Abstract: Systems and methods are provided herein useful to thrust augmentation in a gas turbine engine. In some embodiments, the systems include augmentors that incorporate a rotating detonation architecture. An exhaust system of a gas turbine engine includes an augmentor and a peripheral wall surrounding an exhaust system core. The augmentor comprises a detonation chamber disposed within the exhaust system core. The detonation chamber includes a channel formed in the peripheral wall. A core inlet path delivers a core air-fuel mixture and a pilot inlet path delivers a pilot air-fuel mixture to the detonation chamber. The core air-fuel mixture combusts in the detonation chamber along the midline the detonation chamber. The pilot air-fuel mixture detonates in the detonation chamber adjacent the peripheral wall to create a rotating detonation wave that supports the combustion reaction occurring along the midline of the detonation chamber.

Abstract: Systems and methods are provided herein useful to thrust augmentation in a gas turbine engine. In some embodiments, the systems include augmentors that incorporate a rotating detonation architecture. An exhaust system of a gas turbine engine includes an augmentor and a peripheral wall surrounding an exhaust system core. The augmentor comprises a detonation chamber disposed within the exhaust system core. The detonation chamber includes a channel formed in the peripheral wall. A core inlet path delivers a core air-fuel mixture and a pilot inlet path delivers a pilot air-fuel mixture to the detonation chamber. The core air-fuel mixture combusts in the detonation chamber along the midline the detonation chamber. The pilot air-fuel mixture detonates in the detonation chamber adjacent the peripheral wall to create a rotating detonation wave that supports the combustion reaction occurring along the midline of the detonation chamber.

Abstract: Systems and methods are provided herein useful to thrust augmentation in a gas turbine engine. In some embodiments, the systems include augmentors that incorporate a rotating detonation architecture. An exhaust system of a gas turbine engine includes an augmentor and a peripheral wall surrounding an exhaust system core. The augmentor comprises a detonation chamber disposed within the exhaust system core. The detonation chamber includes a channel formed in the peripheral wall. A core inlet path delivers a core air-fuel mixture and a pilot inlet path delivers a pilot air-fuel mixture to the detonation chamber. The core air-fuel mixture combusts in the detonation chamber along the midline the detonation chamber. The pilot air-fuel mixture detonates in the detonation chamber adjacent the peripheral wall to create a rotating detonation wave that supports the combustion reaction occurring along the midline of the detonation chamber.

Abstract: An adaptive trapped vortex combustor for a gas turbine engine includes a combustion chamber, a fuel injector, and one or more chutes. The combustion chamber is defined by an outer liner, an inner liner, and a dome, and includes a primary combustion zone within the combustion chamber defining a vortex cavity for a trapped vortex, the vortex cavity having a volume therein, a secondary combustion zone within the combustion chamber, and an opening from the primary combustion zone to the secondary combustion zone. The fuel injector injects a fuel into the primary combustion zone. The one or more chutes provide an air flow to the primary combustion zone and/or the secondary combustion zone. A feature of the adaptive trapped vortex combustor is controllable such that a residence time of the fuel in the vortex cavity is controllable based on an operating condition of the gas turbine engine.

Abstract: A combustion system may include a detonation combustor comprising one or more detonation chamber walls defining a detonation chamber, a deflagration combustor comprising one or more deflagration chamber walls defining a deflagration chamber, and one or more conjugate chamber walls defining a conjugate chamber, with the conjugate chamber in fluid communication with the detonation chamber and the deflagration chamber. The detonation chamber includes a detonation region and a nozzle region, with the nozzle region providing fluid communication between the detonation region and the conjugate chamber.

Abstract: An adaptive trapped vortex combustor for a gas turbine engine includes a combustion chamber, a fuel injector, and one or more chutes. The combustion chamber is defined by an outer liner, an inner liner, and a dome, and includes a primary combustion zone within the combustion chamber defining a vortex cavity for a trapped vortex, the vortex cavity having a volume therein, a secondary combustion zone within the combustion chamber, and an opening from the primary combustion zone to the secondary combustion zone. The fuel injector injects a fuel into the primary combustion zone. The one or more chutes provide an air flow to the primary combustion zone and/or the secondary combustion zone. A feature of the adaptive trapped vortex combustor is controllable such that a residence time of the fuel in the vortex cavity is controllable based on an operating condition of the gas turbine engine.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.