Energy recovery-recycling turbine integrated with a capillary tube gas compressor
A centrifugal gas compressor with rotating hollow housing and an independently rotating, turbine compresses gas bubbles in capillary tubes and recovers energy from the liquid drain (sometimes a liquid recycler). The housing rotatably retains an internal spool having the turbine. Gas-liquid emulsion fed to the capillaries generates compressed gas-liquid emulsion at a radially distal annular region in an annular lake within the spool. Compressed gas leaves the lake and is ported away. A turbine blade edge in spilt over liquid drives the turbine, converting angular velocity/momentum into shaft torque as recovered energy. Blade captured liquid is recycled to capillary inputs.
1. An energy recovery system for a gas compressor having an input axle rotated by a prime mover, comprising:
the gas compressor including a substantially hollow cylindrical housing rotatably driven by the prime mover, the rotating hollow cylindrical housing having an inboard surface distal to an axis of rotation and proximate to an annular chamber formed within the hollow cylindrical housing;
a turbine rotatably positioned inside the annular chamber and rotating independent of the rotating hollow cylindrical housing, the turbine having an output axle;
the annular chamber defining an annular compressed gas chamber and containing an annular lake of liquid and compressed gas formed by the gas compressor;
the turbine being configured to capture the liquid from the annular lake to return the liquid to an inlet of the gas compressor and to convert one or both of an angular velocity and an angular momentum of the liquid in the annular lake into turbine shaft torque applied to the output axle.
2. An energy recovery system for a gas compressor as claimed in claim 1 , wherein:
the turbine having one or more turbine blades, the turbine including a pressure plate at one axial end and the one or more turbine blades at another axial end, the pressure plate and the one or more turbine blades having substantially the same radial extent and forming the annular compressed gas chamber therebetween;
the annular lake forming a liquid seal between the pressure plate and the one or more turbine blades, the annular lake having an axial length between the pressure plate and the one or more turbine blades and a radial lake depth therebetween which depth is greater than a radial space between the one or more turbine blades and the inboard wall of the hollow cylindrical housing;
a dam beneath the annular lake protruding radially inboard from the inboard surface of the hollow cylindrical housing, the radial height of the dam being less than the radial depth of the annular lake;
a portion of the liquid in the annular lake spilling over the dam as spilt over liquid; and
the spilt over liquid driving the one or more turbine blades.
3. An energy recovery system for a gas compressor as claimed in claim 2 , wherein:
the turbine including a plurality of fluid capture vanes radially, distally extending into the spilt over liquid, the fluid capture vanes including a plurality of continuously curved arc passageways between the spilt over liquid and a radially inboard location.
4. An energy recovery system for a gas compressor as claimed in claim 3 , wherein:
the turbine includes a hollow coaxial frustoconical base between the one or more turbine blades and the pressure plate;
each the continuously curved arc passageways fluidly coupled to a central conical liquid collection chamber defined inside the hollow coaxial frustoconical base;
a radially inboard liquid annular space axially located near the pressure plate and at one axial end of the central conical liquid collection chamber opposite the axial location of the one or more turbine blades; and
the inlet of the gas compressor supplied with liquid from the radially inboard liquid annular space.
5. An energy recovery system for a gas compressor as claimed in claim 4 , including
a weir in the radially inboard liquid annular space to control the radial depth of the liquid therein, the weir forming an annular pool of liquid to be fed to the inlet of the gas compressor.
6. An energy recovery system for a gas compressor as claimed in claim 5 , wherein:
the gas compressor includes a plurality of compression tubes, each of the plurality of compression tubes having a siphon passageway extending between the annular pool to a corresponding compression tube output and a respective input port for each corresponding compression tube and a gas inlet supplying gas to each respective siphon passageway;
whereby the gas is mixed with the liquid fed into the inlet of the gas compressor emulsion is generated by the siphon passageway, the gas inlet and the annular pool.
7. An energy recovery system for a gas compressor as claimed in claim 6 , wherein each of the plurality of compressor tubes includes one or more castellated tube ends formed at a radially proximally terminal end.
8. An energy recovery system for a gas compressor as claimed in claim 1 , including a heat transfer subsystem including one or more of internally extending heat transfer fins and one or more externally extending heat transfer fins, the internal heat transfer fins extending into the annular lake, the external heat transfer fins extending outboard of the hollow cylindrical housing.
9. An energy recovery system for a gas compressor as claimed in claim 1 , wherein the output axle extends coaxially outboard from the hollow cylindrical housing; and wherein the gas compressor provides energy recovery by utilization of torque applied to the output axle.
10. A gas compressor as claimed in claim 1 , including a brake operatively coupled to either the turbine or to the output axle.