Abstract: An example turbomachine assembly includes a plurality of fuel spraybars spaced about a turbine exhaust inner case of the turbomachine. At least one fuel injector assembly is associated with each of the fuel spraybars. The at least one fuel injector assembly may include a fuel nozzle having a fuel delivery conduit. The at least one fuel injector assembly includes a seal member that is biased away from the fuel nozzle in a direction. The fuel nozzle is configured to limit movement of the seal member in the direction.

Abstract: Integrally formed, multi zone fuel manifolds for gas turbine engines and methods of construction are provided. The fuel manifold includes a plurality of annular channel members positioned adjacent each other, aligned and coupled together at the inner and outer peripheral sides thereof, with each pair of channel members defining a separate fluid conduit or passage within the manifold assembly. The fuel manifold can be constructed of any number of stacked and secured channel members to provide a compact multi zone fuel manifold having the desired number of fluid conduits or passages with a minimum number of sealed joints.

Abstract: A flame holder for an augmentor includes geometry to produce large radial variations in heat release to prevent coupling with modes within the exhaust duct that produce combustor screech. A surface of the flame holder varies axially in a radial direction to produce a radial phase variation in heat released from the flame holder. The radially changing surface produces radially non-uniform and unsteady heat release that does not couple with acoustic modes within the exhaust duct.

Abstract: A device attaching an afterburner to a turbojet casing. The device comprises a transverse plate for attachment to the casing and at least two side brackets for supporting two legs of the afterburner. The brackets and the two legs extend longitudinally. The afterburner includes a flame-arrestor arm with the two legs.

Abstract: A flameholder arm for an afterburner of a turbomachine, particularly a jet engine, is disclosed. The arm includes a ventilation duct which is centered and immobilized inside the arm independent of the heatshield. The duct also includes a transverse lip which includes an orifice for centering and guiding a fuel injection harness. The transverse lip prevents the harness from being positioned in any way incorrectly in the arm.

Abstract: A flameholder for an augmentor rotates about an axis radially positioned with a turbine engine. The flameholder is in a streamlined position when the augmentor is not operating to minimize pressure loss and radar cross-section and a turbulent position when the augmentor is operating. A linkage connects the flameholder to an actuator to control the rotational position of the flameholder on the axis. Bypass airflow from the fan cools the flameholders and linkages. The length of the linkages can be varied from one flameholder to another to create asymmetric heat release within the augmentor to avoid screech.

Abstract: A gas turbine engine fueling system includes a number of spray bars having conduits extending through associated vanes. A number of fuel injector nozzles are along each conduit. Each of the nozzles are positioned to discharge an associated fuel stream from one of the sides of the associated vane. A number of wear members are each mounted relative to the associated one of the nozzles for a range of motion relative thereto. The wear members movably cooperate with the associated vane to accommodate operating deflection and/or tolerances of the spray bars and vanes.

Abstract: A method facilitates assembling a gas turbine engine with a flameholder. The method comprises coupling at least one turning vane between a radially outer casing and a radially inner casing to form a flameholder, forming at least two slots that extend substantially radially through the outer and inner casings, coupling at least one fuel injector to the flameholder, and coupling the flameholder within the augmenter.

Abstract: A combustor for a gas turbine engine uses compressed air to cool a combustor liner and uses at least a portion of the same compressed air for combustion air. A flow diverting mechanism regulates compressed air flow entering a combustion air plenum feeding combustion air to a plurality of fuel nozzles. The flow diverting mechanism adjusts combustion air according to engine loading.