Improvements to the Performance of a Prototype Pulse, Pressure Gain, Gas-Turbine Combustor
Keyword(s):
A description is given of a simple, prototype, pulse, pressure-gain, combustor for a gas turbine. The work reported was targeted at alleviating problems previously observed with the prototype combustor. These were related to irreversibilities, causing a performance deficiency, in the secondary flow passage. The work consisted of investigating experimentally the effect of tuning the secondary-flow path-length, adding a flow restrictor at the combining-cone entry station and redesigning the combining-cone itself. The overall result was to eradicate the previously noted performance deficiency thereby increasing the maximum pressure-gain obtained in the gas turbine from 1.6% to 4.0% of the compressor absolute delivery pressure.
1990 ◽
Vol 112
(1)
◽
pp. 67-72
◽
Keyword(s):
2018 ◽
Vol 140
(7)
◽
Keyword(s):
2013 ◽
Vol 19
(3)
◽
pp. 327-333
◽
2006 ◽
Vol 372
(1)
◽
pp. 247-255
◽
Keyword(s):
2012 ◽
Vol 178-181
◽
pp. 1672-1675
2020 ◽
Vol 140
(3)
◽
pp. 70-71
Keyword(s):
Keyword(s):