Abstract: A flameless cooking apparatus for use with liquid fuels and for indoor or outdoor use under field operations. The burner exhibits low CO and hydrocarbon emissions and meets standards for burner thermal efficiency when used with JP-8 fuel. The apparatus employs a catalytic burner having among its parts (i) a combustion catalyst; (ii) a conductive surface, e.g., cooking surface; and (iii) in between the catalyst and the conductive surface and in direct physical contact with both surfaces, a heat spreader for conductively transferring heat of combustion from the catalyst to the conductive surface. Also claimed are a method of heat flux and a method of cooking.

Abstract: A method for low NOx combustion, without premixing of fuel and air prior to passage to a combustor, is provided wherein a fuel is injected into a reaction zone via an eductor thereby inducing an air flow and producing a fuel-rich mixture. The fuel-rich mixture is reacted and produces partial reaction products plus heat. A portion of the heat is to transferred to a cooling air stream and the cooled partial reaction products are brought into contact with the heated cooling air stream for combustion. Increased injection of the fuel results in an increased induction of the air flow.

Abstract: The present invention provides a combustor for an aerospace gas turbine engine comprising two stages wherein each stage defines an inlet and an exit. The second stage inlet is in fluid communication with the first stage exit such that a first flowpath is defined and it passes substantially through the second stage. A plurality of flow channel tubes is positioned within the second stage and each flow channel tube passes sealingly through a header plate positioned upstream of the second stage inlet thereby defining a second flowpath that also passes substantially through the second stage. The first flowpath exit and the second flowpath exit are positioned adjacent and proximate to one another to provide for the generation of microflames or microflame jets exiting the second stage from between and around the flow channel tube exits. The first stage of the combustor provides a gasifier and a reformer.

Abstract: The invention provides an apparatus for generating heat and transferring the heat to a heater head of an external combustion engine, preferably, a Stirling engine. Fuel and air are introduced into a combustion chamber and mixed to form an air/fuel mixture. The air/fuel mixture is combusted over a combustion catalyst positioned in physical contact with a heat spreader, which itself is positioned in physical contact with a heat acceptor surface. The heat acceptor surface is secured in thermal communication with the heater head. Depending upon the design of the heater head, heat flux from the heat acceptor surface into the heater head may occur radially or non-radially.

Abstract: A flameless cooking apparatus for use with liquid fuels and for indoor or outdoor use under field operations. The burner exhibits low CO and hydrocarbon emissions and meets standards for burner thermal efficiency when used with JP-8 fuel. The apparatus employs a catalytic burner having among its parts (i) a combustion catalyst; (ii) a conductive surface, e.g., cooking surface; and (iii) in between the catalyst and the conductive surface and in direct physical contact with both surfaces, a heat spreader for conductively transferring heat of combustion from the catalyst to the conductive surface. Also claimed are a method of heat flux and a method of cooking.

Abstract: The invention provides an apparatus for generating heat and transferring the heat to a heater head of an external combustion engine, preferably, a Stirling engine. Fuel and air are introduced into a combustion chamber and mixed to form an air/fuel mixture. The air/fuel mixture is combusted over a combustion catalyst positioned in physical contact with a heat spreader, which itself is positioned in physical contact with a heat acceptor surface. The heat acceptor surface is secured in thermal communication with the heater head. Depending upon the design of the heater head, heat flux from the heat acceptor surface into the heater head may occur radially or non-radially.

Abstract: The present invention provides a combustor for an aerospace gas turbine engine comprising two stages wherein each stage defines an inlet and an exit. The second stage inlet is in fluid communication with the first stage exit such that a first flowpath is defined and it passes substantially through the second stage. A plurality of flow channel tubes is positioned within the second stage and each flow channel tube passes sealingly through a header plate positioned upstream of the second stage inlet thereby defining a second flowpath that also passes substantially through the second stage. The first flowpath exit and the second flowpath exit are positioned adjacent and proximate to one another to provide for the generation of microflames or microflame jets exiting the second stage from between and around the flow channel tube exits. The first stage of the combustor provides a gasifier and a reformer.