Patent ID: 6931862

Claim:
A combustion system for a miniature gas turbine engine comprising: an annular combustor liner having an outer wall; a plurality of fuel-air tubes extending into said annular combustor liner outer wall adjacent a leading segment of said combustor liner to form a primary burning region which approximates a well-stirred reactor; a plurality of secondary air only-feed tubes extending into said annular combustor liner outer wall downstream of said purality of fuel-air tubes to form a secondary burning region which approximates a well-stirred reactor to provide a near-stoichiometric fuel/air ratio; a plurality of dilution air only-feed tubes through said annular combustor liner outer wall downstream of said plurality of secondary air-feed tubes and which form a final dilution mixing region adjacent a combustor exit; and a fuel manifold which communicates fuel through a fuel orifice in at least one of said plurality of fuel-air tubes to provide a fuel/air stoichiometry in said primary burning region which tends towards rich stoichiometry at full engine power operating conditions.