LOW CALORIFIC FUEL COMBUSTOR FOR GAS TURBINE

摘要

A low calorific value fuel-fired can combustor for a gas turbine include a generally cylindrical housing, and a generally cylindrical liner disposed coaxially within the housing to define with the housing a radial outer flow passage for combustion air, the-liner also defining inner combustion and a dilution zone, the dilution zone being axially distant a closed housing end relative to the combustion zone. A nozzle assembly disposed at the closed housing end includes an air blast nozzle and surrounding swirl vanes. An impingement cooling sleeve coaxially disposed in the combustion air passage between the housing and the liner impingement cools the portion of the liner defining the combustion zone. The combustion liner has an L/D ratio of in the range 1= L/D= 4, and a ratio of the combustion zone volume (m3) to heat energy flow rate Q (MJ/sec) in the range 0.0026 < V/Q < 0.018.