Rotor and bearing system for a turbomachine
View Patent ↗A rotor and bearing system for a turbomachine. The turbomachine includes a drive shaft, an impeller positioned on the drive shaft, and a turbine positioned on the drive shaft proximate to the impeller. The bearing system comprises one gas journal bearing supporting the drive shaft between the impeller and the turbine. The area between the impeller and the turbine is an area of increased heat along the drive shaft in comparison to other locations along the drive shaft. The section of the drive shaft positioned between impeller and the turbine is also a section of the drive shaft that experiences increased stressed and load in the turbomachine. The inventive bearing machine system positions only one radial bearing in this area of increased stress and load.
1. A bearing system for a turbomachine, the turbomachine including a powerhead assembly having a shaft and a location of increased heat, the bearing system comprising only one gas bearing positioned in the location of increased heat, the only one gas bearing positioned to support the shaft and further including a gas thrust bearing positioned remote from the location of increased heat.
2. The bearing system of claim 1 , wherein the only one gas bearing is a radial bearing.
3. The bearing system of claim 2 , wherein the turbomachine further includes a compressor and a turbine and the location of increased heat is located between the compressor and the turbine.
4. The bearing system of claim 1 , wherein the location of increased heat is also a location of increased load.
5. The bearing system of claim 1 , further including a second gas bearing positioned remote from the location of increased heat.
6. The bearing system of claim 1 , wherein the turbomachine further includes an impeller and a turbine and the location of increased heat is located between the impeller and the turbine.
7. The bearing system of claim 6 , wherein the position of the only one gas bearing increases gas flow from the impeller to the turbine.
8. The bearing system of claim 7 , wherein the increased gas flow from the impeller to the turbine decreases the temperature of the only one gas bearing.
9. A bearing system for a turbomachine, the turbomachine including a powerhead assembly having a shaft and a location of increased heat, the bearing system comprising only one gas bearing positioned in the location of increased heat, the only one gas bearing positioned to support the shaft, wherein the turbomachine further includes an impeller and a turbine and the location of increased heat is located between the impeller and the turbine, and further including a thrust bearing positioned near the impeller and opposite the location of increased heat.
10. A bearing system for a turbomachine, the turbomachine including a drive shaft, an impeller positioned on the drive shaft, and a turbine positioned on the drive shaft proximate to the impeller, the bearing system comprising only one gas bearing supporting the drive shaft between the impeller and the turbine, and further including at least one gas axial bearing supporting the drive shaft wherein the impeller is positioned between the turbine and the at least one gas axial bearing.
11. The bearing system of claim 10 , further including an axial rotor attached to the drive shaft and fluidly engaging the at least one gas axial bearing, wherein the at least one gas axial bearing and the axial rotor axially position the drive shaft, the impeller, and the turbine.
12. The bearing system of claim 10 , further including a second gas journal bearing supporting the drive shaft wherein the impeller is positioned between the turbine and the second gas journal bearing.
13. The bearing system of claim 10 , wherein the impeller has a first gas pressure and the turbine has a second gas pressure; and
the one gas journal bearing is positioned to allow increased gas flow from the first gas pressure to the second gas pressure.
14. The bearing system of claim 13 , wherein the increased gas flow from the first gas pressure to the second gas pressure decreases the temperature of the one gas journal bearing.
15. A bearing system for a turbomachine, the turbomachine including a drive shaft, an impeller positioned on the drive shaft, and a turbine positioned on the drive shaft proximate to the impeller, the bearing system comprising only one gas bearing supporting the drive shaft between the impeller and the turbine, wherein the turbomachine further includes a magnetic assembly positioned distal to the turbine and having a magnetic shaft and a first fore end gas journal bearing supporting the magnetic shaft.
16. The bearing system of claim 15 , further including a second fore end gas journal bearing supporting the magnetic shaft.
17. A bearing system for an energy conversion machine, the energy conversion machine including a magnetic assembly and a powerhead assembly operatively attached to the magnetic assembly, the magnetic assembly including a magnetic shaft, the powerhead assembly including a drive shaft, a compressor positioned on the drive shaft and having fore and aft ends, and a turbine positioned on the drive shaft near the aft end of the compressor, the bearing system comprising:
a single gas journal bearing positioned between the compressor and the turbine to radially support the drive shaft; and
a thrust bearing positioned near the fore end of the compressor to axially support the drive shaft.
18. The bearing system of claim 17 , further including a second gas journal bearing positioned near the fore end of the compressor to radially support the drive shaft.
19. The bearing system of claim 17 , further including third and fourth gas journal bearings positioned in the magnetic assembly to radially support the magnetic shaft.
20. A rotor and bearing system for an energy conversion machine, the energy conversion machine including a magnetic assembly and a powerhead assembly operatively attached to the magnetic assembly, the magnetic assembly including a magnetic shaft, the powerhead assembly including a drive shaft, a compressor positioned on the drive shaft and having fore and aft ends, and a turbine positioned on the drive shaft near the aft end of the compressor, the rotor and bearing system comprising:
a single gas journal bearing positioned between the compressor and the turbine to radially support the drive shaft;
a thrust bearing positioned near the fore end of the compressor; and
a thrust rotor attached to the drive shaft and fluidly engaging the thrust bearing, wherein the thrust bearing and the thrust rotor axially position the drive shaft, the compressor, and the turbine.