Cooling device for a gun barrel
A cooling device for a gun barrel has a muzzle assembly. The muzzle assembly has a shaft, a baffle, a turbine assembly, a compressor assembly, and a rotary drive tube. The rotary drive tube connects the turbine assembly to the compressor assembly. A heat exchanger may be releasably connected to the cooling device. A diffuser or muzzle device may be arranged downstream of the turbine assembly.
1. A device for cooling a gun barrel with a cooling media, the device comprising:
a muzzle assembly having:
a shaft, the shaft having a first end and an axial opposite second end with a length between the first and second ends, the second end of the shaft being adapted and configured to releasably connect to an end of a gun barrel, the shaft having a bore, the bore of the shaft being adapted and configured to allow a round discharged from the gun to pass through the shaft from the second end of the shaft to the first end of the shaft;
a baffle operatively connected at the first end of the shaft;
a turbine assembly operatively connected to the shaft adjacent the first end of the shaft, the turbine assembly have a plurality of turbine blades downstream of the baffle and the first end of the shaft, the plurality of turbine blades being adapted and configured to rotate relative to the shaft;
a compressor assembly operatively connected to the shaft and disposed between the first end of the shaft and the second end of the shaft, the compressor assembly having a plurality of compressor blades, the compressor blades being adapted and configured to rotate relative to the shaft; and
a rotary drive tube operatively connected to a radially outward region of at least one turbine blade and a radially outward region of at least one compressor blade, the rotary drive tube being adapted and configured to rotate relative to the shaft and rotate with the plurality of a turbine blades and the plurality of compressor blades, the rotary drive tube having a plurality of outlet vents downstream of the plurality of compressor blades.
2. The device of claim 1 , further comprising:
a heat exchanger upstream of the muzzle assembly, the heat exchanger being adapted and configured to be removably connected with the muzzle assembly adjacent the second end of the shaft, the heat exchanger comprising an intake and a discharge, and at least one cooling fin, the intake being adapted and configured to direct the cooling media onto the at least cooling fin, the discharge being aligned with and adapted and configured to direct the cooling media from the at least one cooling fin to the plurality of compressor blades.
3. The device of claim 2 , wherein the heat exchanger further comprises:
an outer shell;
a plurality of segments contained within the outer shell, the plurality of segments being radially movable within the outer shell;
a locking nut removably connectable with the outer shell;
wherein the outer shell and at least one of the segments has cooperating tapered surfaces such that removably connecting the locking nut with the outer shell moves the at least one segment radially inward in the outer shell.
4. The device of claim 2 wherein the heat exchanger comprises a chamber defined by an outer shell with a plurality of fins projecting radially inward from the outer shell.
5. The device of claim 2 wherein the heat exchanger comprises a center tube with a plurality of fins projecting radially outward from the center tube.
6. The device of claim 5 wherein the center tube is adapted and configured to supercircumjacently receive the barrel of the gun.
7. The device of claim 1 further comprising:
a tube operatively and removably connectable to the muzzle assembly, the tube being radially outward of the rotary drive tube, the tube having vents that direct effluent from the outlet vents of the rotary drive tube away from the muzzle assembly.
8. The device of claim 1 further comprising:
a shield operatively and repositionally connected to the muzzle assembly, the shield being radially outward of the rotary drive tube, the shield being adapted and configured to selectively directionally deflect effluent from the outlet vents of the rotary drive tube away from the muzzle assembly.
9. The device of claim 1 , wherein the baffle is conically shaped and arranged to expand outward to the turbine blades.
10. The device of claim 1 wherein a majority of the turbine blades are connected to the rotary drive tube.
11. The device of claim 1 wherein a majority of the compressor blades are connected to the rotary drive tube.
12. The device of claim 1 wherein the plurality of compressor blades comprises a first set of blades with a first pitch and a second set of blades having a second pitch, the first pitch being different than the second pitch.
13. The device of claim 1 wherein the plurality of compressor blades comprises a first set having a first number of blades in the first set and a second set having a second number of blades in the second set, the first number of blades being different than the second number of blades.
14. The device of claim 1 wherein the turbine assembly further comprises a turbine bearing, and wherein the turbine assembly is adapted and configured to allow the cooling media to cool the turbine bearing.
15. The device of claim 1 , wherein the compressor assembly comprises a compressor bearing, and wherein the compressor assembly is adapted and configured to allow the cooling media to cool the compressor bearing.
16. The device of claim 1 , further comprising a diffuser plate downstream of the turbine assembly, the diffuser plate having outlet openings, the outlet openings being adapted and configured to direct a flow of propellant gases from the baffle and turbine away from the muzzle assembly, the diffuser plate having a muzzle opening coaxially aligned with and spaced from the first end of the shaft and adapted to allow passage of the round therethrough.
17. The device of claim 16 wherein the openings of the diffuser plate are adapted and configured to straighten a flow of the propellant gases flowing though the diffuser plate.
18. The device of claim 16 wherein the openings of the diffuser plate are adapted and configured to direct a flow of the propellant gases flowing though the diffuser plate in a direction of at least one of radially away from the diffuser plate and upstream of the diffuser plate.
19. The device of claim 1 wherein the cooling media is ambient air.
20. The device of claim 1 further comprising a suppressor removably connectable to the muzzle assembly downstream of the turbine assembly.