Tip clearance control
View Patent ↗Aspects of the invention relate to a system and method for actively managing blade tip clearances in a turbine engine, particularly under start up and steady state operating conditions. During start up, the rotor can be cooled while the blade ring can be heated. During steady state operation, the rotor may be heated while the blade ring may be cooled. The sources of the heating fluid and cooling fluid can be compressor delivery air, boiler steam and ambient air. The fluids can be compressed to maintain efficiency.
1. A blade clearance control system for a turbine engine having a compressor section, a rotor assembly with a rotor, and an exhaust duct, the system comprising:
a blade ring concentric with the rotor assembly and positioned radially outward from blade tips of the rotor assembly to define a gap therebetween;
a first cooling circuit in fluid communication with the compressor section and the rotor, the first cooling circuit being in thermal communication with a heat exchanger; and
a first heating circuit in fluid communication with the exhaust duct and the blade ring,
wherein during engine start up the first cooling circuit extracts compressor delivery air from the compressor section, cools the compressor delivery air via the heat exchanger and supplies the compressor delivery air to the rotor for cooling of the rotor, and
wherein during engine start up the first heating circuit extracts hot exhaust gases from the exhaust duct and supplies the hot exhaust gases to the blade ring for heating of the blade ring.
2. The system of claim 1 , further comprising:
a second cooling circuit in fluid communication with a boiler and the blade ring; and
a second heating circuit in fluid communication with the compressor section and the rotor, the second heating circuit being in thermal communication with a heating device,
wherein during steady state operation the second cooling circuit extracts steam from the boiler and supplies the steam to the blade ring for cooling of the blade ring, and
wherein during steady state operation the second heating circuit extracts compressor delivery air from the compressor section, heats the compressor delivery air via the heating device and supplies the compressor delivery air to the rotor for heating of the rotor.
3. The system of claim 2 , wherein the second heating circuit has a bypass valve for controlling the temperature of the compressor delivery air that is supplied to the rotor.
4. The system of claim 2 , further comprising a blade clearance probe, wherein at least one of the first heating circuit, the second heating circuit, the first cooling circuit or the second cooling circuit is controlled based at least in part on data from the blade clearance probe.
5. The system of claim 1 , further comprising:
a second cooling circuit in fluid communication with the compressor section and the blade ring, the second cooling circuit being in thermal communication with the heat exchanger; and
a second heating circuit in fluid communication with the compressor section and the rotor, the second heating circuit being in thermal communication with a heating device,
wherein during steady state operation the second cooling circuit extracts compressor delivery air from the compressor section, cools the compressor delivery air via the heat exchanger and supplies the compressor delivery air to the blade ring for cooling of the blade ring, and
wherein during steady state operation the second heating circuit extracts compressor delivery air from the compressor section, heats the compressor delivery air via the heating device and supplies the compressor delivery air to the rotor for heating of the rotor.
6. The system of claim 1 , wherein the first heating circuit has a compressor that compresses the hot exhaust gases prior to delivery to the blade ring.
7. The system of claim 6 , wherein the compressor has a compression ratio of 2:1.
8. The system of claim 1 , wherein the heat exchanger is a boiler.
9. A blade clearance control system for a turbine engine having a rotor assembly, a shell and a boiler, the system comprising:
a blade ring concentric with the rotor assembly and positioned radially outward from blade tips of the rotor assembly to define a gap therebetween;
a heating circuit in fluid communication with ambient air and the blade ring, the heating circuit having a compressor that provides compressed air prior to delivery to the blade ring; and
a cooling circuit in fluid communication with ambient air, the compressor, the boiler and the blade ring,
wherein during engine start up the heating circuit supplies the compressed air to the blade ring for heating of the blade ring, and
wherein during steady state operation the cooling circuit delivers the compressed air to the boiler and supplies the compressed air to the blade ring for cooling of the blade ring.
10. The system of claim 9 , further comprising a bypass valve for actuating the heating circuit or the cooling circuit.
11. The system of claim 9 , wherein the compressor has a compression ratio of 20:1.
12. The system of claim 9 , further comprising a blade clearance probe, wherein at least one of the heating circuit or the cooling circuit is controlled based at least in part on data from the blade clearance probe.
13. A method of blade clearance control in a gas turbine comprising:
positioning a blade ring concentric with a rotor assembly and radially outward from blade tips of the rotor assembly to define a gap therebetween;
during engine start up maintaining clearance by at least one of supplying cooling fluid to the rotor via a heat exchanger, supplying heating fluid to the blade ring from an exhaust duct, or supplying compressed ambient air to the blade ring; and
during steady state operation maintaining clearance by at least one of supplying cooling fluid from a boiler to the blade ring, supplying heating fluid to the rotor via a heating device, or supplying compressed ambient air through the boiler to the blade ring;
wherein during engine start up the supplying of cooling fluid to the rotor via the heat exchanger is compressor delivery air from a compressor section.
14. The method of claim 13 , wherein during steady state operation the supplying of heating fluid to the rotor via the heating device is compressor delivery air from a compressor section.
15. The method of claim 13 , wherein during engine start up the supplying of heating fluid to the blade ring from the exhaust duct is at a temperature of about 1000° F. and at a compression ratio of 2:1.
16. The method of claim 13 , wherein during steady state operation the supplying of compressed ambient air through the boiler to the blade ring is at a temperature of about 500° F.
17. The method of claim 16 , wherein during steady state operation the supplying of compressed ambient air through the boiler to the blade ring is at a compression ratio of 20:1.