Paul N Sherrill

US Patent:

8286908, Oct 16, 2012

Filed:

Jul 15, 2005

Appl. No.:

11/632421

Inventors:

John M. Kebrle - Dallas TX, US
Justin Daw - Fort Worth TX, US
Jim Hurdle - Fort Worth TX, US
Paul Sherrill - Grapevine TX, US
Jimmy C. Narramore - Bedford TX, US
Sidney Xue - Colleyville TX, US
Charles Hollimon - Fort Worth TX, US
Dudley Smith - Arlington TX, US
Bryce Docker - Arlington TX, US
John T. Brieger - Colleyville TX, US

Assignee:

Bell Helicopter Textron Inc. - Hurst TX

International Classification:

B64C 27/82

US Classification:

244 1719, 416203

Abstract:

A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub.

US Patent:

8632310, Jan 21, 2014

Filed:

Dec 18, 2007

Appl. No.:

12/808201

Inventors:

Bryan Marshall - Mansfield TX, US
Paul Sherrill - Grapevine TX, US
Bryan K. Baskin - Arlington TX, US
Tricia Hiros - Haltom City TX, US
Paul K. Oldroyd - Azle TX, US

Assignee:

Textron Innovations Inc. - Providence RI

International Classification:

B64C 27/473

US Classification:

416226

Abstract:

A helicopter rotor blade includes a structural composite skin defining a cavity therein; a composite spar disposed within the cavity and adhesively bonded to the skin, a portion of the spar exhibiting a C-shape in cross section; and a foam core disposed within the cavity and adhesively bonded to the skin. The structural composite skin forms an external, closed box structure configured to transmit mechanical loads encountered by the rotor blade.

US Patent:

8640984, Feb 4, 2014

Filed:

Aug 7, 2012

Appl. No.:

13/568262

Inventors:

John M. Kebrle - Dallas TX, US
James R. Andrews - Mansfield TX, US
Justin Daw - Fort Worth TX, US
Jim Hurdle - Fort Worth TX, US
Paul Sherrill - Grapevine TX, US
Jimmy C. Narramore - Bedford TX, US
Sidney Xue - Colleyville TX, US
Charles Hollimon - Forth Worth TX, US
Dudley Smith - Arlington TX, US
Bryce Docker - Arlington TX, US
John T. Brieger - Colleyville TX, US

Assignee:

Bell Helicopter Textron Inc. - Hurst TX

International Classification:

B64C 27/82

US Classification:

244 1719, 416203

Abstract:

A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub.

US Patent:

20080101934, May 1, 2008

Filed:

Jan 24, 2006

Appl. No.:

11/794850

Inventors:

Frank B. Stamps - Colleyville TX, US
Patrick R. Tisdale - Roanoke TX, US
Paul Sherrill - Grapevine TX, US
Richard Rauber - Arlington TX, US
Thomas C. Campbell - Keller TX, US
James Lee Braswell Jr. - Colleyville TX, US
Ron Measom - Hurst TX, US
Tricia Hiros - Hurst TX, US
David Popelka - Colleyville TX, US
Michael J. Southerland - North Richland Hills TX, US
Keith Stanney - Dallas TX, US
Mark Wasikowski - Keller TX, US
Tim Ledbetter - Hurst TX, US

International Classification:

B64C 11/12
B64C 27/48

US Classification:

416134 A

Abstract:

An assembly for providing flexure to a blade of a rotary blade system includes an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween. At least one of the upper and lower yoke surfaces has a layer of cushioning material positioned thereon and secured thereto. An alternate embodiment includes an assembly for providing flexure to a blade of a rotary blade system, including, an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween and directly contacting the support plates wherein one of the curved surfaces is a non-circular arc that does not form part of the circumference of a circle. Another alternate embodiment includes a similar assembly having a twist-shank type of yoke for providing rotation of attached blades about their respective pitch axes.

US Patent:

20120301299, Nov 29, 2012

Filed:

Nov 12, 2010

Appl. No.:

13/578975

Inventors:

Paul B. Sherrill - Grapevine TX, US
Frank B. Stamps - Colleyville TX, US
Ronald J. Measom - Hurst TX, US

Assignee:

Bell Helicopter Textron Inc. - Ft. Worth TX

International Classification:

F01D 5/16
B32B 37/00
B32B 7/02

US Classification:

416144, 428218, 1563071

Abstract:

A rotor blade for an aircraft includes a composite portion having fiber-reinforced resin material, the composite portion having an outside surface that forms at least a partial airfoil shape. The weighted portion includes a plurality of weighted material layers and a plurality of fiber-reinforced resin material layers. Weighted material is configured to be compatible with and integrated into composite manufacturing processes used to fabricate the rotor blade. The weighted portion has a higher density than the composite portion and positioned to produce desired mass balance characteristics of the rotor blade.

US Patent:

20120305698, Dec 6, 2012

Filed:

Nov 4, 2010

Appl. No.:

13/577633

Inventors:

Troy C. Schank - Keller TX, US
Peter H. Kitzinger - Grapevine TX, US
Paul B. Sherrill - Grapevine TX, US
Thomas C. Parham - Colleyville TX, US
David A. Popelka - Colleyville TX, US

Assignee:

BELL HELICOPTER TEXTRON INC. - Fort Worth TX

International Classification:

B64C 27/615
B64C 13/30

US Classification:

244 1711, 244 993, 244213

Abstract:

A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a cross-axis flexure pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements.

US Patent:

20130082136, Apr 4, 2013

Filed:

Nov 1, 2010

Appl. No.:

13/703813

Inventors:

Troy C Schank - Keller TX, US
Peter H Kintzinger - Grapevine TX, US
Paul B Sherrill - Grapevine TX, US
Thomas Parham - Colleyville TX, US

Assignee:

BELL HELICOPTER TEXTRON INC. - FORT WORTH TX

International Classification:

B64C 13/26
F16H 21/44
B64C 27/00

US Classification:

244 1711, 244 992, 74469, 74103

Abstract:

A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements.

US Patent:

20130287571, Oct 31, 2013

Filed:

Apr 15, 2013

Appl. No.:

13/862515

Inventors:

Paul B. Sherrill - Grapevine TX, US
Robert A. Self - Euless TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

F01D 5/14

US Classification:

416146 R

Abstract:

The electrical harness system is configured for routing a harness between a rotor yoke and a rotor blade. A recess in an inboard cap member is configured to house a connector and an associated harness. As the recess extends along a radial path in the chordwise direction of the rotor blade, the harness is configured to lie within the recess. Operationally induced centrifugal forces promote positioning the slack of harness within the recess, while the slack in the harness remains available for relative dynamic movements between the rotor blade and the rotor yoke. Such a routing of the harness reduces aerodynamic drag and minimizes damage that could otherwise occur to the harness.