초록 ▼

A staged low NOx gas turbine combustor includes a refractory fibrous thermally insulatively lined primary combustion chamber, operating fuel-rich, and exhausting through a throat into a metallic secondary combustion chamber containing a fuel-lean secondary combustion zone in which combustion is comp

A staged low NOx gas turbine combustor includes a refractory fibrous thermally insulatively lined primary combustion chamber, operating fuel-rich, and exhausting through a throat into a metallic secondary combustion chamber containing a fuel-lean secondary combustion zone in which combustion is completed. A radiation cooling zone is provided intermediate the throat and secondary combustion zone for cooling of the primary combustion products before quick quench in the secondary combustion zone. The fibrous lining of the primary combustion chamber is densified at its interior surface with a refractory such as zirconia or silicon carbide to inhibit flame erosion. The liner is wrapped with a supportive compliant blanket of fibrous refractory insulation. Air cooling of the metallic wall of the secondary chamber surrounding the radiation cooling zone is intensified relative to the remainder of the secondary combustion chamber.

대표청구항 ▼

In a staged gas turbine combustor having a primary combustion chamber for containing a fuel-rich combustion zone followed by a secondary combustion chamber for containing a secondary combustion zone for combusting the unburned combustion products exhausting from said primary combustion chamber: line

In a staged gas turbine combustor having a primary combustion chamber for containing a fuel-rich combustion zone followed by a secondary combustion chamber for containing a secondary combustion zone for combusting the unburned combustion products exhausting from said primary combustion chamber: liner means for lining the interior wall of said primary combustion chamber with a layer of porous fibrous refractory thermally insulative material; and coating means infiltrated into said lining material from the interior wall thereof for coating the fibers of said fibrous lining material with a coating of refractory coating material so as to produce a radial gradient in the density of the resultant coated fibrous lining with decreasing density taken in the radial direction from the interior surface thereof toward the outer surface thereof, whereby the interior region of the infiltrated and coated refractory lining is rendered resistant to erosion by combustion products within the primary combustion chamber of the gas turbine combustor.