Roger C Clark

US Patent:

6763651, Jul 20, 2004

Filed:

Oct 25, 2002

Appl. No.:

10/280411

Inventors:

Arvin Shmilovich - Huntington Beach CA
Yoram Yadlin - Irvine CA
David M. Smith - Santa Ana CA
Roger W. Clark - Huntington Beach CA

Assignee:

The Boeing Company - Chicago IL

International Classification:

F02G 300

US Classification:

60 39092, 244 53 B

Abstract:

The active system for the wide area suppression of a ground vortex generated by the engine of an aircraft includes an actuator assembly in fluid communication with a fluid source; and, at least one nozzle assembly, including at least one movable nozzle. The movable nozzle is in fluid communication with the actuator assembly for receiving fluid from the actuator assembly. The actuator assembly controls the motion of the movable nozzle, wherein fluid is injected over a desired region relative to an inlet of the engine to disrupt the flow structure of a ground vortex, thus mitigating ground vortex ingestion. This ensures the operational health of the engine during airplane maneuvering on the ground.

US Patent:

7635107, Dec 22, 2009

Filed:

Aug 9, 2005

Appl. No.:

11/200515

Inventors:

Arvin Shmilovich - Huntington Beach CA, US
Yoram Yadlin - Irvine CA, US
Roger W. Clark - Huntington Beach CA, US
David J. Manley - Huntington Beach CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 21/04

US Classification:

244207, 244208

Abstract:

A system and method for controlling boundary layer flow over an aircraft wing are provided. The system includes at least one wing element, and a plurality of ports defined in the wing element and in fluid communication with one another. The system also includes at least one fluidic device operable to continuously ingest the fluid through at least one of the ports and eject the fluid out of at least one other port to control boundary layer flow of the fluid over the wing element.

US Patent:

7661629, Feb 16, 2010

Filed:

Mar 7, 2006

Appl. No.:

11/370099

Inventors:

Arvin Shmilovich - Huntington Beach CA, US
Yoram Yadlin - Irvine CA, US
Roger W. Clark - Huntington Beach CA, US
Donald H. Leopold - Rancho Santa Margarita CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 23/00
B64C 21/04

US Classification:

2441992, 244207

Abstract:

Apparatuses and methods for the controlled trailing wake flows. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device carried by the airfoil, with the vortex dissipation device including a fluid flow nozzle, a valve device, and a controller. The fluid flow nozzle can be coupleable to a source of pressurized fluid and can include an orifice positioned to direct a flow of fluid outwardly from the tip. The valve device can be coupled in fluid communication with the fluid flow nozzle to selectively control the flow passing through the orifice. The controller can be coupled to the valve device to direct the operation of the valve device. Accordingly, the vortex dissipation device can be activated to accelerate the rate at which vortices (e. g.

US Patent:

7669785, Mar 2, 2010

Filed:

Apr 24, 2006

Appl. No.:

11/379971

Inventors:

Arvin Shmilovich - Huntington Beach CA, US
Yoram Yadlin - Irvine CA, US
David M. Smith - Santa Ana CA, US
Roger W. Clark - Huntington Beach CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B63H 11/10

US Classification:

23926519, 23926543, 244 73 R, 60771

Abstract:

Integrated engine exhaust systems and methods for reducing drag and thermal loads are disclosed. In one embodiment, a propulsion system includes an engine installation configured to be mounted on a wing assembly of an aircraft. The engine installation includes an engine, and an exhaust system operatively coupled to the engine. The exhaust system includes at least one nozzle configured to exhaust an exhaust flow from the engine. The nozzle includes a variable portion configured to vary an exit aperture of the nozzle from a first shape to a second shape to change a flowfield shape of at least a portion of the nozzle flowfield proximate the wing assembly, thereby reducing at least one of drag and thermal loading on the wing assembly. In a further embodiment, the exhaust system includes an inner nozzle that exhausts a core exhaust flow, and an outer nozzle that exhausts a secondary exhaust flow, the outer nozzle having the variable portion configured to vary the exit aperture of the outer nozzle.

