Abstract: A gas turbine engine augmentor has a centerbody within a gas flowpath from upstream to downstream. The augmentor has upstream and downstream shell sections, a downstream rim of the upstream shell section meeting an upstream rim of the downstream shell section shell section. A plurality of vanes are positioned in the gas flowpath outboard of the centerbody. An augmentor spray bar fuel conduit extends through the centerbody and a first of the vanes to deliver fuel to the centerbody. A seal is mounted to the spray bar and positioned in a recess extending from at least one of the downstream rim of the upstream shell section and upstream rim of the downstream shell section shell section. The seal has a first portion and a second portion engaging the first portion in a backlocked interfitting.

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 gas turbine engine augmentor has a centerbody within a gas flowpath from upstream to downstream. The augmentor has upstream and downstream shell sections, a downstream rim of the upstream shell section meeting an upstream rim of the downstream shell section shell section. A plurality of vanes are positioned in the gas flowpath outboard of the centerbody. An augmentor spray bar fuel conduit extends through the centerbody and a first of the vanes to deliver fuel to the centerbody. A seal is mounted to the spray bar and positioned in a recess extending from at least one of the downstream rim of the upstream shell section and upstream rim of the downstream shell section shell section. The seal has a first portion and a second portion engaging the first portion in a backlocked interfitting.

Abstract: A gas turbine engine augmentor has a centerbody within a gas flowpath from upstream to downstream. The augmentor has upstream and downstream shell sections, a downstream rim of the upstream shell section meeting an upstream rim of the downstream shell section shell section. A plurality of vanes are positioned in the gas flowpath outboard of the centerbody. An augmentor spray bar fuel conduit extends through the centerbody and a first of the vanes to deliver fuel to the centerbody. A seal is mounted to the spray bar and positioned in a recess extending from at least one of the downstream rim of the upstream shell section and upstream rim of the downstream shell section shell section. The seal has a first portion and a second portion engaging the first portion in a backlocked interfitting.

Abstract: A gas turbine engine augmentor has a centerbody within a gas flowpath from upstream to downstream. A plurality of vanes are positioned in the gas flowpath outboard of the centerbody. An augmenter fuel conduit extends through a first of the vanes to deliver fuel to the centerbody. An electrographitic carbon bushing guides and supports the augmentor fuel conduit.