Cooling system having a vortex tube and a fluidic oscillator for gas turbine blades
A cooling system for a gas turbine is disclosed comprising a vortex tube defining a body having an inlet port connectable to a compressor to receive compressed fluid. The vortex tube is configured to separate flow of the compressed fluid into a cold stream and a hot stream. The cooling system further includes a fluidic oscillator in fluid communication with the vortex tube, the first end of which is connected to a cold stream outlet port of the vortex tube to receive the cold stream. The fluidic oscillator is configured to generate at least two oscillator jets of the cold stream, operating at different oscillation frequencies, to produce biaxial pulsating flow oscillations onto a surface of at least one gas turbine blade of the gas turbine. A more efficient cooling system will result from the proposed cooling system's increased cooling impinging surface area and significantly reduced cooling fluid temperature differential.
1. A cooling system for a gas turbine, the cooling system comprising:
a vortex tube defining a body having an inlet port connectable to a compressor to receive compressed fluid, the vortex tube being configured to separate flow of the compressed fluid into a cold stream and a hot stream; and
a fluidic oscillator in fluid communication with the vortex tube, the fluidic oscillator defining a first end, a second end, and at least two outlet passages,
wherein the first end being connected to a cold stream outlet port of the vortex tube to receive the cold stream, and the fluidic oscillator being configured to generate at least two oscillator jets of the cold stream, operating at different oscillation frequencies, to produce biaxial pulsating flow oscillations onto a surface of at least one gas turbine blade of the gas turbine.
2. The cooling system according to claim 1 , wherein the at least two outlet passages are oriented orthogonal to one another.
3. The cooling system according to claim 1 , wherein the at least two outlet passages of the fluidic oscillator are configured to generate at least two oscillator jets.
4. The cooling system according to claim 1 , wherein the fluidic oscillator includes a flow passage defining an internal flow network configured to split the cold stream toward the at least two outlet passages.
5. The cooling system according to claim 4 , wherein the internal flow network comprises curved bifurcation paths configured to induce a phase shift between the at least two oscillator jets emitted from the at least two outlet passages.
6. The cooling system according to claim 1 , wherein the fluidic oscillator comprises a nozzle positioned at the second end, the nozzle being configured to direct the biaxial pulsating flow oscillations onto the surface of the at least one gas turbine blade.
7. The cooling system according to claim 1 , wherein the at least two oscillator jets produce biaxial sweeping jet patterns in vertical and horizontal directions over the surface of the at least one gas turbine blade.
8. The cooling system according to claim 1 , wherein the fluidic oscillator is a double-sided fluidic oscillator configured to direct pulsating flow to opposing surfaces of the at least one gas turbine blade.
9. The cooling system according to claim 1 , wherein the vortex tube comprises a hot stream outlet port having a throttle valve configured to control the temperature and flow rate of the cold stream.
10. The cooling system according to claim 1 , wherein the fluidic oscillator is configured to be received within an internal cavity of the at least one gas turbine blade of the gas turbine.
11. A gas turbine comprising:
at least one gas turbine blade; and
a cooling system in fluidic communication to the at least one gas turbine blade, the cooling system comprising:
a vortex tube defining a body having an inlet port connectable to a compressor to receive compressed fluid, the vortex tube being configured to separate flow of the compressed fluid into a cold stream and a hot stream; and
a fluidic oscillator in fluid communication with the vortex tube, the fluidic oscillator defining a first end, a second end, and at least two outlet passages,
wherein the first end being connected to a cold stream outlet port of the vortex tube to receive the cold stream, and the fluidic oscillator being configured to generate at least two oscillator jets of the cold stream, operating at different oscillation frequencies, to produce biaxial pulsating flow oscillations onto a surface of the at least one gas turbine blade of the gas turbine.
12. The gas turbine according to claim 11 , wherein the at least two outlet passages are oriented orthogonal to one another.
13. The gas turbine according to claim 11 , wherein the fluidic oscillator includes a flow passage defining an internal flow network configured to split the cold stream toward the at least two outlet passages.
14. The gas turbine according to claim 13 , wherein the internal flow network comprises curved bifurcation paths configured to induce a phase shift between the at least two oscillator jets emitted from the at least two outlet passages.
15. The gas turbine according to claim 11 , wherein the fluidic oscillator comprises a nozzle positioned at the second end, the nozzle being configured to direct the biaxial pulsating flow oscillations onto the surface of the at least one gas turbine blade.
16. The gas turbine according to claim 11 , wherein the at least two oscillator jets produce biaxial sweeping jet patterns in vertical and horizontal directions over the surface of the at least one gas turbine blade.
17. The gas turbine according to claim 11 , wherein the fluidic oscillator is a double-sided fluidic oscillator configured to direct pulsating flow to opposing surfaces of the at least one gas turbine blade.
18. The gas turbine according to claim 11 , wherein the vortex tube comprises a hot stream outlet port having a throttle valve configured to control the temperature and flow rate of the cold stream.
19. The gas turbine according to claim 11 , wherein the fluidic oscillator is configured to be received within an internal cavity of the at least one gas turbine blade of the gas turbine.