Paul M Bevilaqua

US Patent:

6641082, Nov 4, 2003

Filed:

Apr 1, 2002

Appl. No.:

10/112144

Inventors:

Paul Bevilaqua - Newhall CA
Patrick Tait - Sagus CA

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B64D 500

US Classification:

244 2, 244189

Abstract:

The invention is a system for ferrying at least one aircraft by a ferrying aircraft, the at least one aircraft and ferrying aircraft having vehicle management systems. In detail, the invention includes an attachment device for joining a wing tip of the at least one aircraft to one of the wing tips of the ferrying aircraft. A system is included for controlling the at least one aircraft and the ferrying aircraft such that the at least one aircraft flight characteristics are controlled by the ferrying aircraft. The method of ferrying a at least one aircraft by a ferrying aircraft from a first point to a second point includes the steps of: flying the at least one aircraft and ferrying aircraft; while in flight at the first point, joining a wing tip of the at least one aircraft to one of the wing tips of ferrying aircraft; and controlling the flight characteristics of the joined at least one aircraft such that the at least one aircraft and ferrying aircraft become a single aircraft controlled by the ferrying aircraft as the jointed aircraft fly toward the second point.

US Patent:

6729575, May 4, 2004

Filed:

Apr 1, 2002

Appl. No.:

10/112145

Inventors:

Paul Bevilaqua - Newhall CA

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B64D 2702

US Classification:

244 123, 244 53 R, 244 55, 244 23 D

Abstract:

The invention is a propulsion system for a V/STOL aircraft. In detail, the invention includes a turbo-fan engine having a fan section with a variable pitch fan, a compressor section, a combustion section, a turbine section, said turbine section having a low-pressure turbine portion coupled to and driving the fan section and a high-pressure turbine portion coupled to and driving the compressor section. The engine further having a selectable operating point wherein a portion of the power generatable by the low-pressure turbine at a selected operating power setting is extracted to drive the fan section. A turbine outlet duct is included for directing the turbine section exhaust gases. A first angular shaped nozzle section is co-incident with the turbine outlet duct for directing exhaust from the fan section. A second nozzle section mounted to the first angular shaped nozzle section between the fan section and the compressor section. A system is included to shift said selectable operating point of said engine to a second operating point at the selected power setting increasing the power extracted by the low-pressure turbine portion of the turbine section; such that power extracted by the low-pressure turbine portion and applied to the fan section can be increased without changing the selected power setting and the pitch of the blades of the variable pitch fan section can be increased to absorb the increased power.

US Patent:

46451404, Feb 24, 1987

Filed:

Aug 18, 1983

Appl. No.:

6/524481

Inventors:

Paul M. Bevilaqua - Dublin OH
John H. Dehart - Powell OH

Assignee:

Rockwell International Corporation - El Segundo CA

International Classification:

B64C 2104
B64D 3304

US Classification:

244 121

Abstract:

A nozzle system for providing improved thrust augmentation for an aircraft lift and/or propulsion system is provided. The unique nozzle structure is designed such that counter-rotating vortices emanate from the nozzle tips. When this unique nozzle configuration is combined with simple slot nozzles in a specific manner a vortex rich flow will result. When a diffuser is placed around this unique combination such that jet pumping is obtained, significant improvement in thrust augmentation is realized from the vortex rich flow mixing with the coflowing secondary air stream.

US Patent:

45199906, May 28, 1985

Filed:

May 24, 1983

Appl. No.:

6/497617

Inventors:

Paul M. Bevilaqua - Dublin OH
Stanley J. Stachura - Woodland Hills CA

Assignee:

Rockwell International Corporation - El Segundo CA

International Classification:

B01D 116

US Classification:

423210

Abstract:

A spray dryer apparatus for contacting a hot gas stream containing gaseous impurities with an aqueous medium containing an absorbent for the impurities to produce a gas stream of reduced impurity content and dried powder products. The apparatus includes a chamber formed symmetrically about a vertical axis and an atomizer means located in an upper portion of the chamber for introducing a finely dispersed spray of the aqueous medium, a conduit for delivering the hot gas stream to the chamber and a gas injection means for receiving a major portion of the hot gas stream from the conduit and introducing it circumferentially about the atomizer means. The gas injection means imparts both axial and angular velocity components to the major portion of the hot gas stream whereby the hot gas stream swirls downwardly through the chamber. The apparatus provides a bypass means for withdrawing a minor portion (about 5 to 25 vol. %) of the hot gas stream from the conduit and a duct for introducing the withdrawn minor portion of hot gas into the chamber at a tangent to a radius extending from the vertical axis and in a substantially horizontal plane.

US Patent:

52094286, May 11, 1993

Filed:

May 7, 1990

Appl. No.:

7/521211

Inventors:

Paul M. Bevilaqua - Santa Clarita CA
Paul K. Shumpert - Valencia CA

Assignee:

Lockheed Corporation - Calabasas CA

International Classification:

B64C 2900

US Classification:

244 123

Abstract:

The invention is a propulsion system for a V/STOL type aircraft. In detail, the invention comprises a turbofan engine including a fan section, compressor section, combustion section, turbine section and nozzle section. The turbine section comprises a low-pressure turbine portion coupled to and driving the fan section and a high-pressure turbine portion coupled to and driving the compressor section. A lift fan is coupled to the fan section by means of a drive shaft. A clutch is incorporated for decoupling the lift fan from the fan section. A mechanism is incorporated for extracting additional power from the low-pressure turbine portion of the turbine section to drive the lift fan that augments the basic engine thrust for V/STOL operation.