Self compressing supersonic flow device

Claim 2

A self-compressing supersonic flow device where self-compression is due to convergence and divergence of flow without the need for external walls to constrain a flow pattern comprising: a working fluid; a means for driving said fluid at a predetermined rate; and a plurality of supersonic nozzles placed in a path of said driven fluid for converging said driven fluid, where said convergence arises due to the nozzles which consist of a plurality of curved blades having a subsonic entrance section and a supersonic exit section placed in said driver fluid thereby altering fluid flow such that no external walls are needed to have a convergent-divergent flow pattern downstream from said plurality of nozzles.

Claim 3

A self-compressing supersonic flow device as described in claim 1 further comprising a high pressure chamber in said fluid path and behind said supersonic nozzles for maintaining a uniform flow.

Claim 4

A self-compressing supersonic flow device as described in claim 1 wherein said curved nozzle blades comprise an arc of a circle of predetermined radius.

Claim 5

A self-compressing supersonic flow device as described in either claim 3 further comprising a high pressure chamber in said fluid path and behind said subsonic sections of said supersonic nozzles for maintaining a uniform flow.

Claim 6

A self-compressing supersonic flow device as described in claim 1 wherein said supersonic nozzles comprise a plurality of axi-symmetric supersonic nozzles, said plurality having a combined effect of one single self-compressing nozzle.

Claim 7

A self-compressing supersonic flow device as described in any of claims 1, 2, 3, or 5 further comprising Coanda effect means for creating a wall of turbulent subsonic flow surrounding said converging fluid upon said fluids emission from said supersonic nozzles.

Claim 8

A self-compressing supersonic flow device as described in any of claims 1, 2, 3, or 5 further comprising means for creating a high speed jet flow wall about said predetermined converging fluid upon said fluids emission from said supersonic nozzles.

Claim 9

A self-compressing supersonic gas flow laser where self-compression is due to convergence and divergence of flow without need for external walls to constrain a flow pattern comprising: an air compressor for inputting a specific volume of air into predetermined motion; a manifold connected to said air compressor for inputting said air into a combustion chamber; a fuel tank with combustible fuel connected to said manifold for burning with said compressed air when it is in said combustion chamber so as to form a gas capable of lasing; a high pressure chamber connected to said manifold for maintaining a uniform high pressure gas flow; a plurality of supersonic nozzles mounted to said high pressure chamber for focusing said gas from said high pressure chamber into a self-compressing supersonic flow such that said gas emits radiation in a predetermined portion of said supersonic flow, said self-compressing effect achieved by having said plurality of supersonic nozzles arranged to form a convergent-divergent flow without the need for walls surrounding said flow to force such a pattern; a mirror system placed across said predetermined radiation emitting portion of said supersonic flow for extracting said emitted radiation along a preset path; and a gas turbine placed in said supersonic flow after said predetermined emitting radiation portion and after said self-compressing flow starts to diverge for being driven by said supersonic flow, said turbine connected to said air compressor so as to drive said air compressor.

Claim 10

A self-compressing supersonic gas flow laser where self-compression is due to convergence and divergence of flow without need for external walls to constrain a flow pattern comprising: an air compressor for inputting a specific volume of air into predetermined motion; a manifold connected to said air compressor for inputting said air into a combustion chamber; a fuel tank with combustible fuel connected to said manifold for burning with said compressed air when it is in said combustion chamber so as to form a gas capable of lasing; a high pressure chamber connected to said manifold for maintaining a uniform high pressure gas flow; a plurality of supersonic nozzles mounted to said high pressure chamber for focusing said gas from said high pressure chamber into a self-compressing supersonic flow such that said gas emits radiation in a predetermined portion of said supersonic flow, said self-compressing effect achieved by having said plurality of supersonic nozzles arranged to form a convergent-divergent flow without the need for walls surrounding said flow to force such a pattern; a mirror system placed across said predetermined radiation emitting portion of said supersonic flow for extracting said emitted radiation along a preset path; and a gas turbine placed in said supersonic flow after said predetermined emitting radiation portion and after said self-compressing flow starts to diverge for being driven by said supersonic flow, said turbine connected to said air compressor so as to drive said air compressor.

Claim 11

A self-compressing supersonic flow gas laser as described in claim 8 wherein said supersonic nozzles comprise a plurality of curved blades each having a subsonic entrance section and a supersonic exit section.

Claim 12

A self-compressing supersonic flow gas laser as described in claim 8 wherein said supersonic nozzles comprise a plurality of axi-symmetric supersonic nozzles, said plurality having a combined effect of one single self-compressing nozzle.

Claim 13

A self-compressing supersonic flow gas laser as described in claim 8 wherein said supersonic nozzle comprises approximate cylindrical symmetry about an axis such that the supersonic self-compression pattern emitted from said supersonic nozzles has a cylindrical region of lasing.

Claim 14

A self-compressing supersonic flow gas laser as described in any of claims 8, 9, 10, or 11 further comprising Coanda effect means for creating a wall of turbulent subsonic flow surrounding said supersonic flow from said supersonic nozzles.

