A flight vehicle has an engine that includes air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes a bulged region that has at least one dimension, perpendicular to the direction of the air flow from the inlet to the combustor, that is at a local maximum, larger than comparable isolator dimensions both upstream and downstream of the bulged region. The bulged region stabilizes shocks within the isolator, and facilitates flow mixing. The flow diversion of high energy flow around the outermost walls of the bulged section into the center of the flow at the aft end of the isolator, increases mixing of the flow, and results in a more consistent flow profile entering the combustor over a wide range of flight conditions (Mach, altitude, angle-of-attack, yaw) and throttle settings.

In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture configured to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first channel directing a first air stream into the fuel conduit; and a second channel directing a second air stream into the fuel conduit. The first air stream and the second air stream cooperatively shape the fuel jet coming out of the fuel window.

In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture configured to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first channel directing a first air stream into the fuel conduit; and a second channel directing a second air stream into the fuel conduit. The first air stream and the second air stream cooperatively shape the fuel jet coming out of the fuel window.

A closed trapped vortex apparatus includes: a tubular structure having a structural wall, the structural wall forming a cavity within the tubular structure, the structural wall having a lower boundary wall forming a boundary between the cavity and a core flow passage; at least one driver hole passing through the structural wall; an ignition source communicating with the cavity; a fuel source communicating with the cavity; and a plurality of flame tubes extending through the lower boundary wall of the tubular structure at preselected locations so as to provide communication between the cavity and the core flow passage.

A closed trapped vortex apparatus includes: a tubular structure having a structural wall, the structural wall forming a cavity within the tubular structure, the structural wall having a lower boundary wall forming a boundary between the cavity and a core flow passage; at least one driver hole passing through the structural wall; an ignition source communicating with the cavity; a fuel source communicating with the cavity; and a plurality of flame tubes extending through the lower boundary wall of the tubular structure at preselected locations so as to provide communication between the cavity and the core flow passage.

The subject matter of this specification can be embodied in, among other things, a fuel delivery component, a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defined by the unitary structure as a first loop.

A nozzle tip for a premix fuel nozzle includes an outer body having an outer body external face facing the downstream end of the burner tube, the outer body external face having a smaller cross-sectional area than the cross-sectional area of the burner tube; and at least one segment radiating radially outwardly toward the internal wall of the burner tube from the outer body, wherein each segment has a proximal end disposed adjacent to the outer body external face and a distal end disposed in a direction toward the burner tube, wherein each segment has a segment downstream face angled relative to the longitudinal axis of the burner tube towards the downstream end of the burner tube. When the gas turbine is in operation, an axial flow field of an air and fuel mixture flows through the burner tube and around the nozzle tip, and two or more recirculation zones of differing radial extent are generated on the nozzle tip by the segments to provide strong flame holding and flame propagation.

A fuel nozzle includes a shroud; an injection cylinder surrounded by the shroud and configured to supply fuel to a combustion chamber; a swirler disposed between the injection cylinder and the shroud; and a porous disk disposed downstream of the swirler to surround an outer peripheral surface of the injection cylinder in order to prevent a flashback phenomenon occurring due to a reduction in pressure around the swirler. The porous disk includes a disk body to block a flame produced in the combustion chamber, and a plurality of flow holes are formed in the disk body through which the fuel flows. It is possible to prevent flashback by installing the porous disk downstream of the swirler, and to impart linearity and a swirling effect to the fuel passing through the fuel nozzle by forming variously configured flow holes in the porous disk.

A fuel nozzle includes a shroud; an injection cylinder surrounded by the shroud and configured to supply fuel to a combustion chamber; a swirler disposed between the injection cylinder and the shroud; and a porous disk disposed downstream of the swirler to surround an outer peripheral surface of the injection cylinder in order to prevent a flashback phenomenon occurring due to a reduction in pressure around the swirler. The porous disk includes a disk body to block a flame produced in the combustion chamber, and a plurality of flow holes are formed in the disk body through which the fuel flows. It is possible to prevent flashback by installing the porous disk downstream of the swirler, and to impart linearity and a swirling effect to the fuel passing through the fuel nozzle by forming variously configured flow holes in the porous disk.

The present invention generally relates to high g-field combustion methods and integrated processes requiring high-energy efficiency and low NOx emissions to maximize fuel productivity and integrated process production output. In one embodiment, the present invention relates to the combustor having a g-field greater than 100,000 g's in an isothermal configuration by achieving concurrent combustion and expansion with the high g-field combustor in a rim-rotor turbomachine.