James E Putt

US Patent:

6736611, May 18, 2004

Filed:

Oct 23, 2001

Appl. No.:

10/000569

Inventors:

James Putt - Doylestown OH
Michael M. Kugelman - Akron OH

Assignee:

Goodrich Corporation - Charlotte NC

International Classification:

F04B 1700

US Classification:

417386, 417385, 417225, 417401, 92 5 R, 244134 A

Abstract:

An aircraft fluid delivery device ( ) including a piston assembly ( ), a pilot assembly ( ), and a control assembly ( ). The control assembly ( ) includes non-contact proximity sensors (S , S ) that sense the position of the piston ( ) and a controller ( ) that controls the pilot assembly ( ), and thus the piston assembly ( ), based on information received from the sensors (S ,S ). Specifically, the controller ( ) energizes a solenoid ( ) to cause fluid to flow through the pilot assembly ( ) into a large portion of the piston chamber ( ) during the compression stroke of the piston ( ). When the solenoid ( ) is deenergized during the return stroke of the piston ( ), or when the delivery device is electrically turned off, an ejector ( ) in the pilot assembly ( ) generates a vacuum on the pressure side of the wide portion of the piston chamber ( ).

US Patent:

7556221, Jul 7, 2009

Filed:

Jun 28, 2007

Appl. No.:

11/769774

Inventors:

James T. Hindel - Tallmadge OH, US
Michael J. Dorsey - Uniontown OH, US
James C. Putt - Doylestown OH, US
Kyle H. Deiwert - Stow OH, US

Assignee:

Goodrich Corporation - Charlotte NC

International Classification:

B64D 15/00

US Classification:

244134D, 244134 R, 219202

Abstract:

A method of removing a delay-induced ice accumulation (e. g. , an ice cap) from an airfoil's leading-edge region with a zoned electrothermal device. The method comprises delay-rectifying steps which are performed prior to routine-deicing steps. The delay-rectifying steps comprise continuously heating the parting strip (PS), continuously heating the upper fore zone (UF), and continuously heating the lower fore zone (LF). These steps efficiently and effectively remove the delay-induced ice accumulation, whereby routine deicing can be resumed.

US Patent:

20050067532, Mar 31, 2005

Filed:

Sep 23, 2004

Appl. No.:

10/947671

Inventors:

James Hindel - Tallmadge OH, US
David Brittingham - Canton OH, US
Dean Burner - N. Canton OH, US
James Putt - Doylestown OH, US
Richard Cole - Stow OH, US

International Classification:

B64C027/22

US Classification:

24413400D

Abstract:

Radar absorbing electrothermal deicing apparatus for use in deicing an airfoil surface comprises: a heater element including a predetermined area pattern of conductive metallic material; and a layer of radar absorbing material disposed over the heater element. In addition, a method of absorbing radar signals in an electrothermal deicer comprises the steps of: disposing an electrothermal deicing element at a surface of an airfoil; and disposing a layer of dielectric material comprising a filler of magnetic material over the electrothermal deicing element.

US Patent:

50980610, Mar 24, 1992

Filed:

Mar 17, 1989

Appl. No.:

7/325271

Inventors:

Robert N. Hohenshil - Doylestown OH
James C. Putt - Doylestown OH
Richard L. Rauckhorst - North Canton OH
David M. Ronyak - Copley OH

Assignee:

The B. F. Goodrich Company - Akron OH

International Classification:

F16K 3140
B64D 1516

US Classification:

251 3005

Abstract:

A rapid acting valve capable of delivering a high pressure impulse of compressible fluid has a pilot section, and an output section. The output section is pressurized to approximately equilibrium with the inlet pressure during the load portion of the operating cycle. During the dump portion of the operating cycle, the pilot section and output section cooperate to provide extremely rapid full opening of the output section to release fluid under pressure from an accumulator through an output section piston seat. The valve is particularly suitable for use in combination with pneumatic impulse separation systems such as those employed for deicing aircraft surfaces. A plurality of valves may be arranged in series such that dumping of the first tier valve initiates dumping of one or more second tier valves in the series each of which in turn initiates dumping of one or more third tier valves, and so forth until all valves in the series have been actuated, each by its preceding valve.

