Abstract: An assembly is provided that includes a slider seal having a washer and a tubular puck. The washer includes an inner washer surface and an outer washer surface. The inner washer surface extends around an axis of the slider seal and has a non-circular cross-sectional geometry. The inner washer surface forms a washer bore axially through the washer. The outer washer surface extends around the axis and has a cross-sectional geometry with a shape that is different than a shape of the non-circular cross-sectional geometry. The tubular puck projects axially through the washer bore and includes an outer puck surface. The outer puck surface extends around the axis. The outer puck surface is sealingly engaged with and configured to slide axially along the inner washer surface.

Abstract: A combustor or augmentor of a gas turbine engine is provided. The combustor or augmentor includes a wall defining apertures and an interior having an inlet, an outlet and a mixing region between the inlet and the outlet and fuel injectors. The fuel injectors are respectively arrayed along the wall at corresponding apertures to inject fuel into the mixing region. Each fuel injector includes a fuel injector body defining an injection outlet through which fuel exits the fuel injector body toward the mixing region and a pintle. The pintle includes a first end, a second end and a pintle body extending between the first and second ends. At least one of the first and second ends is attachable to the fuel injector body to position the pintle body between the injection outlet and the mixing region.

Abstract: An assembly is provided that includes a slider seal having a washer and a tubular puck. The washer includes an inner washer surface and an outer washer surface. The inner washer surface extends around an axis of the slider seal and has a non-circular cross-sectional geometry. The inner washer surface forms a washer bore axially through the washer. The outer washer surface extends around the axis and has a cross-sectional geometry with a shape that is different than a shape of the non-circular cross-sectional geometry. The tubular puck projects axially through the washer bore and includes an outer puck surface. The outer puck surface extends around the axis. The outer puck surface is sealingly engaged with and configured to slide axially along the inner washer surface.

Abstract: A fuel injection system for a gas turbine engine includes a fuel delivery conduit, a nozzle block with a nozzle aperture, and a cavity block with a cavity. The nozzle aperture has a first cross sectional area, and injects fuel received from the fuel delivery conduit into the cavity. The cavity has a second cross sectional area that is greater than the first cross sectional area.

Abstract: A combustor or augmentor of a gas turbine engine is provided. The combustor or augmentor includes a wall defining apertures and an interior having an inlet, an outlet and a mixing region between the inlet and the outlet and fuel injectors. The fuel injectors are respectively arrayed along the wall at corresponding apertures to inject fuel into the mixing region. Each fuel injector includes a fuel injector body defining an injection outlet through which fuel exits the fuel injector body toward the mixing region and a pintle. The pintle includes a first end, a second end and a pintle body extending between the first and second ends. At least one of the first and second ends is attachable to the fuel injector body to position the pintle body between the injection outlet and the mixing region.

Abstract: A fuel injection system for a gas turbine engine includes a fuel delivery conduit, a nozzle block with a nozzle aperture, and a cavity block with a cavity. The nozzle aperture has a first cross sectional area, and injects fuel received from the fuel delivery conduit into the cavity. The cavity has a second cross sectional area that is greater than the first cross sectional area.

Abstract: A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors. Each of the multiple of doors is operable to control a passage entrance into at least one of a multiple of circumferentially arrayed vanes with a respective strut flow passage which essentially alters its bypass ratio during flight to match requirements.

Abstract: A fuel injection system for a gas turbine engine includes a vane in an airflow path within the gas turbine engine, the vane includes an air channel with an outlet in communication with the airflow path; and a fuel nozzle within the vane operable to inject fuel into the air channel to at least partially premix and prevaporize the fuel with a secondary airflow from within the vane in the air channel prior to entry into the airflow path through the outlet. A method of injecting fuel within a gas turbine engine includes at least partially premixing and prevaporizing fuel with a secondary airflow from within a vane in an air channel within the vane, the vane within an airflow path of the gas turbine engine.

Abstract: A diffuser for a gas turbine engine includes an annular fluid passage that fluidly connects a diffuser inlet to a diffuser outlet. A plurality of airfoils are located in the annular fluid passage and each has a collection surface.

