Byron R Spain

US Patent:

62798421, Aug 28, 2001

Filed:

Feb 29, 2000

Appl. No.:

9/515342

Inventors:

Byron Spain - Maple Valley WA

Assignee:

Rodi Power Systems, Inc. - Puyallup WA

International Classification:

F02M 6100

US Classification:

2395851

Abstract:

Various embodiments of a fuel injector are provided for use in an internal combustion engine. Each embodiment uses an assembly that incorporates a magnetostrictive rod to extend and retract a needle to control fuel expulsion from the injector. In one embodiment, the fuel injector includes an actuation assembly and a nozzle assembly releasably connected thereto In another embodiment, the fuel injector includes a pintle-style needle tip. In yet other embodiments, the fuel injector includes a long-stem style needle tip.

US Patent:

46358820, Jan 13, 1987

Filed:

Apr 18, 1985

Appl. No.:

6/724787

Inventors:

Gautam SenGupta - Renton WA
Byron R. Spain - Mulvane KS

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 100

US Classification:

244119

Abstract:

A method and apparatus for reducing the low to mid frequency interior noise of a reinforced skin structure, such as the cabin of a jet aircraft, by reducing the vibration response of the structure to low to mid frequency disturbances is disclosed. Interior noise is reduced by forming the structure such that the skin panels bounded by reinforcing components have a higher fundamental frequency than the combined bending and tuning fork frequency of reinforcing components with spaced apart legs that support the skin; and, damping the bending, tuning fork and torsional vibration of the reinforcing components. Damping is accomplished by bridging the spaced apart legs of the reinforcing components with rigid elements, viscoelastically attached at either end to the legs. Preferably, the viscoelastic attachment is via flanges that extend outwardly from the legs. The entire length of the reinforcing components may be spanned by a single rigid element; or, a series of spaced apart rigid elements may span the reinforcing components.

US Patent:

48282022, May 9, 1989

Filed:

Aug 31, 1981

Appl. No.:

6/297945

Inventors:

Loyd D. Jacobs - Bellevue WA
Gautam SenGupta - Benton WA
Byron R. Spain - Mulvane KS

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 106

US Classification:

244117R

Abstract:

A method and apparatus for damping the vibration of a reinforced skin structure (e. g. , the fuselage of an aircraft) over a wide frequency range (wideband) in order to reduce the vibration and transmitted noise, and improve the sonic fatigue life, of the structure is disclosed. Wide range damping is accomplished by viscoelastically attaching constraining elements, which can be continuous or segmented, to the skin and to the reinforcing members that support the skin. The viscoelastic attachment between the constraining elements and the reinforcing members directly damp the vibrations of the reinforcing members; and, the viscoelastic attachment between the constraining elements and the skin directly damp the vibrations of the skin. Further, the regions of the constraining elements extending between the regions viscoelastically attached to the reinforcing members and to the skin forms a coupling that allows the skin viscoelastic attachment to indirectly damp the vibrations of the reinforcing member and vice versa. Resonant vibrations due to skin bending, torsional and extensional modes (both cylindrical and panel) and reinforcing member bending, torsional, extensional and tuning fork modes, are all damped.