ANNULAR COMBUSTOR FOR GAS TURBINE ENGINE, DESIGN METHOD THEREOF, AND METHOD FOR CONTROLLING FORMATION OF NOX IN GAS TURBINE ENGINE

摘要

PPROBLEM TO BE SOLVED: To provide a low-NOx discharge combustor for gas turbine engine. PSOLUTION: A combustor module for gas turbine includes a combustor 26, the combustor having a liner assembly that defines an annular combustion chamber having a length, L. The liner assembly includes an inner liner 32, an outer liner 34 and a bulkhead 36 having a height, H1, which extends between the respective forward ends of the inner liner and the outer liner. The liners 34 and 32 include forward and backward heat shields 46 and 48; 60 and 62, respectively. The combustor has an exit height H3 at the respective aft ends of the inner liner and the outer liner interior. The combustor has a ratio H1/H3 having a value less than or equal to 1.7 and a ration L/H3 having a value less than or equal to 6.0. A main air flow, a diluted air flow and a cooling air flow which are introduced into a combustion chamber 30 are controlled so as to distribute combustion air and reduce formation of NOx by a method such that it can reduce peak combustion temperature. PCOPYRIGHT: (C)2007,JPO&INPIT