guide rails, and tilting of the reverser flaps when the second, movable, streamlining element is at a given distance from the first streamlining element, in the flow reversal position.

### Claim 17 (depends on 10)

A turbojet engine comprising a nacelle according to claim 10, wherein the second movable element, forming a pipe, creates with a primary flow fairing a flow section that is variable, as a function of an axial position of the second element.

### Claim 18 (depends on 10)

A turbojet engine comprising a nacelle according to claim 10, the second movable element forming a pipe creating with a primary flow fairing a flow section that is variable, as a function of axial position of the second element, and a flow section of which increases when the second element forming a pipe is driven from its upstream position over a part of its movement in a downstream direction, the thrust reverser device being put in place when the second element forming a pipe continues its movement in a downstream direction.