US Patent:

52883558, Feb 22, 1994

Filed:

Nov 18, 1991

Appl. No.:

7/793906

Inventors:

Kevin L. Leffel - Akron OH
James C. Putt - Doylestown OH
Richard L. Rauckhorst - North Canton OH

Assignee:

The B.F. Goodrich Company - Akron OH

International Classification:

B64D 1500
B29C 4102

US Classification:

156156

Abstract:

A structural member having integral surface de-icing capability and method of manufacture are described. The structural member includes a non-metallic high tensile modulus fiber-reinforced matrix structural backing, thin force and displacement generation means, and a thin high tensile modulus outer skin bonded to said backing and said force and displacement generation means which is postioned between the backing and the skin. The force and displacement generation means may include one or more inflatable tubular members and/or electromagnetic apparatus. The structural member may be substituted for the aluminum alloy leading edge structural skin typically employed on modern aircraft.

US Patent:

48261084, May 2, 1989

Filed:

Jul 16, 1987

Appl. No.:

7/074209

Inventors:

James A. Briscoe - Doylestown OH
James C. Putt - Doylestown OH
Ronald W. Phillips - Mogadore OH
Gary V. Tenison - Massillon OH
Kevin L. Leffel - Akron OH

Assignee:

The B. F. Goodrich Company - Akron OH

International Classification:

B64D 1518

US Classification:

244134A

Abstract:

A de-icer for de-icing those ice accreting surfaces of a skin formed of a material having a substantially elevated modulus, wherein the de-icer is positioned between a support surface and a surface of the skin obverse to the ice accreting surface and inflated to produce a deformation in the skin sufficient to detach and dislodge accumulations of ice on the ice accreting surface but insufficient to exceed an endurance limit for the material from which the skin is formed. The invention finds use in de-icing aircraft surfaces such as wings, tail surfaces, propellers, rotors such as rotating wings, tail rotors and nose cones.

US Patent:

48075159, Feb 28, 1989

Filed:

Apr 3, 1987

Appl. No.:

7/033566

Inventors:

James A. Briscoe - Doylestown OH
James C. Putt - Doylestown OH
Ronald W. Phillips - Mogadore OH

Assignee:

The B. F. Goodrich Company - Akron OH

International Classification:

F04B 1700

US Classification:

91346

Abstract:

An airfoil deicer and method for deicing an airfoil wherein the deicer has an outer skin having an elevated modulus of elasticity and a means for introducing a small deflection into the outer skin thereby creating substantial chord-wise tension in the outer skin, the deflection being induced in less than 0. 250 seconds. In the method of deicing, the deflection is induced periodically and being completed within a time span of about 0. 250 seconds to remove accumulations of ice as thin as 0. 06 centimeters.

US Patent:

48364746, Jun 6, 1989

Filed:

Jul 16, 1987

Appl. No.:

7/074107

Inventors:

James A. Briscoe - Doylestown OH
James C. Putt - Doylestown OH
Ronald W. Phillips - Mogadore OH
Kevin L. Leffel - Akron OH

Assignee:

The B. F. Goodrich Company - Akron OH

International Classification:

B64D 1516

US Classification:

244134A

Abstract:

A de-icer for de-icing those ice accreting surfaces of a skin formed of a material having a substantially elevated modulus, wherein the de-icer is positioned between a support surface and a surface of the skin obverse to the ice accreting surface and inflated to produce a deformation in the skin sufficient to detach and dislodge accumulations of ice on the ice accreting surface but insufficient to exceed an endurance limit for the material from which the skin is formed. The invention finds use in de-icing aircraft surfaces such as wings, tail surfaces, propellers, rotors such as rotating wings, tail rotors and nose cones.