Abstract: A combustor assembly for a gas turbine engine includes a combustor liner disposed about an axis and defining a combustion chamber and an outer case disposed about the combustor liner and defining an air flow duct therebetween. The combustor liner includes an outer wall having a plurality of mounting bosses and a plurality of first holes open to the combustion chamber. The outer case includes a plurality of inlet scoops extending radially inward of the outer case and radially aligned with the plurality of first holes to guide an air flow into first holes. A plurality of pins is fixed to the outer case and slidingly received in openings in the plurality of mounting bosses.

Abstract: A combustor system for an aerial vehicle includes an outer liner with a first end and a second end, an inner combustor case contained within the outer liner and defining a central combustor chamber, a lumen extending into the central combustor chamber, an air flow path extending between the outer liner and the inner combustor case, an integrated air scoop attached to the inner combustor case at the lumen and directing air from the air flow path into the central combustor chamber, and a fuel bolt, the fuel bolt including a head located outside of the outer liner and a body starting outside of the outer liner and extending perpendicular to the outer liner through the outer liner, through the integrated fuel scoop, and ending at the lumen, and fuel manifold with a fuel orifice within the fuel bolt.

Abstract: A combustor for rich-quench-lean combustion includes a combustor shell, a combustion chamber delimited by the combustor shell, and fuel injectors. The combustion chamber includes a primary zone, a quench zone, a secondary zone, and an outlet arranged in axial flow series. Openings through the combustor in the quench zone provide a quench air flow into the quench zone. A method for rich-quench-lean combustion for the combustor includes contemporaneously injecting a rich air-fuel mixture into the primary zone and injecting a second air flow into the quench zone in which the second air flow is equal to or less than four times the primary air flow.

Abstract: An injector for a combustor and a gas turbine engine with the same includes a stem extending from a mount to a nozzle and a swirler. The nozzle extends from the stem along an axis. The nozzle includes a center body and a fuel passage. The swirler circumscribes the nozzle and includes an inner air passage and an outer air passage. An array of circumferentially-spaced inner vanes within the inner air passage each form an inner acute angle with the axis. An array of circumferentially-spaced outer vanes within the outer air passage each form an outer acute angle less than the first acute angle.

Abstract: A fuel delivery system for a combustor of a gas turbine engine. The fuel delivery system having a primary fuel tank configured to store liquid hydrogen and a secondary fuel tank configured to store fuel, such as Jet A or SAF. The fuel being provided and mixed in the jet engine to alleviate the production of contrails. In addition, the primary fuel tank may be a cryogenic tank to enable the storage of liquid hydrogen, or liquid natural gas. As a result, the primary fuel may be utilized to cool the secondary fuel and/or the gas turbine engine.

Abstract: A gas turbine engine includes a compressor configured to receive inlet air at a compressor inlet and generate compressed air at a compressor exit, a combustor positioned fluidically and physically downstream of the compressor, a turbine positioned fluidically and physically downstream of the combustor, and a shaft mechanically connecting the turbine and the compressor. The combustor is fluidically connected to the compressor to receive a first portion of the compressed air as combustor primary inlet air. The combustor includes a combustor liner having an inner combustor liner and an outer combustor liner, surrounding one or more combustion zones. A cooling air flow path is configured to direct a second portion of the compressed air around the outer combustor liner to cool the combustor liner and to provide a source of quench air, inner combustor liner cooling air, fuel injector air, and combustor secondary inlet air.

Abstract: A combustor system for an aerial vehicle includes an diffuser case with a first and second end and a large and small radius section, an inner diffuser wall contained within the diffuser case, the inner diffuser wall with a lumen, a central combustor chamber, a first air flow path extending between the diffuser case and inner diffuser wall, an integrated air scoop attached to the inner diffuser wall at the first lumen that directs air from the first air flow path into the central combustor chamber, a fuel manifold and fuel orifice within the integrated air scoop, and a splash plate comprising with a first and second face. The splash plate extends through the lumen into the central combustor chamber. The large radius section is aligned with the inner diffuser wall away from the splash plate and the small radius section is aligned with the splash plate.

Abstract: A gas turbine engine includes a compressor configured to receive inlet air at a compressor inlet and generate compressed air at a compressor exit, a combustor positioned fluidically and physically downstream of the compressor, a turbine positioned fluidically and physically downstream of the combustor, and a shaft mechanically connecting the turbine and the compressor. The combustor is fluidically connected to the compressor to receive a first portion of the compressed air as combustor primary inlet air. The combustor includes a toroidal recirculation zone configured to receive and combust fuel in a rich combustion zone, an ignitor positioned to ignite an air/fuel mixture in the rich combustion zone, a rapid quench zone downstream of the toroidal recirculation zone, a lean combustion zone downstream of the rapid quench zone, and a cooling air flow path configured to direct a second portion of the compressed air around an outer combustor liner.

