George N Massey

US Patent:

20130068862, Mar 21, 2013

Filed:

Sep 19, 2012

Appl. No.:

13/622447

Inventors:

George N. Massey - Valley Center KS, US

Assignee:

JOHNSON AIRSPRAY, INC. - Argyle MN

International Classification:

B05B 5/043

US Classification:

2396901

Abstract:

An apparatus for spraying and inducing an electrostatic charge upon a liquid in excess of 0.8 millicoloumb/kilogram is connectable to a boom fitted to a vehicle, such as an aircraft, having a dc power supply. The apparatus comprises a nozzle constructed from a substantially non-conductive material and includes a spray tip designed to provide a hollow conical spray pattern. A support member extends from the nozzle and supports a charging electrode for inducing an electrostatic charge upon the liquid sprayed through the nozzle. The charging electrode attaches to the support member and is electrically connectable to the dc power supply. The charging electrode includes a cylindrical portion and a plurality of corona discharge members extending inwardly from a distal end of the cylindrical portion adjacent to the spray tip. The charging electrode is positioned to permit the hollow conical spray pattern to pass unhindered therethrough.

US Patent:

61787361, Jan 30, 2001

Filed:

Dec 3, 1999

Appl. No.:

9/454407

Inventors:

George Massey - Valley Center KS

Assignee:

Lamar Technologies Corporation - Marysville WA

International Classification:

F02C 7268

US Classification:

60 3902

Abstract:

Turbine aircraft engine starter systems and controllers for use therewith, and methods of starting turbine aircraft engines are described. A starter is operably connected with an aircraft engine and configured to initiate an engine start cycle which includes engine rotation and a fuel ignition point. A power source is connected with the starter and is configured to provide power thereto in accordance with at least first and second settings which apply different magnitudes of voltage to the starter. The first setting initiates the engine start cycle and the second setting accelerates the engine through the start cycle after the fuel ignition point. A controller is operably connected with the starter and the power source and is configured to monitor the engine start cycle and responsive to a controller-determinable time during the engine start cycle changes the first setting to the second setting. In a preferred implementation, the power source comprises a pair of batteries which are permanently connected in series.

US Patent:

6018941, Feb 1, 2000

Filed:

Sep 19, 1997

Appl. No.:

8/933874

Inventors:

George Massey - Valley Center KS

Assignee:

Lamar Technologies Corporation - Marysville WA

International Classification:

F02C 7268

US Classification:

60 39142

Abstract:

Turbine aircraft engine starter systems and controllers for use therewith, and methods of starting turbine aircraft engines are described. A starter is operably connected with an aircraft engine and configured to initiate an engine start cycle which includes engine rotation and a fuel ignition point. A power source is connected with the starter and is configured to provide power thereto in accordance with at least first and second settings which apply different magnitudes of voltage to the starter. The first setting initiates the engine start cycle and the second setting accelerates the engine through the start cycle after the fuel ignition point. A controller is operably connected with the starter and the power source and is configured to monitor the engine start cycle and responsive to a controller-determinable time during the engine start cycle changes the first setting to the second setting. In a preferred implementation, the power source comprises a pair of batteries which are permanently connected in series.

US Patent:

61348759, Oct 24, 2000

Filed:

Dec 3, 1999

Appl. No.:

9/454408

Inventors:

George Massey - Valley Center KS

Assignee:

Lamar Technologies Corporation - Marysville WA

International Classification:

F02C 7268

US Classification:

60 39142

Abstract:

Turbine aircraft engine starter systems and controllers for use therewith, and methods of starting turbine aircraft engines are described. A starter is operably connected with an aircraft engine and configured to initiate an engine start cycle which includes engine rotation and a fuel ignition point. A power source is connected with the starter and is configured to provide power thereto in accordance with at least first and second settings which apply different magnitudes of voltage to the starter. The first setting initiates the engine start cycle and the second setting accelerates the engine through the start cycle after the fuel ignition point. A controller is operably connected with the starter and the power source and is configured to monitor the engine start cycle and responsive to a controller-determinable time during the engine start cycle changes the first setting to the second setting. In a preferred implementation, the power source comprises a pair of batteries which are permanently connected in series.