Anthony J Occhipinti, Age 46173 Grande Maison Blvd, Mandeville, LA 70471

2009016, Jul 2, 2009

Dec 26, 2007

12/005200

Anthony C. Occhipinti - Kenner LA, US

F02C 5/00
F23C 15/00

60247, 60 3976, 431 1

The invention provides a liquid fueled pulse detonation air breathing engine. The invention also provides an embodiment of an engine which has an axial flow compressor final stage configured for momentary closure of air flow at the final stage of the compressor followed by pulse detonation combustion that powers compressor, appliances, propeller, and produce thrust. Fuel enters the configured final stage of the axial flow air compressor to allow a mixture of air and fuel before entering the engine's pulse detonation combustion chamber, also referred to as detonation canister, having an inlet opening for receiving the fuel and air mixture charge and an open end down stream to discharge the resulting combustion products. Once the fuel and air mixture enters the detonation chamber there is closure for an instant of the compressor final stage's novel stators and blades before detonation of the fuel and air mixture. Detonation is initiated by a control system at the final compressor stage closure with ignition and impulse force is provided by a resultant shock wave. The front end of the engine allows control, and provides the use of appliances such as starter, alternator, fuel pumps, timing, and propellers if attached, as well as compressed air to the pulse detonation combustion chamber or canisters. Starting the engine is accomplished by an electrical starter motor as are conventional jet engines. Fuel is injected at the final stage of the compressor for good mixing with the compressed air before being pumped into the combustion chamber or canisters. Ignition and detonation occurs immediately downstream of the final compressor stage in the combustion chamber during the closure position of the compressor final stage. Ignition and detonation of the fuel many times a second generates shock waves that travels out of the open end of the combustion chamber or canisters at supersonic speed.

2011022, Sep 22, 2011

Mar 22, 2010

12/661648

Anthony C. Occhipinti - Kenner LA, US

B64C 27/46

416223 R

The invention relates a fluid or air propeller propulsion apparatus using the state of the art propeller that reduces the typical propeller slipstream disc contraction taking place very close to the propeller tips, containing an inlet slot on the leading edge of the propeller some distance measured from the propeller tips and connected internally to an exit tip slot at the propeller trailing edge. Fluid or air enters the leading edge slot during rotation of the propeller and is acted upon by centrifugal force varying directly with the propeller speed causing the fluid or air to be accelerated thru the internal passage and out the trailing edge exit slot parallel to the cambered face of the propeller at less than a right angle to the trailing edge, inducing flow at zero or low forward speed previously with little or no flow at the propeller tips and at greater speeds, increasing the propeller capacity, and adding an additional jetting action or bootstrapping which causes the propeller to turn more easily, all of which increases the propeller thrust and efficiency.

2012018, Jul 26, 2012

Jan 25, 2011

12/931113

Anthony C. Occhipinti - Kenner LA, US

F01D 5/14

416235

The invention relates a fluid or air propeller propulsion apparatus using modified state of the art propeller that reduces the typical propeller slipstream disc contraction at the propeller tips, by simply adding a novel channel or trough on the back surface spanwise midway between the leading edge and trailing edge. A portion of the air or fluid flowing over the back face of propeller blade is raked off and collected in the channel during rotation of the propeller, wherein the fluid or air is acted upon by centrifugal force varying directly with the propeller speed causing the fluid or air to be accelerated thru the channel or trough to the trailing edge of the propeller. This additional flow increases the propeller capacity additional jetting action bootstrapping causing the propeller to turn more easily, all of which increases the propeller thrust and efficiency as much as 10 percent.

5540406, Jul 30, 1996

Jul 26, 1995

8/507811

Anthony C. Occhipinti - Metairie LA

B64C 2110

244200

A low turbulence cambered surface foil, hydrofoil or airfoil, which contains indentations located on maximum camber across which a fluid can be flowed. The indentations create turbulence in the boundary layer downstream of the indentations, changing the characteristics of the flowing fluid to a turbulent boundary layer ahead of the normal point of separation of the fluid from the foil, this causing the fluid to cling close to the surface of the foil and postpone or delay trailing edge separation of the fluid stream from the foil. The noise level is reduced, the performance and efficiency of the foil is improved, or both the noise level is reduced and the performance and efficiency of the foil is improved.