Abstract: A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of premixed fuel and air. The fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides effective mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction.

Abstract: A combustion device used in gas turbine engines that produces propulsion or rotates a shaft for power generation includes an annular combustor with a system of fuel and air inlet passages and nozzles that results in a flameless combustor, such that there is not an anchored flame as in typical gas turbine combustors. The fuel and air inlets are placed at various longitudinal locations and circumferentially spaced, and take on several different configurations where some nozzles inject only air and others inject a rich fuel-air mixture. The combustion device provides an optimal mixing of fuel and air as well as creates an environment for combustion that reduces pollutant emissions reducing the need for costly pollution control devices, and enhances ignition and flame stability, reduces piloting issues and improves vibration reduction.

Abstract: A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes an annular combustor with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air. The fuel and air inlets are placed at various longitudinal locations circumferentially, and can take on different configurations where all nozzles inject a fuel-air mixture or some may inject only air. The combustion device provides an optimal mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions reducing the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, allows increased fuel flexibility, decreases the required size of the first stage nozzle guide vane (NGV), and improves vibration reduction.

Abstract: A combustion device used in gas turbine engines includes an annular combustor that contains the combustion process of air and fuel and then guides the hot gas products to a first stage turbine subsection of a gas turbine engine. The annular combustor has an inner/outer shell having corrugated surfaces that extend radially outward and inward across an entire hot gas stream inside the annular combustor. The corrugations twist about the engine centerline in a longitudinal direction of travel of the engine. The resulting flow path accelerates and turns the hot gas stream to conditions suitable for introduction into the first stage turbine blades, which eliminate the need for first stage turbine vanes. The annular combustor is configured with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air.

Abstract: A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of fuel and air. Fuel, air and/or fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides an optimal mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction.

Abstract: A combustion device used in gas turbine engines includes an annular combustor that contains the combustion process of air and fuel and then guides the hot gas products to a first stage turbine subsection of a gas turbine engine. The annular combustor has an inner/outer shell having corrugated surfaces that extend radially outward and inward across an entire hot gas stream inside the annular combustor. The corrugations twist about the engine centerline in a longitudinal direction of travel of the engine. The resulting flow path accelerates and turns the hot gas stream to conditions suitable for introduction into the first stage turbine blades, which eliminate the need for first stage turbine vanes. The annular combustor is configured with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air.