公开(公告)号：US12196115B2

公开(公告)日：2025-01-14

申请号：US18458588

申请日：2023-08-30

Applicant: THE BOEING COMPANY

Inventor： Michael Hayes ,  Keith A. Etling ,  Jordan Kreitzman ,  Rehan Milarachi ,  Manny Urcia ,  Andrews Guadron

IPC: G10K11/16 ,  B64D27/00 ,  B64D33/02 ,  B64U10/13 ,  B64U50/12 ,  F01N1/02 ,  F02C7/045 ,  G10K11/172 ,  B64U30/40 ,  F02C6/20

Abstract: A flow path duct system for a propulsion system of an aircraft includes a base defining a flow surface. The base has an internal surface and an external surface. A plurality of perforations are formed through the base between the internal surface and the external surface. A plurality of supports define a plurality of cavities. The plurality of supports extend outwardly from the external surface of the of the base. One or more of the plurality of cavities are in fluid communication with the one or more of the plurality of perforations. A backing surface is secured to the plurality of supports. The plurality of supports are disposed between the base and the backing surface. The one or more of the plurality of cavities are in fluid communication with an internal volume defined by the internal surface of the base through the one or more of the plurality of perforations. The base, the plurality of supports, and the backing surface can be integrally formed together as a monolithic, load-bearing structure.

公开(公告)号：US20230407775A1

公开(公告)日：2023-12-21

申请号：US18458588

申请日：2023-08-30

Applicant: THE BOEING COMPANY

Inventor： Michael Hayes ,  Keith A. Etling ,  Jordan Kreitzman ,  Rehan Kaluarachchi ,  Manny Urcia ,  Andrews Guadron

IPC: F01N1/02 ,  B64D27/00 ,  G10K11/16 ,  G10K11/172 ,  F02C7/045

CPC classification number: F01N1/023 ,  B64D27/00 ,  G10K11/161 ,  G10K11/172 ,  F02C7/045 ,  F02C6/20

Abstract: A flow path duct system for a propulsion system of an aircraft includes a base defining a flow surface. The base has an internal surface and an external surface. A plurality of perforations are formed through the base between the internal surface and the external surface. A plurality of supports define a plurality of cavities. The plurality of supports extend outwardly from the external surface of the of the base. One or more of the plurality of cavities are in fluid communication with the one or more of the plurality of perforations. A backing surface is secured to the plurality of supports. The plurality of supports are disposed between the base and the backing surface. The one or more of the plurality of cavities are in fluid communication with an internal volume defined by the internal surface of the base through the one or more of the plurality of perforations. The base, the plurality of supports, and the backing surface can be integrally formed together as a monolithic, load-bearing structure.

公开(公告)号：US11767776B2

公开(公告)日：2023-09-26

申请号：US17321591

申请日：2021-05-17

Applicant: THE BOEING COMPANY

Inventor： Michael Hayes ,  Keith A. Etling ,  Jordan Kreitzman ,  Rehan Kaluarachchi ,  Manny Urcia ,  Andrews Guadron

IPC: G10K11/16 ,  G10K11/172 ,  F02C7/045 ,  B64D33/02 ,  F01N1/02 ,  B64D27/00 ,  F02C6/20

CPC classification number: F01N1/023 ,  B64D27/00 ,  F02C7/045 ,  G10K11/161 ,  G10K11/172 ,  B64D2033/0206 ,  F02C6/20 ,  F05D2220/323 ,  F05D2260/963

Abstract: A flow path duct system for a propulsion system of an aircraft includes a base defining a flow surface. The base has an internal surface and an external surface. A plurality of perforations are formed through the base between the internal surface and the external surface. A plurality of supports define a plurality of cavities. The plurality of supports extend outwardly from the external surface of the of the base. One or more of the plurality of cavities are in fluid communication with the one or more of the plurality of perforations. A backing surface is secured to the plurality of supports. The plurality of supports are disposed between the base and the backing surface. The one or more of the plurality of cavities are in fluid communication with an internal volume defined by the internal surface of the base through the one or more of the plurality of perforations. The base, the plurality of supports, and the backing surface can be integrally formed together as a monolithic, load-bearing structure.

公开(公告)号：US20220074329A1

公开(公告)日：2022-03-10

申请号：US17321591

申请日：2021-05-17

Applicant: THE BOEING COMPANY

Inventor： Michael Hayes ,  Keith A. Etling ,  Jordan Kreitzman ,  Rehan Kaluarachchi ,  Manny Urcia ,  Andrews Guadron

IPC: F01N1/02 ,  B64D27/00 ,  G10K11/16 ,  G10K11/172

Abstract: A flow path duct system for a propulsion system of an aircraft includes a base defining a flow surface. The base has an internal surface and an external surface. A plurality of perforations are formed through the base between the internal surface and the external surface. A plurality of supports define a plurality of cavities. The plurality of supports extend outwardly from the external surface of the of the base. One or more of the plurality of cavities are in fluid communication with the one or more of the plurality of perforations. A backing surface is secured to the plurality of supports. The plurality of supports are disposed between the base and the backing surface. The one or more of the plurality of cavities are in fluid communication with an internal volume defined by the internal surface of the base through the one or more of the plurality of perforations. The base, the plurality of supports, and the backing surface can be integrally formed together as a monolithic, load-bearing structure.