Abstract: A low-NO.sub.x combustor is provided with a rich, primary burn zone and a lean, secondary burn zone. NO.sub.x formation is inhibited in the rich burn zone by an oxygen deficiency and in the lean burn zone by a low combustion reaction temperature.

Abstract: Apparatus and method for starting a gas turbine engine is shown wherein the combustion chamber has a fixed geometry providing a high throughput velocity to prevent flashback during normal operation of the engine. Thus, there is provided a flame holding zone out of the main flow path through the chamber that exhausts into the chamber upstream of a catalytic reactor element to preheat the catalyst to a sufficiently high temperature for continuous auto-combustion therein prior to the rotor of the engine attaining running speed. After running speed the combustion in the flame holding zone is extinguished and the velocity of the fuel/air mixture in the main flow path through the chamber is sufficient to maintain the combustion within the catalytic element for the continuous running of the engine without any flashback.

Abstract: A combustor for a gas turbine engine which includes a fuel nozzle at the head end of the combustor, to provide a diffusion flame, and downstream inlet means at a plurality of axial dimensions of the combustor to inject pre-mixed lean fuel/air into the combustor for admission downstream from the diffusion flame resulting in a series of low temperature premixed flames to provide relatively high turbine inlet temperatures from the combustor with a minimum of thermally formed NOx compounds.

Abstract: An interconnection or crossover construction is provided for interconnecting the combustors of a combustion apparatus such as a gas turbine. The connection between adjacent combustors is made by means of a flexible tube which permits a substantial amount of misalignment between adjacent combustors, and the construction also provides for accommodating thermal expansion and contraction of the parts and for the admission of cooling air.

Abstract: A catalytic combustor arrangement for use with a gas turbine power plant, has independently regulatable fuel injection elements disposed upstream of a discrete array of passageways disposed between the fuel injection elements and a catalytic reaction member. The centermost fuel injection elements of each combustor may function alone which will permit efficient idling operation of the power plant. The passageways will maintain the flow of fuel and air to only the central portion of each catalytic reactor element thus providing the efficient, low speed, idling, operation of the turbine. As additional fuel injection elements are activated, additional portions of the catalytic reaction member perform the combustion function at the desired level of turbine operation. Thus a wide range of operating conditions of the gas turbine is efficiently permitted with the regulatable fuel injection arrangement therewith.

Abstract: A catalytic combustor has an array of fuel injectors and air inductor elements, upstream of a catalytic member in the combustor. Each fuel injector and air inductor arrangement is associated with a discrete passageway confining the air/fuel mixture to a portion of and the catalytic member wherein the combustion of the mixture is initiated. Each fuel injector and air inductor arrangement is provided with controls to vary the fuel and air flowing into each passageway, respectively. This permits the variation of combustion intensity within the catalytic element, which in turn permits a regulatable temperature profile at the exit end of the combustor.