A propulsion system is provided, wherein the propulsion system includes an afterburner assembly. The afterburner assembly including: an exhaust section and a fuel injector assembly that is operable to inject fuel in the exhaust section. The fuel injector assembly includes a plurality of fuel injection members. The plurality of fuel injection members defines a hot zone and a cold zone. The cold zone is positioned to provide a noise insulation barrier for the hot zone.

A swirl preburner that includes a first core defining a first swirl chamber having a first swirl chamber first end and a first swirl chamber second end, the first swirl chamber comprising a first diameter at the first swirl chamber first end and a second smaller diameter at the first swirl chamber second end that is smaller than the first diameter; and a second core defining a second swirl chamber having a second swirl chamber first end and a second swirl chamber second end, the second swirl chamber comprising a third diameter at the second swirl chamber first end and a fourth smaller diameter at the second swirl chamber second end that is smaller than the third diameter, the first diameter being smaller than the third diameter and larger than the fourth smaller diameter.

A combustion system comprising: a combustion chamber extending in an axial direction between an inlet and an outlet, the combustion chamber configured to receive an airflow through the inlet and to discharge the airflow through the outlet; a fuel injection port configured to inject fuel into the airflow to form an air-fuel mixture; an ignition system for igniting the air-fuel mixture in the combustion chamber, the ignition system comprising an array of electrical plasma initiation points disposed downstream of the fuel injection port, and distributed radially and circumferentially around the combustion chamber, wherein each electrical plasma initiation point comprises a pair of electrodes configured to apply a voltage across an electrode gap between the pair of electrodes to produce plasma within the air-fuel mixture passing between the electrodes, thereby igniting the air-fuel mixture.

A swirl preburner that includes a first core defining a first swirl chamber having a first swirl chamber first end and a first swirl chamber second end, the first swirl chamber comprising a first diameter at the first swirl chamber first end and a second smaller diameter at the first swirl chamber second end that is smaller than the first diameter; and a second core defining a second swirl chamber having a second swirl chamber first end and a second swirl chamber second end, the second swirl chamber comprising a third diameter at the second swirl chamber first end and a fourth smaller diameter at the second swirl chamber second end that is smaller than the third diameter, the first diameter being smaller than the third diameter and larger than the fourth smaller diameter.

Provided herein is a fuel injector capable of providing fuel into a jet engine operating at hypersonic speeds. Embodiments may include a system for fuel injection for an engine traveling at supersonic speeds. The system may include a fuel injection strut extending between opposing walls of an inlet to the engine, and a porous surface extending across at least a portion of the fuel injection strut. The fuel may be introduced into the inlet of the engine through the porous surface of the fuel injection strut. The porous surface of the fuel injection strut may extend along a fuel injecting portion of the fuel injection strut spaced a predefined distance from the opposing walls of the inlet. The porous portion of the fuel injection strut may include a porosity of about 100 pores per square inch or lower porosities as dictated by the specific design considerations.

Provided herein is a fuel injector capable of providing fuel into a jet engine operating at hypersonic speeds. Embodiments may include a system for fuel injection for an engine traveling at supersonic speeds. The system may include a fuel injection strut extending between opposing walls of an inlet to the engine, and a porous surface extending across at least a portion of the fuel injection strut. The fuel may be introduced into the inlet of the engine through the porous surface of the fuel injection strut. The porous surface of the fuel injection strut may extend along a fuel injecting portion of the fuel injection strut spaced a predefined distance from the opposing walls of the inlet. The porous portion of the fuel injection strut may include a porosity of about 100 pores per square inch or lower porosities as dictated by the specific design considerations.

A swirl preburner having a first swirl core defining a first swirl chamber having a first swirl chamber first end and a first swirl chamber second end. The swirl preburner further includes a second swirl core defining a second swirl chamber having a second swirl chamber first end and a second swirl chamber second end. The swirl preburner also includes a mixing element defining a mixing chamber, the mixing chamber surrounding a portion of the first and second chamber at least including the first chamber second end and the second chamber second end.

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 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 airflow conduit having a first orifice to discharge a first air stream into the core exhaust flow; and a second airflow conduit having a second orifice to discharge a second air stream into the core exhaust flow. The first orifice and the second orifice may be paired with the fuel window to 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 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 airflow conduit having a first orifice to discharge a first air stream into the core exhaust flow; and a second airflow conduit having a second orifice to discharge a second air stream into the core exhaust flow. The first orifice and the second orifice may be paired with the fuel window to 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 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 airflow conduit having a first orifice to discharge a first air stream into the core exhaust flow; and a second airflow conduit having a second orifice to discharge a second air stream into the core exhaust flow. The first orifice and the second orifice may be paired with the fuel window to cooperatively shape the fuel jet coming out of the fuel window.