Patent ID: 6176075
Filing Date: 2001-01-23
Classification: F01K,F02C,F05D,F23L,F23M

Abstract:
A method of cooling a combustor and combustion gases of a gas turbine engine assembly of the type including a turbine, said combustor having a combustion chamber defining an axis and a burner disposed adjacent to one axial end of said combustion chamber, said burner arranged to receive a pressurized fuel/air mixture and generate products of combustion within said burner for delivery to said turbine through said combustion chamber in a direction parallel to said axis, the method comprising:delivering a substance to only said one axial end of said combustion chamber at a first energy phase;placing said substance at said first energy phase in heat exchange relation to said combustion chamber by forming an annular bath around said combustion chamber to absorb thermal energy from said combustion products within said combustion chamber and thereby converting said substance to a second energy phase, said second energy phase being at a higher level than said first energy phase; andinjecting said substance at said second energy phase into said combustion chamber at a plurality of locations spaced axially along the axial opposite end of said combustion chamber for mixture with said combustion products within said combustion chamber and subsequent delivery in a gaseous phase with said combustion products from said combustion chamber to said turbine.