Ultra high pressure turbomachine for waste heat recovery

• US 9,476,428 B2
• Filed: 05/31/2012
• Issued: 10/25/2016
• Est. Priority Date: 06/01/2011
• Status: Active Grant

• Current Assignee: R&D Dynamics Corporation
• Original Assignee: R&D Dynamics Corporation
• Inventors: Agrawal, Giridhari L., Buckley, Charles W., Shakil, Ali, Coward, Andrew Hamilton
• Primary Examiner(s): LETTMAN, BRYAN MATTHEW
• Application Number:
  US13/484,751
• Publication Number:
  US 20120306206A1
• Time in Patent Office: 1,608 Days
• US Class Current: 1/1
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F01D 25/125 of bearings
• CPC Class Codes: F01D 25/168 for axial load mainly
• CPC Class Codes: F04D 25/024 the driving means being assisted by a power recovery turbine
• CPC Class Codes: F04D 25/0606 the electric motor being specially adapted for integration in the pump
• CPC Class Codes: F04D 29/0513 hydrostatic; hydrodynamic thrust bearings
• CPC Class Codes: H02K 1/32 with channels or ducts for flow of cooling medium

Abstract

A turbine-driven alternator (i.e., a turbomachine) suitable for generating electrical power from process gas waste energy. In particular suitable for very high density process gases such as super critical CO2, R134a, R245fa, etc. The turboalternator comprises two separate machines, specifically, a turbine device and an alternator device operatively connected together by a coupling shaft. The rotating shaft assemblies for each machines on the turbine side and the alternator side are supported by hydrodynamic foil gas bearings. The foil gas bearings use process gas at the turbine side, enabling high-pressure operation (˜3000 psia) and thrust load balancing. At the alternator side, cooling fluid is used in the foil gas bearings, enabling high-speed (˜40,000 rpm), low-windage, oil-free operation with closed-loop shaft cooling.

Claims

1. A turbomachine comprising:

a turbine including;

a turbine housing having an inlet for receiving a process gas at a first pressure and having an outlet for discharging the process gas at a second pressure, wherein said second pressure is lower than said first pressure;

a rotating shaft mounted within the turbine housing for rotation about a central longitudinal axis, said rotating shaft being radially supported by at least one journal bearing assembly and axially supported by a thrust bearing assembly mounted within the turbine housing; and

an impeller rigidly attached to the rotating shaft for rotation therewith for processing the process gas from the first pressure to the second pressure, said impeller being housed in a collector portion of the turbine housing and discharging the process gas to the outlet of the turbine housing; and

a cooling and thrust balancing system including;

a gas injection port through the turbine housing into a thrust bearing chamber housing the thrust bearing assembly;

a supply manifold connected from the inlet of the turbine housing to the gas injection port;

a pressure relief vent port through the turbine housing at a location rearward, in a direction away from the impeller, from the thrust bearing chamber;

an exhaust manifold connected to the outlet of the turbine housing via at least the pressure relief vent port;

first and second axial seals on the rotating shaft respectively forward and rearward of the impeller;

third and fourth axial seals on the rotating shaft rearward of the thrust bearing chamber, said third and fourth axial seals being configured to supply a controlled amount of leakage from the turbine housing;

a flow vent port through the turbine housing between the third and fourth axial seals;

a plurality of pressure equalizing holes axially extending through a thrust runner of the thrust bearing assembly operatively connected to the rotating shaft for rotation therewith; and

a bleed hole vent port formed in the turbine housing to collect flow from the at least one journal bearing assembly and from the second axial seal.

2. The turbomachine as claimed in claim 1, said gas injection port being oriented to inject the process gas tangentially to the thrust runner.

3. The turbomachine as claimed in claim 1, further comprising:

an alternator having a rotating alternator shaft;

an adapter housing connected between static portions of the turbine and the alternator;

a coupling connecting a rotating turbine shaft of the turbine and the rotating alternator shaft of the alternator through the adapter housing;

said alternator comprising;

an alternator housing;

a stator assembly mounted in said alternator housing;

a rotor assembly rotatably housed in said alternator housing and including;

a hub having axial grooves along its outer surface;

a conductive sleeve covering the axial grooves;

at least one permanent magnet mounted over the conductive sleeve; and

an outer sleeve mounting the at least one permanent magnet to the conductive sleeve; and

a cooling fan rotatably housed in said alternator housing and rigidly connected with the rotor assembly for coaxial rotation, said cooling fan configured to drive a gas flow through the axial grooves of the hub for cooling said rotor assembly and for maintaining a pressure level within the alternator housing.

4. The turbomachine as claimed in claim 3, wherein the rotor assembly includes first and second journal bearing assemblies disposed at opposing ends of the rotor assembly for radially supporting said rotor assembly within the alternator housing, and

wherein the cooling fan is configured to drive a gas flow through radial clearances through said journal bearing assemblies.

5. The turbomachine as claimed in claim 3, said thrust runner being associated with thrust bearings for axially supporting the rotor assembly in the alternator housing, and

wherein the cooling fan is configured to drive a gas flow through axial clearances around said thrust runner.

6. The turbomachine as claimed in claim 3, wherein the hub of the rotor assembly is made from a non-conductive material.

7. The turbomachine as claimed in claim 3, wherein the rotor assembly includes forward and rearward rings configured to axially retain the at least one permanent magnet on the conductive sleeve.

8. The turbomachine as claimed in claim 7, wherein the forward ring supports teeth of a labyrinth seal.

9. The turbomachine as claimed in claim 7, wherein the forward and rearward rings include through holes aligned with the axial grooves of the hub.

10. The turbomachine as claimed in claim 3, wherein the cooling fan has an inlet operatively connected to the adapter housing so as to draw the process gas from the adapter housing for maintaining a pressure difference between the alternator housing and the adapter housing, said pressure level in the alternator housing being higher than a pressure level in the adapter housing.

11. The turbomachine as claimed in claim 10, wherein the cooling fan draws the process gas from the adapter housing via a sealed heat exchanger.

12. The turbomachine as claimed in claim 10, wherein the turbine includes a turbine housing and an operating pressure in said turbine housing is higher than the pressure level in the alternator housing.

13. The turbomachine as claimed in claim 3, wherein the cooling and thrust balancing system of the turbine is configured to supply the process gas to the adapter housing via a controlled shaft seal leakage from the turbine housing.