US Patent:

7726609, Jun 1, 2010

Filed:

Mar 16, 2007

Appl. No.:

11/687595

Inventors:

Arvin Shmilovich - Huntington Beach CA, US
Yoram Yadlin - Irvine CA, US
Roger W. Clark - Huntington Beach CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 21/04

US Classification:

244207, 244204, 244212

Abstract:

Aircraft exhaust systems and methods are disclosed. In one embodiment, an integrated propulsion assembly includes a wing assembly having an upper surface and a lower surface, and a propulsion unit at least partially disposed within the wing assembly. An exhaust system is configured to conduct an exhaust flow emanating from the propulsion unit to an exhaust aperture. The exhaust aperture is positioned proximate a trailing edge of the wing assembly, and has an aspect ratio of at least five. In further embodiments, the wing assembly includes a flap member moveably coupled along a trailing edge portion of the wing assembly, and the exhaust aperture is configured to direct the exhaust flow over at least a portion of the flap member.

US Patent:

7798423, Sep 21, 2010

Filed:

Jan 13, 2010

Appl. No.:

12/686639

Inventors:

Arvin Shmilovich - Hungtington Beach CA, US
Yoram Yadlin - Irvine CA, US
David M. Smith - Santa Ana CA, US
Roger W. Clark - Huntington Beach CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B63H 11/10

US Classification:

23926519, 23926543, 244 73 R, 60771

Abstract:

Integrated engine exhaust systems and techniques for operating integrated engine exhaust systems are disclosed. In one embodiment, a propulsion system includes an engine installation configured to be mounted on a wing assembly of an aircraft. The engine installation includes an engine, and an exhaust system operatively coupled to the engine. The exhaust system includes at least one nozzle to exhaust an exhaust flow from the engine. The nozzle includes a variable portion configured to vary an exit aperture of the nozzle from a first shape to a second shape to change a flowfield shape of at least a portion of the nozzle flowfield proximate the wing assembly, thereby reducing at least one of drag and thermal loading on the wing assembly. In a further embodiment, the exhaust system includes an inner nozzle that exhausts a core exhaust flow, and an outer nozzle that exhausts a secondary exhaust flow, the outer nozzle having the variable portion configured to vary the exit aperture of the outer nozzle.

US Patent:

7823840, Nov 2, 2010

Filed:

Oct 29, 2007

Appl. No.:

11/927257

Inventors:

Arvin Shmilovich - Huntington Beach CA, US
Yoram Yadlin - Irvine CA, US
Roger W. Clark - Huntington Beach CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 3/50

US Classification:

244215, 244213, 244198

Abstract:

Coanda Effect and lift produced along a surface of an airfoil are increased by ducting compressed fluid from the engine to the surface of the airfoil. An engine produces exhaust gases that are predominantly directed toward an aft end of the aircraft by a cowling or other structure as an exhaust plume. One or more internal ducts extend from the engine to the surface of the airfoil to thereby transmit a compressed fluid from the engine to the surface in order to suppress flow separation along the surface, thereby causing the engine exhaust flow to remain attached to the surface over a wider span. Such structures and techniques may find particular use in aircraft designed to exploit upper surface blowing (USB) techniques and structures for short takeoff and landing (STOL) performance.

US Patent:

7878458, Feb 1, 2011

Filed:

Oct 29, 2007

Appl. No.:

11/927290

Inventors:

Arvin Shmilovich - Huntington Beach CA, US
Yoram Yadlin - Irvine CA, US
Roger W. Clark - Huntington Beach CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 21/04

US Classification:

244207, 244215, 244 125

Abstract:

Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling extends outwardly from the surface of the airfoil that has an exit plane configured for directing exhaust gases toward a rear of the aircraft. Fences extending outwardly from the surface and proximate to the exit plane of the engine cowling are configured to guide the exhaust gases along at least a portion of the airfoil surface, thereby restricting spanwise movement of the gases and increasing the Coanda Effect exhibited by the gases, thereby increasing the amount of lift produced along the surface of the airfoil. Such techniques may be used in short take-off and landing (STOL) aircraft.

Address:

2089 Homecoming Way, Brentwood, CA 94513

Phone:

(925)4206595

VIN:

1D7HU18257S223884

Make:

DODGE

Model:

RAM PICKUP 1500

Year:

2007