公开(公告)号：US20190137362A1

公开(公告)日：2019-05-09

申请号：US16183981

申请日：2018-11-08

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Laurent Louis Robert BAUDOIN ,  Josselin David Florian Regnard

IPC: G01M15/02 ,  G01M15/14 ,  F01D25/28

Abstract: A ground testing device for a turbomachine, including an aircraft engine (12) extending axially from an air inlet to a nozzle, a shroud (20) having an axis of revolution (A) and surrounding at least partially the engine (12) so as to create an annular air flow between the engine (12) and the shroud (20) when the engine (12) is in operation, and a framework (22) allowing the shroud (20) to be supported.

公开(公告)号：US20180355878A1

公开(公告)日：2018-12-13

申请号：US15781291

申请日：2016-12-07

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Josselin David Florian REGNARD ,  Laurent Louis Robert BAUDOIN

IPC: F04D27/02 ,  F04D29/66 ,  F01D25/30 ,  F02C9/18

Abstract: An assembly including a compressor for a turbine engine, and a discharge system including a supply duct, one end of which is connected to the compressor, the duct being configured to collect therefrom a flow of air compressed by the compressor; and a pressure-reduction device including an inlet and an outlet, the inlet being connected to the other end of the supply duct, wherein the pressure reduction device includes a casing forming a volume between the inlet and the outlet, a porous material occupying the volume, and a device for holding the porous material within the casing, wherein the outlet has an open section allowing the upper air to pass through the open section of the inlet.

公开(公告)号：US20220268212A1

公开(公告)日：2022-08-25

申请号：US17629523

申请日：2020-08-06

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Laurent Louis Robert BAUDOIN ,  Norman Bruno André JODET

IPC: F02C7/18 ,  B64D33/04 ,  F02K1/38

Abstract: Internal structure for a turbomachine nacelle, the internal structure being intended to surround at least one part of a compartment capable of receiving a gas generator of the turbomachine, the internal structure comprising a ventilation cavity of said compartment, the ventilation cavity being provided with a main ventilation outlet and an auxiliary ventilation outlet separate to the main ventilation outlet, the internal structure comprising a shut-off member movable relative to the ventilation cavity between a flow position and a shut-off position in which the shut-off member shuts off the auxiliary ventilation outlet to a greater extent than in the flow position.

公开(公告)号：US20190040795A1

公开(公告)日：2019-02-07

申请号：US16072069

申请日：2017-01-25

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Josselin David Florian REGNARD ,  Laurent Louis Robert BAUDOIN ,  Hélène Monique ORSI

IPC: F02C7/14 ,  F02C7/045

Abstract: The invention relates to an assembly for a turbine engine (1), the assembly including: a casing (20) extending along a longitudinal axis (X-X′) of the turbine engine (1), a surface heat exchanger (100) arranged along an inner edge (22) of said casing (20) and including a plurality of cooling fins (110) extending radially inwards and longitudinally, and a central body (30) partially concentrically arranged within said casing (20), said casing (20) and the central body (30) defining between one another an annular air channel (Va), the width (hVa) of which is substantially constant in the region of the heat exchanger (100). The assembly is characterized in that the fins (110) are distributed over more than 180° of the inner edge (22) of the casing (20) and in that the mean height ((hMOV) of the fms (110) is more than 5% of the width (hVa) of the annular air channel (Va) in the region the heat exchanger (100).

公开(公告)号：US20180311859A1

公开(公告)日：2018-11-01

申请号：US15963985

申请日：2018-04-26

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Norman Bruno Andre JODET ,  Laurent Louis Robert BAUDOIN ,  Jeremy Paul GONZALEZ

IPC: B26F1/24 ,  F02C7/045 ,  B32B3/26 ,  B32B3/12 ,  B32B27/08

CPC classification number: B26F1/24 ,  B26F1/0038

Abstract: Device for perforating an acoustic annular panel for a turbine engine, wherein it includes a perforation needle support ring, the ring having an axis A of revolution and being intended to be inserted substantially coaxially inside the panel, the ring being sectored and including ring sectors regularly distributed around the axis and each one radially mobile opposite the axis from a radially inner rest position up to a perforation position of the radially outer panel, and at least one rotating actuator of rotation axis A and mechanically connected to the ring sectors such that a rotation of the actuator leads to a radial movement of the ring sectors.