Abstract: A combustor liner assembly support is provided that is used to axially and radially position combustor liners in a gas turbine engine. The combustor liner support includes, in one embodiment, a support bracket that is coupled to a diffuser located upstream in the gas turbine engine; a support spool coupled to the support bracket; and a mount stake coupled to the support spool. The mount stake is connected to the combustor liners and maintains the spaced relation therebetween. An alignment device can be used between the support bracket and the support spool.

Abstract: A system includes a nut plate and a polymer sleeve passing through the nut plate. The polymer sleeve contains adhesive for attachment of the nut plate to a substrate. The interior of the sleeve includes an epoxy and a catalyzing agent initially separated from one another, but mixed by kneading the sleeve. A portion of the sleeve can be used to apply the adhesive to a bottom surface of the nut plate.

Abstract: A fuel nozzle for a gas turbine engine is provided having swirlers and a mounting device configured to mount the fuel nozzle to the inside of a combustor. In one embodiment the combustor has an interior surface formed to receive the mounting device of the fuel nozzle from within the combustor. The swirlers can be integrally formed in the fuel nozzle or can be separately attached, thus allowing the fuel nozzle to be mounted within the combustor having the relative placement of the swirlers already determined prior to installation. The fuel nozzle tip can be positioned a predetermined distance from the outlet of a swirler to reduce NOx emissions.

Abstract: A splitter is disclosed that can be coupled with a splitter support and used within a diffuser of a gas turbine engine. The splitter includes apertures for receiving a portion of the splitter support. The splitter support includes support arms that are adapted to be slidingly received within the apertures of the splitter.

Abstract: A morphable composite structure is disclosed herein. The morphable composite structure includes at least first and second layers fixed relative to one another. Each of the first and second layers includes a plurality of structural fibers oriented substantially parallel to one another and a quantity of binder substantially fixing the plurality of structural fibers together. The plurality of fibers of the first layer is oriented asymmetrically to the plurality of fibers of the second layer. The morphable composite structure also includes at least one pattern of electrically-conductive particles connected with the first layer and spaced from the second layer. A current can be directed through the pattern to heat the plurality of fibers of the first layer and change the shape of the morphable composite structure.

Abstract: A tape that can be used to detect cracks in a structure to which it is attached is disclosed herein. The tape includes a plurality of structural fibers. The tape also includes an electrically-insulating binder at least partially encapsulating the plurality of structural fibers. The tape also includes quantities of electrically conductive particles, each quantity of electrically conductive particles connected with one of the plurality of structural fibers.

Abstract: A patch for repairing damaged structures is disclosed herein. The patch includes a plurality of structural fibers. The patch also includes a quantity of binder at least partially encapsulating the plurality of structural fibers. The patch also includes a plurality of carbon nanotubes substantially encapsulated in the binder with the plurality of structural fibers. An inventive and exemplary method for using the patch is also disclosed.

Abstract: The present disclosure provides a multiple use threaded fastener having a plurality of redundant locking features. The fastener includes a threaded hollow lock bolt having a tapered internal wall constructed to threadingly engage a threaded aperture in a housing. A threaded lock stud having a tapered external wall is constructed to fit at least partially within the hollow lock bolt and threadingly engage the threaded aperture of the housing and engage the tapered wall of the hollow lock bolt.

Abstract: A gas turbine engine and method of fabrication includes a gas turbine engine with a structure having movable portions and static portions. At least a portion of the structure includes a composite material having an electrically conductive path formed from carbon nanotubes configured for conducting electrical signals therealong.

Abstract: A seal system having a rotating seal section and a static seal section operable for working together to restrict fluid flow there between. An arm connected to the static seal is tuned to move the static seal asymmetrically to correspond with asymmetric movement of the rotating seal during operation to maintain a desired relative position between the static and rotating seals.

Abstract: A fuel spraybar assembly for spraying fuel within a gas turbine engine. The spraybar assembly includes radial and lateral members that distribute fuel within the flowpath. In one embodiment two lateral members are located at the radially inward end of a radial member and generally form a “T” shape. Circumferentially spaced adjacent spraybars subdivide the flowpath into a plurality of circumferential combustion zone segments. In one embodiment the junction of the radial and lateral members provides a flameholding feature that stabilizes the combustion flame. In another embodiment, fuel is introduced non-uniformly within the afterburner resulting in thermal vectoring of the engine thrust.

Abstract: A fuel spraybar assembly for spraying fuel within a gas turbine engine. The spraybar assembly includes radial and lateral members that distribute fuel within the flowpath. In one embodiment two lateral members are located at the radially inward end of a radial member and generally form a “T” shape. Circumferentially spaced adjacent spraybars subdivide the flowpath into a plurality of circumferential combustion zone segments. In one embodiment the junction of the radial and lateral members provides a flameholding feature that stabilizes the combustion flame. In another embodiment, fuel is introduced non-uniformly within the afterburner resulting in thermal vectoring of the engine thrust.

Abstract: An interchangeable combustor chute for directing airflow into a gas turbine engine combustor. In one aspect the combustor chute is secured to the combustor liner by mechanical fastener. The combustor chute is formed of a high temperature resistant material such as ceramics.

Abstract: The present invention contemplates an apparatus for supporting an annular combustor liner in a gas turbine engine. In one embodiment, the apparatus includes a plurality of radial lugs extending outwardly from an outer surface of the combustor liner and being spaced circumferentially and uniformly about a periphery of the combustor liner. A band is disposed about the outer surface of the combustor liner and coupled to the radial lugs. The radial lugs each include a radially extending slot having opposing circumferentially facing radial surfaces. The band includes a plurality of pins, each pin being disposed within a respective one of the slots. The pin is configured to bear against at least one of the radial surfaces to provide circumferential support to the combustor liner by substantially preventing relative circumferential movement between the combustor liner and the band. The pin is slidable between the radial surfaces to allow relative radial movement between the combustor liner and the band.

Abstract: A gas turbine engine variable vane having a winglet integrally formed therewith. In one embodiment, the variable vane includes a winglet attached to one end so as to reduce endwall losses resulting from air leakage from the high-pressure side to the low-pressure side of the airfoil. The winglet substantially increases the width of the endwall gap thereby reducing the loss associated with the vortex flow caused by leakage of gas from the pressure side to the section side of the airfoil. In another aspect the winglet runs along the airfoil thereby increasing stiffness and acting as a bracing strut to increase the resonant frequency of the airfoil.

Abstract: A retainer for a rotor disk assembly of a gas turbine engine forms one aspect of the present invention. The retainer prevents axial displacement of a plurality of blades coupled to the rotor disk. The retainer includes a plurality of retaining segments and a locking segment. The locking segment is positioned between two of the retaining segments to define a first joint and a second joint. The first and second joints are offset a distance from and are substantially parallel to an axis extending through the center of the rotor disk assembly. The retainer may also be provided with means for preventing displacement of the retainer towards the center of the rotor disk assembly.

Abstract: A fuel spraybar assembly for spraying fuel within a gas turbine engine. The spraybar assembly includes radial and lateral members that distribute fuel within the flowpath. In one embodiment two lateral members are located at the radially inward end of a radial member and generally form a "T" shape. Circumferentially spaced adjacent spraybars subdivide the flowpath into a plurality of circumferential combustion zone segments. In one embodiment the junction of the radial and lateral members provides a flameholding feature that stabilizes the combustion flame. In another embodiment, fuel is introduced non-uniformly within the afterburner resulting in thermal vectoring of the engine thrust.