The test and research results of the flow rate for the fuel injector group in a heavy-duty gas turbine have been expatiated.In order to measure the fuel gas flow in every branch in the fuel injector group

a SH-1 type testing device of gas flow rate has been specially developed.The said testing device has accurate stable performance and good reproducibility

and its cost is onlyfifith of that for the similar type instrument.By using said testing device

the flow rate of Ⅲ

Ⅳ

Ⅴ branches in the fuel injector group has been accurately measured

and the influence of technological process in fabrication and welding etc.upon the flow rate in a combined flow passage being analysed

and a combustion test of the injector group being made in a simple flame tube.Results show that the index in each item all meet the designed requirements

the radial temperature distribution coefficient at outlet of combustion chamber is less than 10%

the radial temperature distribution along the direction of blade height being resonable