Claim 15

A self-compressing supersonic flow gas laser as described in any of claims 8, 9, 10, or 11 further comprising means for creating a high speed jet flow wall about said supersonic flow from said supersonic nozzles.

Claim 16

A self-compressing supersonic flow gas laser as described in any of claims 8, 9, 10, or 11 wherein said combustable fuel comprises benzene.

Claim 17

A self-compressing supersonic flow device where self-compression is due to convergence and divergence of the flow without the need for external walls to constrain flow pattern comprising: a working fluid; a means for driving said fluid at a predetermined flow rate; and a plurality of curved blades having a subsonic entrance section and a supersonic exit section placed in said driven fluid in a pattern which causes said driven fluid to follow a convergent-divergent path without the need for walls surrounding said flow to force such a convergent-divergent path, said plurality of curved blades pattern being a partial spherical array of supersonic nozzles.

Claim 18

A self-compressing supersonic flow device where self-compression is due to convergence and divergence of the flow without the need for external walls to constrain flow pattern comprising: a working fluid; a means for driving said fluid at a predetermined flow rate; and a plurality of curved blades having a subsonic entrance section and a supersonic exit section placed in said driven fluid in a pattern which causes said driven fluid to follow a convergent-divergent path without the need for walls surrounding said flow to force such a convergent-divergent path, said plurality of curved blades pattern being a partial spherical array of supersonic nozzles.

Claim 19

A self-compressing supersonic flow device as described in claim 15 further comprising means for creating a high speed jet flow wall about said predetermined focused fluid upon said fluids emission from said plurality of curved blades.

Claim 20

A self-compressing supersonic flow gas laser where self-compression is due to convergence and divergence of the flow without the need for external walls to constrain a flow pattern comprising: an air compressor for inputting a specific volume of air into predetermined motion; a manifold connected to said air compressor for inputting said air into a combustion chamber; a fuel tank with combustible fuel connected to said manifold for burning with said compressed air when it is in said combustion chamber so as to form a gas capable of lasing; a high pressure chamber connected to said manifold for maintaining a uniform high pressure gas flow; a plurality of curved blades having a subsonic entrance section and a supersonic exit section, said plurality configured to form a partial spherical array of supersonic nozzles, said partial spherical array mounted to said high pressure chamber for focusing said gas from said high pressure chamber into a self-compressing supersonic flow such that said gas emits radiation in a predetermined portion of said supersonic flow, said self-compressing effect achieved by having said plurality of curved blades arranged to form a converging flow of the gas without the need for surrounding walls to force the flow into a smaller cross-section area downstream in said flow; a mirror system placed across said predetermined radiation emitting portion for extracting said emitted radiation along a preset path; and a gas turbine placed in said supersonic flow after said predetermined emitting radiation portion and after said self-compressing flow starts to diverge for being driven by said supersonic flow, said turbine connected to said air compressor so as to drive said air compressor.

Claim 21

A self-compressing supersonic flow gas laser where self-compression is due to convergence and divergence of the flow without the need for external walls to constrain a flow pattern comprising: an air compressor for inputting a specific volume of air into predetermined motion; a manifold connected to said air compressor for inputting said air into a combustion chamber; a fuel tank with combustible fuel connected to said manifold for burning with said compressed air when it is in said combustion chamber so as to form a gas capable of lasing; a high pressure chamber connected to said manifold for maintaining a uniform high pressure gas flow; a plurality of curved blades having a subsonic entrance section and a supersonic exit section, said plurality configured to form a partial spherical array of supersonic nozzles, said partial spherical array mounted to said high pressure chamber for focusing said gas from said high pressure chamber into a self-compressing supersonic flow such that said gas emits radiation in a predetermined portion of said supersonic flow, said self-compressing effect achieved by having said plurality of curved blades arranged to form a converging flow of the gas without the need for surrounding walls to force the flow into a smaller cross-section area downstream in said flow; a mirror system placed across said predetermined radiation emitting portion for extracting said emitted radiation along a preset path; and a gas turbine placed in said supersonic flow after said predetermined emitting radiation portion and after said self-compressing flow starts to diverge for being driven by said supersonic flow, said turbine connected to said air compressor so as to drive said air compressor.

Claim 22

A self-compressing supersonic flow device as described in claim 17 further comprising Coanda effect means for creating a wall of turbulent subsonic flow surrounding said focused supersonic fluid upon said fluids emission from said plurality of curved blades.

Claim 23

A self-compressing supersonic flow gas laser as described in claim 17 further comprising Coanda effect means for creating a wall of turbulent subsonic flow surrounding said supersonic flow from said plurality of curved blades.

Claim 24

A self-compressing supersonic flow gas laser as described in claim 17 further comprising means for creating a high speed jet flow wall about said supersonic flow from said plurality of curved blades.

Claim 25

A self-compressing supersonic flow gas laser as described in claim 17 wherein said combustible fuel comprises benzene.