Engine brake for part load CO reduction
View Patent ↗Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the T_PZ above a lower T_PZ limit. A method for operating a turbine engine assembly is also disclosed.
1. A turbine engine assembly for a generator, the assembly comprising:
a turbine engine having a compressor section, a combustor section and a turbine section, the combustor section having a primary zone temperature and the turbine engine having a design load;
at least one air bleed line in communication with the compressor section;
at least one valve for controlling air flow through the at least one air bleed line;
a plurality of inlet guide vanes in the compressor section;
a controller that upon sensing a decreased operating load first closes the inlet guide vanes and then, in parallel, opens the at least one valve to allow bleed air to flow through the at least one air bleed line and opens the inlet guide vanes to increase compressor inlet flow when an operating load is less than the design load, wherein a flow rate through the at least one air bleed line is increased and compressor inlet flow is increased as the operating load is decreased thereby reducing power delivered to the generator while maintaining the primary zone temperature above a primary zone temperature lower limit, whereby additional inlet flow drawn into the compressor section is dumped out through the bleed line.
2. The turbine engine assembly of claim 1 , wherein the at least one air bleed line is a high pressure bleed line.
3. The turbine engine assembly of claim 1 , wherein the primary zone temperature lower limit is selected so as to maintain CO production at less than about 10 ppmvd at 15% O 2 .
4. The turbine engine assembly of claim 1 , wherein flow through the at least one air bleed line is supplied to at least one of exhaust flow from the turbine engine, an inlet of the turbine engine and atmosphere.
5. A CO reduction system for a turbine engine operably coupled to a generator, the system comprising:
a bleed line in communication with a compressor section of the turbine engine;
a flow control device for controlling flow through the bleed line;
a plurality of inlet guide vanes in the compressor section;
a controller that upon sensing a decreased operating load first closes the inlet guide vanes and then, in parallel, actuates the flow control device to allow bleed air to flow through the bleed line and opens the inlet guide vanes to increase compressor inlet flow when an operating load is less than a design load of the turbine engine, wherein a flow rate through the bleed line is increased and compressor inlet flow is increased as the operating load is decreased thereby reducing power delivered to the generator while maintaining the primary zone temperature above a primary zone temperature lower limit, whereby additional inlet flow drawn into the compressor section is dumped out through the bleed line.
6. The system of claim 5 , wherein the bleed line is a high pressure bleed line.
7. The system of claim 5 , wherein the primary zone temperature lower limit is selected so as to maintain CO production at less than about 10 ppmvd at 15% O 2 .
8. The system of claim 5 , wherein flow through the bleed line is supplied to atmosphere.
9. The system of claim 5 , wherein flow through the bleed line is supplied to exhaust flow from the turbine engine.
10. The system of claim 5 , wherein flow through the bleed line is supplied to an inlet of the turbine engine.
11. A method of operating a turbine engine assembly comprising:
sensing a load on a turbine engine for a reduced operating load;
closing inlet guide vanes responsive to the reduced operating load;
after inlet guide vanes have been closed, bleeding air from a compressor section of the turbine engine and in parallel opening the inlet guide vanes responsive to the reduced operating load, wherein a flow rate of bleed air is increased as the operating load is decreased and, in parallel, compressor inlet flow is increased thereby reducing power delivered to a generator and maintaining a primary zone temperature of a combustor section above a primary zone temperature lower limit.
12. The method of claim 11 , further comprising bleeding the air from a high pressure region of the compressor.
13. The method of claim 11 , further comprising selecting the primary zone temperature lower limit so as to maintain CO production at less than a desired limit.
14. The method of claim 11 , further comprising directing the bleed air to exhaust flow of the turbine engine.
15. The method of claim 11 , further comprising directing the bleed air to an inlet of the turbine engine.
16. The method of claim 11 , further comprising directing the bleed air to atmosphere.