Abstract A gas turbine combustion chamber having an outer casing and a concentrically mounted inner liner. The inner liner is formed with annular rows of spaced louvers for admitting cooling air and annular rows of spaced primary air holes. A shroud is circumscribed about the inner liner and spaced there from. Annular rows of spaced cooling air holes are formed in the shroud and direct jets of cooling air to hot spots or hot highly stressed areas between the louvers. The presence of the shroud makes it possible to increase the opening of the louvers for increasing the thickness of a cooling air film. The shroud also is formed with primary air holes which are slightly larger than and in approximate register with the primary air holes in the inner liner.
In a gas turbine combustion chamber of the type including an outer casing having a fuel nozzle disposed therein communicating with an inner liner concentrically mounted within the outer casing, said inner liner being formed with annular rows of spaced louver openings and annular rows of spaced primary air holes along the length thereof, and further including: a shroud surrounding the liner and spaced therefrom including a plurality of annular rows of spaced cooling air holes along the length of the shroud to overlie the areas between the annular rows of spaced louver openings; the shroud further including a plurality of annular rows of spaced primary air holes substantially in register with and larger than the primary air holes in the liner.
Claim 2
Dependent Claim
122 words
In a gas turbine combustion chamber of the type including an outer casing having a fuel nozzle disposed therein communicating with an inner liner concentrically mounted within the outer casing, said inner liner being formed with annular rows of spaced louver openings and annular rows of spaced primary air holes along the length thereof, and further including: a shroud surrounding the liner and spaced therefrom including a plurality of annular rows of spaced cooling air holes along the length of the shroud to overlie the areas between the annular rows of spaced louver openings; the shroud further including a plurality of annular rows of spaced primary air holes substantially in register with and larger than the primary air holes in the liner.
Claim 3
Dependent Claim
26 words
The combustion chamber recited in claim 1 wherein the cooling air holes are disposed to overlay hot spots on the inner liner between the louver openings.
Claim 4
Dependent Claim
48 words
The combustion chamber as recited in claim 1 wherein the primary air holes in the shroud are in the range 1.25 to 1.7 times larger in area than the primary air holes in the liner, the exact value dependent upon the spacing between the shroud and the liner.