Abstract: A gas turbine engine include a compressor configured to receive inlet air at a compressor inlet and generate compressed air at a compressor exit, a combustor positioned fluidically and physically downstream of the compressor, a turbine positioned fluidically and physically downstream of the combustor, and a shaft mechanically connecting the turbine and the compressor. The combustor is fluidically connected to the compressor to receive a first portion of the compressed air as combustor primary inlet air and also includes a toroidal recirculation zone configured to receive and combust fuel in a rich combustion zone, an ignitor positioned to ignite an air/fuel mixture in the rich combustion zone, a rapid quench zone downstream of the toroidal recirculation zone, a lean combustion zone downstream of the rapid quench zone, and a cooling air flow path.

Abstract: A gas turbine engine includes a compressor configured to receive inlet air at a compressor inlet and generate compressed air at a compressor exit, a combustor positioned fluidically and physically downstream of the compressor, a turbine positioned fluidically and physically downstream of the combustor, and a shaft mechanically connecting the turbine and the compressor. The combustor is fluidically connected to the compressor to receive a first portion of the compressed air as combustor primary inlet air. The combustor includes a combustor liner having an inner combustor liner and an outer combustor liner, surrounding one or more combustion zones. A cooling air flow path is configured to direct a second portion of the compressed air around the outer combustor liner to cool the combustor liner and to provide a source of quench air, inner combustor liner cooling air, fuel injector air, and combustor secondary inlet air.

Abstract: A gas turbine engine includes a compressor configured to receive inlet air at a compressor inlet and generate compressed air at a compressor exit, a combustor positioned fluidically and physically downstream of the compressor, a turbine positioned fluidically and physically downstream of the combustor, and a shaft mechanically connecting the turbine and the compressor. The combustor is fluidically connected to the compressor to receive a first portion of the compressed air as combustor primary inlet air and also includes a toroidal recirculation zone configured to receive and combust fuel in a rich combustion zone, an ignitor positioned to ignite an air/fuel mixture in the rich combustion zone, a rapid quench zone downstream of the toroidal recirculation zone, a lean combustion zone downstream of the rapid quench zone, and a cooling air flow path configured to direct a second portion of the compressed air around an outer combustor liner.

Abstract: A military vehicle includes a cabin. The cabin includes a bottom assembly and a foldable top assembly. The bottom assembly is configured to receive and removably couple with different top assemblies. The foldable top assembly is configured to transition between a folded position for a low velocity aerial drop (LVAD) and a deployed position. The foldable top assembly includes a torsional spring configured to provide a torque to assist transitioning of the foldable top assembly from the folded position to the deployed position.

Abstract: Embodiments include systems, methods and devices for the percutaneous delivery of therapeutic agents to tendons, ligaments and muscle. Certain embodiments include a device comprising a needle-catheter based delivery system with adjustable characteristics to allow a clinician to control the angle and depth of needle and/or catheter deployment to a desired location. System embodiments may include a controller unit where a clinician can adjust the axial position depth and location of needles and/or catheters.

Abstract: Embodiments include systems, methods and devices for the percutaneous delivery of therapeutic agents to tendons, ligaments and muscle. Certain embodiments include a device comprising a needle-catheter based delivery system with adjustable characteristics to allow a clinician to control the angle and depth of needle and/or catheter deployment to a desired location. System embodiments may include a controller unit where a clinician can adjust the axial position depth and location of needles and/or catheters.

Abstract: A concealable cantilever support has a first leg extending from an outward end to an inward end, and near its inward end at least one adjusting hole; and a second leg orthogonal to the first leg, and integrally joined at an inward end thereof to the inward end of the first leg, inward faces of the first and second legs facing each other without intervening material. A portion of the first leg distal from the adjusting hole is restrained flat to the hidden face of the wall, the second leg protrudes from a roomward face of the wall with its outward face upward and orthogonal to the wall, a portion of the first leg adjacent the adjusting hole is free to flex away from the hidden face of the wall by actuation of an adjusting screw inserted through the adjusting hole.

Abstract: A gas turbine engine augmentor nozzle has an inlet for connection to an augmentor fuel conduit and an outlet for expelling a spray of fuel. A passageway between the inlet and outlet is at least partially bounded by outlet end surface portions diverging from each other. The nozzle may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline toward radial.

Abstract: An exit guide vane array for a turbine engine includes a set of guide vanes 28 having a solidity and defining fluid flow passages 74 with a chordwisely converging forward portion 80. The high solidity and convergent passage portion 80 resist fluid separation. The vanes may also cooperate with each other to restrict an observer's line of sight to planes upstream of the vane array.

Abstract: An apparatus for inspection of fluids having a fluid analysis cell with a cavity therein enclosed by two light transmitting windows and having a spacer member fixedly positioned therebetween which provides a fluid analysis chamber of fixed pathlength where fluid flows by the windows and preferably wherein the flow laminar and at a uniform shear to provide accurate color measurements. Light transmitting and receiving probes are positioned adjacent to the viewing windows and wherein the faces of each probe are contiguous and flush with the viewing windows but are separated from the flow by the viewing windows, so that transmission measurements can be taken orthogonal to the direction of flow. The apparatus is particularly useful in the manufacture of dispersions and tints used in the manufacture of paints, so that the color of material being made can be accurately matched to a standard color in the wet state with confidence that the color will match in the dry state.