Development of aero-derivative gas turbine dual fuel low emission combustion technology was studied

and major technical approaches to the success of the development were summarized. Range of fuel-air ratio of dual fuel combustor

effect of fuel-air ratio on CO and NOx emission

and design of transition operation were discussed; considerations in designing dual fuel low emission combustion were summarized comprehensively. By study of a variety of dual fuel lean premixed fuel-air modules

as well as long-term and lasting research and development on combustion test

the result shows that

the designed dual fuel combustion can meet the requirements of low pollution in the range of 50%-100% operation

and such low emission combustion technology and design of transient operation are practicable and can be directly used into the typical product of aero-engine.