公开(公告)号：US10971128B2

公开(公告)日：2021-04-06

申请号：US15559180

申请日：2015-04-10

Applicant: MRA Systems, LLC

Inventor： Andrew Michael Roach ,  Graham Frank Howarth ,  Steven Thomas Davies ,  Richard David Cedar ,  Michael Moses Martinez ,  Timothy Richard Depuy

IPC: G10K11/172 ,  G10K11/168 ,  B24C1/04

Abstract: An acoustic liner (20) with perforation (30) and method of constructing (100) an acoustic liner including forming perforations in the facing sheet by grit blasting (104) the facing sheet and mounting (106) the facing sheet to one side of a support layer having a set of partitioned cavities wherein the facing sheet closes an open face of the cavities except for the perforations to form a set of acoustic resonator cells.

公开(公告)号：US10961913B2

公开(公告)日：2021-03-30

申请号：US15553207

申请日：2015-03-10

Applicant: MRA SYSTEMS, LLC

Inventor： Graham Frank Howarth ,  Andrew Michael Roach ,  Steven Thomas Davies ,  Richard David Cedar ,  Michael Moses Martinez ,  Timothy Richard DePuy

IPC: F02C7/24 ,  F02C7/045 ,  G10K11/172 ,  F02K1/82

Abstract: An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a facing sheet operably coupled to the support layer such that the facing sheet overlies and closes the open faces, a set of perforations located in the facing sheet and in fluid communication with a corresponding one of the cavities to form a set of acoustic resonators, and at least a subset of the perforations have an axially-oriented, relative to the axial flow path, inlet.

公开(公告)号：US20190063318A1

公开(公告)日：2019-02-28

申请号：US15689699

申请日：2017-08-29

Applicant: MRA Systems, LLC.

Inventor： Andrew Michael Roach ,  Graham Frank Howarth

IPC: F02C7/045 ,  B64D33/02 ,  B64D29/00 ,  E04B1/84

Abstract: An acoustic liner can include a support layer with a set of partitioned cavities defining a set of cells with open faces, a first facing sheet operably coupled to the support layer such that the first facing sheet overlies and closes the open faces, and a set of internal separator structures within at least some of the set of partitioned cavities.

公开(公告)号：US20190048824A1

公开(公告)日：2019-02-14

申请号：US15674164

申请日：2017-08-10

Applicant: MRA Systems, LLC.

Inventor： David Patrick Calder ,  Keith EJ Blodgett ,  Graham Frank Howarth ,  Andrew Michael Roach

IPC: F02K1/62 ,  F02C3/04 ,  F01D25/24 ,  F01D9/02 ,  F02K1/76

Abstract: A thrust reverser assembly for a turbine engine can include a core engine surrounded by a nacelle. A bypass duct can be formed in the space between the core engine and the nacelle. A blocker door can be movable to a deployed position extending into the bypass duct. A stop can be provided on the core engine to abut and support force applied to the deployed blocker door. The stop can have an airfoil shape.

公开(公告)号：US11149686B2

公开(公告)日：2021-10-19

申请号：US16363157

申请日：2019-03-25

Applicant: MRA Systems, LLC

Inventor： David Patrick Calder ,  Graham Frank Howarth ,  Andrew Michael Roach ,  Timothy Robert Beasman

IPC: F02K1/70 ,  F02K1/76 ,  F02K3/06

Abstract: A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine defining a bypass duct between the nacelle and the core engine where an outer door movable between a stowed position and a deployed position extends outwards from the nacelle and a blocker door movable between a stowed position and a deployed position extends into an airflow conduit defined by the bypass duct to deflect air outwards.

公开(公告)号：US20180245515A1

公开(公告)日：2018-08-30

申请号：US15442158

申请日：2017-02-24

Applicant: MRA Systems, LLC

Inventor： Andrew Michael Roach ,  David Patrick Calder ,  Graham Frank Howarth

IPC: F02C7/24 ,  B32B3/26 ,  B32B5/18 ,  B32B3/12 ,  B32B15/04 ,  B32B15/20 ,  F02K3/06 ,  F02C7/045

CPC classification number: F02C7/24 ,  B32B3/12 ,  B32B3/266 ,  B32B5/18 ,  B32B15/046 ,  B32B15/20 ,  B32B2307/102 ,  B32B2307/7265 ,  B32B2605/18 ,  F02C7/045 ,  F02K3/06 ,  F05D2220/323 ,  F05D2250/283 ,  F05D2260/963 ,  F05D2300/601 ,  F05D2300/612 ,  Y02T50/672

Abstract: An acoustic liner can include a support layer having a set of partitioned cavities with open faces, a first facing sheet and second facing sheet both having perforations and operably coupled to the support layer such that the facing sheets overlie and close the open faces, and an aerogel layer operably coupled to the second facing sheet.

公开(公告)号：US10578055B2

公开(公告)日：2020-03-03

申请号：US15674164

申请日：2017-08-10

Applicant: MRA Systems, LLC.

Inventor： David Patrick Calder ,  Keith E J Blodgett ,  Graham Frank Howarth ,  Andrew Michael Roach

IPC: F02K1/72 ,  F02K1/62 ,  F01L9/02 ,  F01D25/24 ,  F02C3/04 ,  F02K1/76

Abstract: A thrust reverser assembly for a turbine engine can include a core engine surrounded by a nacelle. A bypass duct can be formed in the space between the core engine and the nacelle. A blocker door can be movable to a deployed position extending into the bypass duct. A stop can be provided on the core engine to abut and support force applied to the deployed blocker door. The stop can have an airfoil shape.

公开(公告)号：US20200025136A1

公开(公告)日：2020-01-23

申请号：US16363157

申请日：2019-03-25

Applicant: MRA Systems, LLC

Inventor： David Patrick Calder ,  Graham Frank Howarth ,  Andrew Michael Roach ,  Timothy Robert Beasman

IPC: F02K1/70 ,  F02K1/76

Abstract: A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine defining a bypass duct between the nacelle and the core engine where an outer door movable between a stowed position and a deployed position extends outwards from the nacelle and a blocker door movable between a stowed position and a deployed position extends into an airflow conduit defined by the bypass duct to deflect air outwards.

公开(公告)号：US20190257268A1

公开(公告)日：2019-08-22

申请号：US15898723

申请日：2018-02-19

Applicant: MRA Systems, LLC.

Inventor： Andrew Michael Roach ,  Graham Frank Howarth ,  David Patrick Calder

IPC: F02K1/72

Abstract: A thrust reverser cascade can include a peripheral frame having at least one side. At least one plate can be mounted to the at least one side and have a plurality of spaced grooves. In addition, a plurality of vanes can include corresponding terminal ends positioned in the plurality of spaced grooves.

公开(公告)号：US10995699B2

公开(公告)日：2021-05-04

申请号：US15898723

申请日：2018-02-19

Applicant: MRA Systems, LLC.

Inventor： Andrew Michael Roach ,  Graham Frank Howarth ,  David Patrick Calder

IPC: F02K1/72 ,  F02K1/54 ,  F02K1/64

Abstract: A thrust reverser cascade can include a peripheral frame having at least one side. At least one plate can be mounted to the at least one side and have a plurality of spaced grooves. In addition, a plurality of vanes can include corresponding terminal ends positioned in the plurality of spaced grooves.