Abstract: A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors. Each of the multiple of doors is operable to control a passage entrance into at least one of a multiple of circumferentially arrayed vanes with a respective strut flow passage which essentially alters its bypass ratio during flight to match requirements.

Abstract: A gaspath component includes a flowpath body. A cooling plenum is disposed within the flowpath body. The cooling plenum includes a first region configured to receive a cooling flow and a second region configured to expel the cooling flow from the flowpath body. A metering obstruction is positioned between the first region and the second region and is configured to meter a flow of coolant through the cooling plenum.

Abstract: A trailing edge box for an augmentor vane includes an exterior-facing slot extending longitudinally along the trailing edge box. A monolithic spraybar provides fuel to a working environment of the augmentor vane. The monolithic spraybar includes a spray arm that is slidably inserted into the slot. A fuel aperture is integral with and extends into the spray arm. The fuel aperture receives fuel provided through a supply passage in the spray arm and provides the fuel to the working environment. The spray arm is disposed in the slot such that the fuel aperture is directly exposed to the working environment.

Abstract: A fuel injection system for a gas turbine engine includes a fuel nozzle with a fuel injection aperture to inject a fuel jet and a multiple of airflow passages in the fuel nozzle to communicate a multiple of air streams to interact with the fuel jet.

Abstract: A fuel injection system for a gas turbine engine includes a fuel nozzle with a fuel injection aperture to inject a fuel jet and a multiple of airflow passages in the fuel nozzle to communicate a multiple of air streams to interact with the fuel jet.

Abstract: A gaspath component includes a flowpath body. A cooling plenum is disposed within the flowpath body. The cooling plenum includes a first region configured to receive a cooling flow and a second region configured to expel the cooling flow from the flowpath body. A metering obstruction is positioned between the first region and the second region and is configured to meter a flow of coolant through the cooling plenum.

Abstract: A method for providing thermo-acoustic coupling of a gas turbine engine augmentor includes determining acoustic resonances and heat release phase relationships associated with the augmentor. A fuel injector of the augmentor is positioned at an axial position relative to a flame holder of the augmentor in response to the determined acoustic resonances and heat release phase relationships associated with the augmentor. Heat release and acoustic pressure oscillation cycles associated with the augmentor are out of phase by at least approximately 100 degrees.

Abstract: A method for operating a sensor, including simultaneously exciting a first set of electrodes and sensing an output of each electrode of a second set of electrodes, storing output data corresponding to the output of each electrode of the second set of electrodes in a memory storage device, shifting at least one electrode from the first set of electrodes to the second set of electrodes and at least one electrode from the second set of electrodes to the first set of electrodes, and repeating the simultaneously exciting and sensing, the storing, and the shifting until an output data has been stored for each possible pair of electrodes in the first and second set of electrodes.

Abstract: Aspects of the disclosure are directed to an engine of an aircraft. A first duct may be configured to convey a first flow, a second duct may be configured to convey a second flow that corresponds to a first portion of the first flow, and a third duct may be configured to convey a third flow that corresponds to a second portion of the first flow. At least one valve may be configured to control a cross-sectional area associated with at least one of the second duct or the third duct in order to control the ratio of the first portion to the second portion.

Abstract: A pulse detonation combustor may include a valve and a tubular combustor wall, which forms an airflow inlet and a combustion chamber. The valve may be configured to selectively fluidly couple the airflow inlet with the combustion chamber. The valve may include a center body and an annular projection. The center body and the projection may be configured to sealingly engage with one another.

Abstract: A method for operating a sensor, including simultaneously exciting a first set of electrodes and sensing an output of each electrode of a second set of electrodes, storing output data corresponding to the output of each electrode of the second set of electrodes in a memory storage device, shifting at least one electrode from the first set of electrodes to the second set of electrodes and at least one electrode from the second set of electrodes to the first set of electrodes, and repeating the simultaneously exciting and sensing, the storing, and the shifting until an output data has been stored for each possible pair of electrodes in the first and second set of electrodes.