A pulsejet is provided that includes an inlet, an exhaust nozzle, and a combustion chamber between the inlet and the exhaust nozzle. The pulsejet additionally includes a flow-turning device positioned over an end of the inlet. The flow turning device forms an air flow pathway (AFP) having a substan
A pulsejet is provided that includes an inlet, an exhaust nozzle, and a combustion chamber between the inlet and the exhaust nozzle. The pulsejet additionally includes a flow-turning device positioned over an end of the inlet. The flow turning device forms an air flow pathway (AFP) having a substantially 180° turn. The 180° turn aligns a direction of exhaust exiting the combustion chamber through the inlet along a positive axial thrust line and substantially parallel with exhaust exiting the combustion chamber through the nozzle.
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What is claimed is: 1. A pulsejet comprising: an inlet; an exhaust nozzle; a combustion chamber between the inlet and the exhaust nozzle; and a flow-turning device positioned over an end of the pulsejet to form an air flow pathway (AFP) having a substantially 180° turn for aligning a direction of
What is claimed is: 1. A pulsejet comprising: an inlet; an exhaust nozzle; a combustion chamber between the inlet and the exhaust nozzle; and a flow-turning device positioned over an end of the pulsejet to form an air flow pathway (AFP) having a substantially 180° turn for aligning a direction of exhaust exiting the combustion chamber through the inlet to be substantially parallel with exhaust exiting the combustion chamber through the nozzle along a positive axial thrust line. 2. The pulsejet of claim 1, wherein the AFP ensures returning inlet reflection waves meet returning nozzle reflective waves within the combustor chamber. 3. The pulsejet of claim 1, wherein an outside diameter of a side wall of the flow-turning device is approximately 100% to 125% as long as an outside diameter of the combustion chamber. 4. The pulsejet of claim 1, wherein the pulsejet further includes a straight inlet section extending from an end of the combustion chamber opposite the exhaust nozzle, the straight inlet providing an AFP area ratio that expands as a side wall of the flow-turning device extends toward the combustion chamber and nozzle. 5. The pulsejet of claim 4, wherein the straight inlet section comprises a length to diameter ratio that acoustically tunes the straight inlet section. 6. The pulsejet of claim 1, wherein the flow-turning device is formed so that as a side wall of the flow-turning device extends toward the exhaust-nozzle, the air gap area between the flow-turning device side wall and the inlet nozzle increases to allow more air flow into the inlet during the compression phase and diffuse the exhaust exiting the combustion chamber through the inlet during the combustion phase. 7. The pulsejet of claim 1, wherein the combustion chamber has an elongated cruciform shape including a plurality of linear apexes and linear valleys that create a plurality of AFPs between a side wall of the flow-turning device and the valleys that provide effectively unimpeded air intake flow and exhaust flow into and out of the inlet. 8. A method for providing vertical take off and landing propulsion for an aircraft, said method comprising: providing at least one valve-less pulsejet integrated within a fuselage of the aircraft, the pulsejet including a body having an inlet, an exhaust nozzle, a combustion chamber between the inlet and the exhaust nozzle; and positioning a flow-turning device over an end of the pulsejet to form an air flow pathway (AFP) having a substantially 180° turn for aligning a direction of exhaust exiting the combustion chamber through the inlet to be substantially parallel with exhaust exiting the combustion chamber through the nozzle along a positive axial thrust line. 9. The method of claim 8, wherein positioning a flow-turning device over the end of the pulsejet comprises forming the flow-turning device to have an outside diameter that is approximately 100% to 125% of an outside diameter of the combustion chamber. 10. The method of claim 8, wherein providing the valve-less pulsejet comprises providing an AFP area ratio that expands as a side wall of the flow-turning device extends toward the combustion chamber and nozzle by providing a straight inlet section extending from an end of the combustion chamber opposite the exhaust nozzle. 11. The method of claim 10, wherein the straight inlet section comprises a length to diameter ratio that acoustically tunes the straight inlet section. 12. The method of claim 8, wherein positioning a flow-turning device over an end of the pulsejet comprises increasing air flow into the inlet during a compression phase and diffusing the exhaust exiting the combustion chamber through the inlet by forming the flow turning device such that an area of the AFP increases as a side wall of the flow-turning device extends toward the exhaust nozzle. 13. The method of claim 8, wherein providing at least one valve-less pulsejet comprises forming the combustion chamber to have an elongated cruciform shape including a plurality of linear apexes and linear valleys that create a plurality of AFPs between a side wall of the flow-turning device and the valleys that provide effectively unimpeded air intake flow and exhaust flow into and out of the inlet. 14. A vertical take off and landing (VTOL) aircraft, said aircraft comprising: a fuselage having integrated therein at least one valve-less pulsejet, the pulsejet comprising: a body having an inlet, an exhaust nozzle, a combustion chamber between the inlet and the exhaust nozzle; a flow-turning device positioned over an end of the pulsejet to form an air flow pathway (AFP), the flow-turning device adapted to direct intake air flow into the inlet and exhaust flow exiting the combustion chamber through the inlet; and an augmentor cell connected to the body, the augmentor cell including a pair of opposing entraining walls adapted to entrain ambient air with exhaust flows of the pulsejet to maximize a propulsion thrust from the pulsejet. 15. The aircraft of claim 14, wherein the flow-turning device forms the AFP to have a substantially 180° turn for aligning a direction of the exhaust exiting the combustion chamber through the inlet to be substantially parallel with exhaust flow exiting the combustion chamber through the nozzle along a positive axial thrust line. 16. The aircraft of claim 14, wherein the AFP ensures returning inlet reflection waves meet returning nozzle reflective waves within the combustor chamber. 17. The aircraft of claim 14, wherein an outside diameter of a side wall of the flow-turning device is approximately 100% to 125% as long as an outside diameter of the combustion chamber. 18. The aircraft of claim 14, wherein the pulsejet further includes a straight inlet section extending from an end of the combustion chamber opposite the exhaust nozzle, the straight inlet providing an AFP area ratio that expands as a side wall of the flow-turning device extends toward the combustion chamber and nozzle. 19. The aircraft of claim 18, wherein the straight inlet section comprises a length to diameter ratio that acoustically tunes the straight inlet section. 20. The aircraft of claim 14, wherein the flow-turning device is formed so that as a side wall of the flow-turning device extends toward the exhaust-nozzle, the air gap area between the flow-turning device side wall and the inlet nozzle increases to allow more air flow into the inlet during the compression phase and diffuse the secondary exhaust during the combustion phase. 21. The aircraft of claim 14, wherein the combustion chamber has an elongated cruciform shape including a plurality of linear apexes and linear valleys that create a plurality of AFPs between a side wall of the flow-turning device and the valleys that provide effectively unimpeded air intake flow and exhaust flow into and out of the inlet.
Genz Matthew L. R. (4445 Delbrook Rd. North Vancouver ; British Columbia CAX V7N 4A6) Villman Bruce (2990 Sunnyside Rd. Port Moody ; British Columbia CAX V3H 3C8), Pulse-sonic jet nozzle.
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