Stuart J Byrne, 6411551 Corte Playa Las Brisas, San Diego, CA 92124

7047725, May 23, 2006

May 28, 2003

10/446896

Jeffrey W. Moe - Chula Vista CA, US
Stuart J. Byrne - San Diego CA, US
Norman J. James - San Diego CA, US
Ricardo A. Burdisso - Blacksburg VA, US

Rohr, Inc. - Chula Vista CA

B64F 1/26

60262, 181210, 181214

An assembly useful in reducing aircraft engine noise such as turbofan engine noise comprises: (a) a core portion comprising at least one entrance end and at least one exit end for the passage of acoustic energy therethrough; (b) a first member having an exterior face and an interior face, wherein the first member is adjacent to at least a part of the core portion, and the first member has a plurality of openings therein to permit the passage of acoustic energy therethrough; and (c) a second member having an exterior face and an interior face, wherein the interior face of the second member is adjacent to the core portion. The core portion may be a honeycomb acoustic structure, and the first member may be perforated to permit the passage of acoustic energy into and out of the conduit portion.

7055648, Jun 6, 2006

Oct 2, 2001

10/343567

Stuart Byrne - San Diego CA, US
Jeffrey W. Moe - Chula Vista CA, US

Rohr, Inc. - Chula Vista CA

F02K 1/08
F01N 1/06
F01N 1/18
F02B 27/02

181241, 181216, 181253, 181271, 181277, 181219, 60312, 602263, 381 715

An assembly useful in reducing aircraft engine noise such as turbofan engine noise () comprises: (i) at least one tube “H-Q” having an inlet end (), an outlet end () and a central tube portion therebetween; and (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube. The assembly of this invention may be used in a method for reducing noise, the method comprising: (a) providing means for generating non-uniform noise energy about an inner surface and within a disclosure having at least an inlet; (b) providing an assembly for reducing noise comprising; (i) at least one having an inlet end, an outlet end and a central tube portion therebetween, and (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube; and (c) directing at least a portion of the non-uniform noise into the assembly.

7416051, Aug 26, 2008

Jun 2, 2006

11/445734

Stuart Byrne - San Diego CA, US
Jeffrey W. Moe - Chula Vista CA, US

Rohr, Inc. - Chula Vista CA

F01N 1/06

181254, 181253, 181241, 181271, 181206, 60322, 602263, 415145, 415119

An assembly useful in reducing aircraft engine noise such as turbofan engine noise () comprises: (1) at least one tube “H-Q” having an inlet end (), an outlet end () and a central tube portion therebetween; an (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube. The assembly of this invention may be used in a method for reducing noise, the method comprising: (a) providing means for generating non-uniform noise energy about an inner surface and within a disclosure having at least an inlet; (b) providing an assembly for reducing noise comprising; (i) at least one tube having an inlet end, an outlet end and a central tube portion therebetween, and (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube; and (c) directing at least a portion of the non-uniform noise into the assembly.

2004007, Apr 29, 2004

Oct 29, 2002

10/282550

Jihad Ramlaoui - Chula Vista CA, US
Randall Seaver - Chula Vista CA, US
Norman James - San Diego CA, US
Stuart Byrne - San Diego CA, US
Sheila Cornejo - San Diego CA, US

F02K001/54

060/226200

A thrust reverser for a turbofan engine having an air duct defined radially inwardly by a wall around the turbofan engine and radially outwardly in part by a fan cowl of the engine. A bulkhead is adapted to be mounted on the fan cowl having a shaped surface defining an upstream wall. A translating cowl is supported for movement axially between a closed position substantially adjacent the bulkhead and an open position spaced axially apart from the bulkhead so as to form an outlet for discharge of air from the air duct. The translating cowl has a first wall and a kicker plate defining a shaped surface. The kicker plate and/or the bulkhead may have a dimension which varies at different radial locations about a circumference of the translating cowl to selectively control the forward component of velocity of the air discharged from the air duct. A plume control device may extend longitudinally across the outlet to divide the air discharged from the air duct into a plurality of plumes. A vane spaced axially aft from the bulkhead has an airfoil section to guide air to the outlet in order to control turning and area match when the translating cowl is in the deployed position.

2020029, Sep 17, 2020

Mar 12, 2019

16/299992

- Chula Vista CA, US
Vijay V. Pujar - San Diego CA, US
Stuart J. Byrne - San Diego CA, US
Adam G. Saunders - Chula Vista CA, US
Gary Euan Bowman - Lenzie, GB

ROHR, INC. - Chula Vista CA

F02K 1/80
F02C 7/20
F01D 25/00

A nacelle system is disclosed. In various embodiments, the nacelle system may include a nacelle component; an attachment structure; and a bracket configured to secure the nacelle component to the attachment structure, the bracket comprising a first arm having a first bead structure disposed between a proximal end and a distal end of the bracket.

2017000, Jan 12, 2017

Jul 7, 2015

14/793429

- Chula Vista CA, US
STUART BYRNE - San Diego CA, US

ROHR, INC. - Chula Vista CA

F02K 1/76

A nacelle may include a tertiary lock for a thrust reverser. The tertiary lock may comprise a locking face which prevents the thrust reverser from accidentally deploying. An actuator may be coupled to a track beam. The actuator may contact a left tertiary lock and a right tertiary lock to disengage the locks. The locks may rotate and allow the thrust reverser to deploy. A spring may bias the locks to engage when the thrust reverser returns to the stowed position.

2017000, Jan 5, 2017

Sep 16, 2016

15/267547

- Chula Vista CA, US
Stuart J. Byrne - San Diego CA, US

ROHR, INC. - Chula Vista CA

F01D 25/04
F16F 15/02
F01D 25/26
B64D 29/06
B64D 27/10

A compression rod may include a plunger and a spring. A proximal end and a distal end of the compression rod may contact engagement features in a core cowl of a gas turbine engine. The compression rod may transmit loads between halves of the core cowl. The spring may cause the plunger to extend and contract in response to vibrations or other relative movement between halves of the core cowl.

2016037, Dec 29, 2016

May 15, 2015

14/713621

- Chula Vista CA, US
Stuart J. Byrne - San Diego CA, US
Steven M. Kestler - Winchester CT, US

B64C 21/06
B64D 33/02
B64D 29/00

A nacelle is provided for an aircraft propulsion system. The nacelle may include an outer barrel and an active laminar flow control system. The active laminar flow control system may include a plurality of suction sources and a plurality of arrays of perforations in the outer barrel. The active laminar flow control system may be configured with a plurality of zones. Each of the zones may include a respective one of the suction sources which is fluidly coupled with a respective one of the arrays of perforations in the outer barrel.