Abstract: Aspects of the disclosure are directed to a system of an aircraft, comprising: at least one fairing, a liner, and an actuator configured to cause the at least one fairing to be translated relative to the liner in order to obtain a modulation of a metering area between the liner and the at least one fairing,

Abstract: A nozzle system includes a static structure including a multiple of convergent flap rails and a synchronization ring including an inner ring radially spaced from an outer ring via a multiple of struts. The multiple of convergent flap rails extend at least partially between the inner ring and the outer ring.

Abstract: A liner for a gas turbine engine includes a liner defining an inner surface exposed to exhaust gases and a duct spaced radially outward of the liner. A plurality of hanger assemblies is disposed within the radial space between the liner and the duct for supporting the liner relative to the duct. Each of the hanger assemblies includes a cable having a first end attached to the duct and a second end attached to the liner.

Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

Abstract: A fuel delivery system is provided for a turbine engine. This fuel delivery system includes a variable orifice jet configured to spray fuel received from a spray bar fuel conduit. The variable orifice jet includes a flexible body and a pintle that extends through a sidewall of the flexible body. An area of an orifice between the sidewall and the pintle is variable.

Abstract: A hanger includes a connector assembly for coupling the hanger to a first annular duct, a bracket for coupling the hanger to a second annular duct concentrically disposed within the first annular duct, and a cable formed by a plurality of wires bound together that extend from the connector assembly to the bracket. A plurality of circumferentially-spaced hangers placed in tension support an exhaust duct liner relative to an exhaust duct. The hangers permit circumferential and axial displacement at each hanger of the exhaust duct liner relative to the exhaust duct. The displacement of the exhaust duct liner relative to the exhaust duct at each hanger is permitted in a first radial direction that decreases tension in the cable and is restrained in a second radial direction that increases tension in the cable.

Abstract: A hanger for suspending a liner within an exhaust duct of a gas turbine engine exhaust system comprises a connector assembly, a cable and a bracket. The connector assembly is for connecting to an exhaust duct of the gas turbine exhaust system. The cable extends from the connector assembly and is configured to extend into the exhaust duct. The bracket is for connecting to an exhaust duct liner of the gas turbine exhaust system. The bracket is connected to the cable.

Abstract: A thermally insulative component is a thermal barrier panel attached to a rigid structural member with means for attaching the insulative component to an external structure. The connection between the structural member and the thermal barrier panel is mechanically compliant to minimize intercomponent stress build up during operation. The thermal barrier panel is a fiber wrapped ceramic oxide foam insulating structure.

Abstract: A push-lock pin for connecting a plate to surface includes a cylindrical pin housing and a shaft within the housing. The shaft has a ball-lock mechanism and a push-down pop-up mechanism.

Abstract: A hanger for suspending a liner within an exhaust duct of a gas turbine engine exhaust system comprises a connector assembly, a cable and a bracket. The connector assembly is for connecting to an exhaust duct of the gas turbine exhaust system. The cable extends from the connector assembly and is configured to extend into the exhaust duct. The bracket is for connecting to an exhaust duct liner of the gas turbine exhaust system. The bracket is connected to the cable.

Abstract: A thermally insulative component is a thermal barrier panel attached to a rigid structural member with means for attaching the insulative component to an external structure. The connection between the structural member and the thermal barrier panel is mechanically compliant to minimize intercomponent stress build up during operation. The thermal barrier panel is a fiber wrapped ceramic oxide foam insulating structure.

Abstract: A liner for a gas turbine engine includes a liner defining an inner surface exposed to exhaust gases and a duct spaced radially outward of the liner. A plurality of hanger assemblies is disposed within the radial space between the liner and the duct for supporting the liner relative to the duct. Each of the hanger assemblies includes a cable having a first end attached to the duct and a second end attached to the liner.

Abstract: An aircraft engine nozzle assembly includes an adjustable flap portion that is movable about a pivot for changing the size of an exhaust exit area. A bracket having a curved slot establishes a range of possible movement of the flap portion. A link includes a guide member portion that is received in the curved slot for guiding the movement of the flap portion. The link is connected to a static engine structure and the bracket is movable with the flap portion. The curved slot establishes a range of possible movement of the flap portion along a direction of the curved slot.

Abstract: A nozzle system includes a multitude of circumferentially distributed divergent seals that circumscribe an engine centerline. Each divergent seal includes an interface between a forward seal bridge bracket and an aft seal bridge bracket with a forward bridge support and an aft bridge support which provides axial and radial support for the divergent seals between adjacent divergent flaps. A divergent-convergent seal joint structure includes a horn and a fork. By having the forward bridge bracket retain the divergent seal in the axial direction, there is no need for axial sliding of the divergent seal relative to the divergent flap. The joint structure provides circumferential support as the axial and radial support are provided by the bridge-bracket interface.

Abstract: A fastener assembly for attaching components of dissimilar materials includes a fastener having a base portion and a protruding portion, and a mechanism for tightening the assembly. The base portion is shaped to be complementary for mating with an attachment feature formed within the non-metal component such that the base portion is retained within the non-metal component. The protruding portion including a base end and a distal end with the distal end including a threaded portion. The fastener assembly allows attachment of components fabricated from dissimilar materials without forming through holes in one of the components. Additionally, the fastener assembly compensates for differences in thermal expansion rates between the non-metal component and the metal component while providing a tight attachment therebetween.

Abstract: A turbine engine nozzle assembly has an upstream flap and a downstream flap pivotally coupled thereto for relative rotation about a hinge axis. An actuator linkage is coupled to the flaps for actuating the nozzle between a number of throat area conditions. First and second mode struts respectively restrict rotation of the downstream flap in first and second directions.

Abstract: A fastener assembly for attaching components of dissimilar materials includes a fastener having a base portion and a protruding portion, and a mechanism for tightening the assembly. The base portion is shaped to be complementary for mating with an attachment feature formed within the non-metal component such that the base portion is retained within the non-metal component. The protruding portion including a base end and a distal end with the distal end including a threaded portion. The fastener assembly allows attachment of components fabricated from dissimilar materials without forming through holes in one of the components. Additionally, the fastener assembly compensates for differences in thermal expansion rates between the non-metal component and the metal component while providing a tight attachment therebetween.

Abstract: A convergent/divergent nozzle for a gas turbine engine has a throat portion of non-constant radius of curvature varying from an upstream high value to an intermediate low value and then to a downstream high value.

Abstract: A convergent/divergent nozzle for a gas turbine engine has a throat portion of non-constant radius of curvature varying from an upstream high value to an intermediate low value and then to a downstream high value.

Abstract: A stack sampler for collecting particulate samplings in gaseous emissions includes means for automatically matching the volume rate of flow through the sampler to the flow in the stack. Pressure drops and temperatures in the stack and in the sampler are continuously detected and applied to calculating circuitry which controls a valve in the sampler for maintaining isokinetic flow conditions. Filter means removably disposed in the sampler collects particulate material from the gaseous emission during the isokinetic flow which is obtained. Also, flow and flow rate are detected and displayed.