公开(公告)号：US10745140B2

公开(公告)日：2020-08-18

申请号：US15829131

申请日：2017-12-01

Applicant: Safran Nacelles

Inventor： Vincent Peyron ,  Serge Bunel ,  Pascal Soulier ,  Arnaud Bonny

IPC: B64D29/06 ,  B64D29/00 ,  E05B65/06 ,  E05C1/00 ,  E05C7/04 ,  B64C7/02 ,  F02K1/64

Abstract: The present disclosure provides a device for locking a first cowling and a second cowling of a thrust reverser of an aircraft propulsion assembly. The cowlings are mounted such that each cowl pivots around a longitudinal axis between a closed flight position and an open maintenance position. The locking device includes a telescopic connecting rod having at least one sliding shaft, a locking mechanism on a proximal end of a shaft on the second cowling, and a connecting rod support. The connecting rod support or the tubular element includes two walls each delimiting a hole, and the tubular element of the connecting rod or the connecting rod support has two support fingers which each extend longitudinally on a side of the tubular element into a hole. The holes engage with the support fingers when the cowlings are open and allow free movement of the support fingers in a closed-cowlings configuration.

公开(公告)号：US11883874B2

公开(公告)日：2024-01-30

申请号：US17492790

申请日：2021-10-04

Applicant: Safran Nacelles

Inventor： Vincent Peyron ,  Jean-Nicolas Bouchout ,  Flavie Hubert-Choinard ,  Alexandra Dugardin

IPC: B21D53/04

CPC classification number: B21D53/04 ,  Y10T29/4935

Abstract: A method for manufacturing a structural surface heat exchanger of preset or left-hand final shape for an aircraft includes the steps of forming, shaping and assembling, by welding or brazing, a first corrugated skin and a second smooth skin in order to obtain channels. Each channel is delimited by a corrugation of the first skin and the second smooth skin so as to form a structural surface heat exchanger of preset or left-hand final shape, wherein a fluid is configured to circulate in the channels and air is configured to circulate in contact with the second smooth skin.

公开(公告)号：US11512638B2

公开(公告)日：2022-11-29

申请号：US16839123

申请日：2020-04-03

Applicant: Safran Nacelles

Inventor： Vincent Peyron ,  Jean-Nicolas Bouchout

IPC: F02C7/16 ,  F28F9/00

Abstract: A surface heat-exchanger for a turbojet engine nacelle between a fluid (C) to be cooled down and air (F) includes a circulation duct of the fluid (C) to be cooled down disposed in contact with air. The circulation duct includes a plurality of channels extending substantially in the same direction with a distance (D) between two adjacent channels between two and five times the width (L) of the channels, each channel having a wall with an area intended to be in contact with air and an area opposite to the area intended to be in contact with air.

公开(公告)号：US11268443B2

公开(公告)日：2022-03-08

申请号：US16253352

申请日：2019-01-22

Applicant: Safran Nacelles

Inventor： Vincent Peyron ,  Patrick Gonidec ,  Jean-Nicolas Bouchout

IPC: F02C7/14 ,  F02C7/16 ,  F02K3/115 ,  B64D33/10 ,  F02C7/00 ,  B64D29/06 ,  B64D33/08 ,  F02K3/06

Abstract: A nacelle of a turbine engine has a substantially tubular structure and defines a secondary channel. The nacelle includes a shroud forming a trailing edge on a downstream end of the nacelle, the shroud being defined by at least one outer face subjected to an outside air flow and an inner face subjected to an inside air flow circulating in the secondary channel of the nacelle. The nacelle further includes a cooling device having at least one heat-exchange channel that extends into the shroud.

公开(公告)号：US11199158B2

公开(公告)日：2021-12-14

申请号：US16876704

申请日：2020-05-18

Applicant: Safran Nacelles

Inventor： Pierre Caruel ,  Vincent Peyron

IPC: F02K1/70 ,  B64D29/06 ,  F02K1/76

Abstract: An aircraft propulsion assembly with an engine provided with a cascade-type thrust reverser includes cascades of mobile deflection vanes connected to cascade rails with a slideway connection that allows the cascades of vanes a translational movement between a cruising-flight position and a reverse-thrust position. The thrust reverser allows the cascade rails to be positioned in a forward position, in which the engine, the cascade rails and the deflection vanes can be removed from the propulsion assembly without the cascade rails colliding with the mobile cowl of the reverser. Dismantling and assembly or reassembly methods allow maintenance operations to be carried out on the engine thus dismantled.

公开(公告)号：US11959439B2

公开(公告)日：2024-04-16

申请号：US17685649

申请日：2022-03-03

Applicant: Safran Nacelles

Inventor： Vincent Peyron

IPC: F02K1/76 ,  F02K1/72

CPC classification number: F02K1/72 ,  F02K1/763 ,  F05D2250/34 ,  F05D2260/50

Abstract: A thrust reverser includes a diverter configured to divert at least a portion of an air flow from a nacelle and a cowl movable relative to an outer fixed structure of the thrust reverser. The thrust reverser further includes at least one rotatably hinged flap. The cowl configured to move from a closure position in which it provides aerodynamic continuity of the nacelle with the flap and covers the diverter. The flap is movable from a retracted position to an opening position in which it opens a passage in the nacelle and uncovers the diverter. The flap obstructs a portion of an annular channel of the nacelle when in the opening position. The thrust reverser also includes a cable-pulley system for driving the flap. The cable-pulley system includes at least one cable associated with at least one pulley to connect the flap to the thrust reverser.

公开(公告)号：US11772810B2

公开(公告)日：2023-10-03

申请号：US16839145

申请日：2020-04-03

Applicant: Safran Nacelles

Inventor： Vincent Peyron ,  Jean-Nicolas Bouchout

IPC: B64D33/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  F02C7/16 ,  F28D9/00 ,  F28D21/00

CPC classification number: B64D33/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  F02C7/16 ,  F28D9/00 ,  F05D2260/213 ,  F28D2021/0021

Abstract: An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).

公开(公告)号：US11230973B2

公开(公告)日：2022-01-25

申请号：US16839118

申请日：2020-04-03

Applicant: Safran Nacelles

Inventor： Vincent Peyron ,  Jean-Nicolas Bouchout

IPC: F02C7/16 ,  F02C7/14

Abstract: In a cooling system of an aircraft turbojet engine surrounded by a nacelle, a heat-transfer fluid is circulated that is less flammable than a lubricant (H) for the turbojet engine and liquid at temperatures between −70° C. and +175° C., the heat-transfer fluid (C) being intended to circulate in a closed-circuit circulation duct including a first surface heat-exchanger between the heat-transfer fluid (C) and air (F), at the level of at least one of the outer fairing and the inner fairing of the nacelle, and a second surface heat-exchanger between the heat-transfer fluid (C) and the lubricant (H).