Abstract: In a staged low NOx lean premix hot wall gas turbine combustor, the interior wall of the combustor is maintained at or near the flame temperature to provide stable operation over a wide range of heat release values. One or more stages of the staged combustor includes a Stirred Reactor region followed by a Plug Flow Reactor region. In one embodiment, a lean premixture of fuel and air is inducted tangentially into an annular intake manifold for inducting a cyclonic flow of the premixture into the combustion chamber. In another embodiment, the Stirred Reactor region is developed by colliding, preferably head-on, a plurality of jets of lean premixture within the combustion chamber.

Abstract: A staged low NO.sub.x 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.

Abstract: In a staged lean premix low NOx gas turbine combustor, the inside of the combustor is lined with a low density refractory thermal insulator for maintaining the hot face of the lining at or near the flame temperature, i.e., within 200.degree. F. and preferably within 50.degree. F. The heat release value in the first stage is held at a maximum value consistent with low NOx emission while decreasing the heat release value in the second or third stage to achieve a wide range of turndown. The flame temperature in the respective stages are maintained between a low of 1700.degree. F. and a maximum of 2700.degree. F. The flow of compressed air into the combustor is maintained generally uniform over the entire operating range of 5 to 1 turndown.

Abstract: A gas turbine combustor is ignited by a torch igniter. The ignition chamber of the torch igniter receives a swirled stream of air into which is injected atomized fuel. The mixture of fuel and air is ignited by a spark plug in the ignition chamber. The combustion products and igniter flame are exhausted from the ignition chamber through a gas passageway penetrating through the sidewall of the gas turbine combustor to ignite a flame in the combustor. The igniter flame and the combustion flame are detected by a U.V. detector looking through aligned igniter air inlet and igniter exhaust passageways into the combustor. A U.V. transmissive window is disposed in the air inlet passageway to isolate the detector from the pressure of the igniter and combustor. A swirler in the air inlet tubulation supplies a flow of air across the window to inhibit deposit of combustion products thereon.

Abstract: In a low NO.sub.x stage combustor, the hot fuel rich combustion gases exit the primary combustion chamber through a constriction including a throat portion and pass into a secondary combustion chamber wherein burning is completed by injection of secondary air such as the exhaust from a turbine. Swirl is imparted to the primary gas stream in the primary combustion chamber so as to cause the primary gas stream to fill the entire primary combustion chamber and for increasing the residence time within the primary chamber for reducing fuel NO.sub.x emissions. Swirl suppression means are employed in the throat of the flow constrictor, between the primary and secondary combustion chambers, for suppressing swirl in the outermost regions of the primary gas stream so as to reduce turbulent mixing with the injected, secondary air thereby reducing the peak flame temperature in the secondary combustion chamber and for reducing thermal NO.sub.x emissions.

Abstract: A low NO.sub.x staged combustor for a TEOR steam generator includes a primary combustion chamber lined with an improved refractory lining. The refractory lining includes a first layer of low density ceramic fibrous thermal insulation as of 4" in thickness coated on its hot face with a protective coating of a durable tough material. The ceramic fibers of the insulative layer are oriented normal to the plane of the hot face. In one embodiment, a low density castable refractory thermally insulative layer is sandwiched between the shell of the combustion chamber and the first layer of fibrous insulation. In a second embodiment, a low density thermally insulative ceramic fibrous layer is sandwiched between the shell of the combustion chamber and the first layer of fibrous insulation. In the second embodiment, the ceramic fibrous layers are adhered to the shell by refractory hangers embedded in the fibrous insulation and resistance welded to the shell.

Abstract: In a low NO.sub.x power and steam generator for thermally enhanced oil recover, a gas turbine fired with nitrogen-bearing crude oil and air produces power and hot turbine exhaust. A portion of the turbine exhaust is fed into the primary combustion chamber of a two-stage combustor for supplying the combustion air for burning a high nitrogen-containing crude oil in the primary combustion zone under fuel-rich conditions. The combustion is completed in a secondary combustion zone supplied with air derived from a second portion of the turbine exhaust at about 1200.degree. F. A third portion of the turbine exhaust is fed into a convection stage disposed to receive the exhaust from the secondary combustion zone for capturing the heat from the turbine exhaust and from the exhaust of the secondary zone and converting it to steam.