You are here
A New Advanced System for Gas Turbine Combustors
Phone: (713) 790-9892
Cooling of the liner wall in gas turbine combustors has become increasingly difficult and problematic as engine pressure ratios are constantly increased. Existing cooling techniques have limitations in perfomance. At Energy Innovations, Inc., we have developed a new technology that has potential to effectively and efficiently solve the cooling problem for gas turbine combustors. One significant characteristic of our new technology is the capability of successfully preventing cooling air from merging with the hot gases without compromising the beneficial cooling effects. Our new advanced system for gas turbine combustors can greatly reduce the liner wall temperature, temperature gradients and fluctuations with significant reduction in the quantity of cooling air required. Our new advanced system can allow higher combustor inlet temperature and engine pressure ratio, thereby resulting in enhanced combustion efficiency and fuel economy. One more characteristic of our new advanced system is the capability of being dynamically tuned for operation at different working conditions. In Phase I, the feasibility of this new technology will be validated by preliminary model tests. Based upon mathematical modeling and experimental results, relationships among characteristic variables will be established. Upon completion of Phase I, II, and III, it is anticipated that the new advanced retrojet system for gas turbine combustors will more effectively and efficiently cool the liner of gas turbine combustors, significantly enhance combustion efficiency and fuel economy, greatly improve temperature capability and component durability, and considerably reduce combustion noise and pollutant emission levels. The applications for gas turbine with this advanced system include commercial and military aviation, electric power generation, gas-pipeline transmission, transportation, and many other industrial uses.
* Information listed above is at the time of submission. *