Supersonic compressor comprising radial flow path
The present invention provides novel supersonic compressors comprising novel supersonic compressor rotors. The supersonic compressor rotors are designed to operate at very high rotational speed wherein the velocity of the gas entering the supersonic compressor rotor is greater than the local speed of sound in the gas, hence the descriptor “supersonic”. The new supersonic compressors comprise at least one supersonic compressor rotor defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp. The novel supersonic compressor rotors are expected to enhance the performance of supersonic compressors comprising them, and to provide for greater design versatility in systems comprising such novel supersonic compressors.
1. A supersonic compressor comprising:
(a) a fluid inlet;
(b) a fluid outlet; and
(c) a plurality of supersonic compressor rotors, said supersonic compressor rotors defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp,
wherein a first supersonic compressor rotor is disposed within an inner cylindrical cavity of a second supersonic compressor rotor.
2. The supersonic compressor according to claim 1 , wherein said supersonic compressor rotors comprise a plurality of vanes disposed between a pair of rotor support plates, at least one of said vanes comprising a supersonic compression ramp.
3. The supersonic compressor according to claim 1 further comprising a centrifugal compressor rotor.
4. The supersonic compressor according to claim 1 , wherein the supersonic compressor rotor is configured for inside-out compression.
5. The supersonic compressor according to claim 1 , wherein said supersonic compressor rotors comprise a plurality of radial flow channels.
6. The supersonic compressor according to claim 1 , further comprising a plurality of vanes defining a plurality of radial flow channels.
7. The supersonic compressor according to claim 1 , which is comprised within a gas turbine engine.
8. The supersonic compressor according to claim 1 , wherein the first and second supersonic compressor rotors are configured for counter rotary motion.
9. The supersonic compressor according to claim 1 , wherein said supersonic compression ramp is integral to a vane.
10. The supersonic compressor according to claim 1 , wherein said supersonic compression ramp is not integral to a vane.
11. The supersonic compressor according to claim 1 , wherein at least one of the supersonic compressor rotors defines a plurality of radial flow channels.
12. The supersonic compressor according to claim 1 , wherein the supersonic compressor rotors are configured for inside-out compression.
13. The supersonic compressor according to claim 12 , further comprising a centrifugal compressor disposed within an inner cylindrical cavity of the first supersonic compressor rotor.
14. The supersonic compressor rotor according to claim 1 , wherein the radial flow channel defines a subsonic diffusion zone.
15. The supersonic compressor rotor according to claim 1 , wherein a plurality of vanes disposed between a pair of rotor support plates define a plurality of radial flow channels, at least one of said vanes comprising said supersonic compression ramp.
16. A supersonic compressor comprising:
(a) a gas conduit comprising (i) a low pressure gas inlet, and (ii) a high pressure gas outlet;
(b) a first supersonic compressor rotor defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp;
(c) a second supersonic compressor rotor defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp; and
(d) a centrifugal compressor rotor;
said centrifugal compressor rotor being disposed within the inner cylindrical cavity of the first supersonic compressor rotor, said first supersonic compressor rotor being disposed within the inner cylindrical cavity of the second supersonic compressor rotor, said centrifugal compressor rotor being configured to counter-rotate with respect to said first supersonic compressor rotor, said first supersonic compressor rotor being configured to counter-rotate with respect to said second supersonic compressor rotor, said centrifugal compressor rotor and said first supersonic compressor rotor and said second supersonic compressor rotor being disposed within the gas conduit.
17. A method of compressing a fluid, said method comprising:
(a) introducing a fluid through a low pressure gas inlet into a gas conduit comprised within a supersonic compressor; and
(b) removing a gas through a high pressure gas outlet of said supersonic compressor;
said supersonic compressor comprising a plurality of supersonic compressor rotors, said supersonic compressor rotors defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp,
wherein a first supersonic compressor rotor is disposed within an inner cylindrical cavity of a second supersonic compressor rotor.
18. The method according to claim 17 , wherein said fluid comprises carbon dioxide.