Fuel efficient ultra-low emission and improved pattern factor colorless distributed combustion for stationary and propulsion gas turbine applications
Colorless distributed combustion (CDC) reactors or green combustion gas turbine combustors having a combustion chamber are presented for improved performance of gas turbine combustion engines. The combustors are configured and designed for providing a superior pattern factor (uniform thermal field in the combustion zone) and a reduction or complete elimination of pollutants emission from the combustor (i.e., zero emission gas turbine combustor) and uniform thermal field in the entire combustion zone to provide significantly improved pattern factor. Colorless distributed combustion is achieved with fuel and air entering the combustion chamber via one or more injection ports as non-premixed, or premixed. Rectangular, cylindrical, stadium and elliptical shaped combustors are presented with injection ports and exit ports located in various locations of the combustors. The mixture preparation between fuel and air with the hot combustion products is carried out either with the gases present in the combustion chamber or via a communication link between the exit gases from the combustor back to the combustion chamber.
1. A gas turbine combustor comprising:
a housing defining first and second arcuate surface portions and defining a combustion chamber;
at least one first fluid injection port extending through the first arcuate surface portion of the housing and in fluid communication with the combustion chamber;
at least one second fluid injection port extending through the first arcuate surface portion of the housing and in fluid communication with the combustion chamber; and
an exit port located on the first arcuate surface portion of the housing and in fluid communication with the combustion chamber;
wherein the at least one first fluid injection port, the at least one second fluid injection port, and the exit port are located on the first arcuate surface portion of the housing such that during operation a heated oxidizer fluid is introduced into the combustion chamber via the at least one first fluid injection port and fuel is introduced into the combustion chamber via the at least one second fluid injection port to cause ignition and colorless distributed combustion to occur within the combustion chamber creating a single uniform thermal field within the housing, and
wherein the combustion byproducts exit the combustion chamber via the exit port.
2. The gas turbine combustor according to claim 1 , wherein the housing is selected from the group consisting of rectangular, square, circular, stadium and elliptical shaped housings, and wherein the at least one first fluid injection port is located on a side of the first arcuate surface portion of the housing which is opposite a side of the first arcuate surface portion of the housing where the at least one second fluid injection port is located.
3. The gas turbine combustor according to claim 1 , wherein the housing is selected from the group consisting of cylindrical and elliptical shaped housings, and wherein the exit port is located on a lateral side of the first arcuate surface portion of the housing.
4. The gas turbine combustor according to claim 1 , wherein the housing is selected from the group consisting of cylindrical, stadium and elliptical shaped housings, and wherein the exit port is located on an outer circular surface of the first arcuate surface portion of the housing.
5. The gas turbine combustor according to claim 1 , wherein the housing is selected from the group consisting of cylindrical, stadium and elliptical shaped housings, and wherein the at least one first injection port and the at least one second injection port are located along an outer circular surface of the first arcuate surface portion of the housing.