Abstract: A method for managing the energy produced by a gas turbine engine, which includes utilizing an endothermic fuel to cool the combustion products in the exhaust section of the gas turbine engine prior to burning the fuel in the combustion section of the engine.

Abstract: A method of producing a rocket thrust chamber includes positioning cooling tubes within a structural jacket to form a tube bundle, and positioning a mandrel within the tube bundle thereby sandwiching the tubes between the jacket and the mandrel. The tubes are then inflated at high temperature into intimate contact with adjacent tubes and the jacket, and the temperature is maintained until bonding has occurred between the tubes and jacket.

Abstract: A method of producing a rocket thrust chamber includes positioning sleeved cooling tubes within a structural jacket to form a tube bundle, and positioning a liner within the tube bundle thereby sandwiching the tubes between the jacket and the liner. The tubes are then subjected to high internal pressure and inflated at high temperature while the liner is simultaneously subjected to the same high pressure, thereby forcing the sleeved tubes into intimate contact with adjacent sleeved tubes, the liner and the jacket, and the temperature is maintained until bonding has occurred between the liner, sleeved tubes and jacket.

Abstract: A method of producing a tubular structure, such as a rocket thrust chamber, includes positioning cooling tubes about an inner tooling fixture to form a tube bundle, and positioning a segmented outer tooling fixture about the tube bundle thereby sandwiching the tubes between the inner tooling fixture and the outer tooling fixture. The tubes are then pressurized at high temperature and the inner tooling fixture, outer tooling fixture and tube bundle are heated to a temperature at which each of the tubes bonds to adjacent tubes.

Abstract: A seal centering and restraining device for positioning the seals between the divergent flaps of a vectoring convergent/divergent nozzle. The device includes a restraint bar that spans between two adjacent divergent flaps and is pivotally attached to the air side of a seal and slidably secured by sliders to tracks on the adjacent divergent flaps, thereby sandwiching the adjacent divergent flaps between the seal and sliders. A positioning linkage connecting the two adjacent divergent flaps centers the seal at all nozzle operating conditions.

Abstract: This invention relates to a clip for securing a segmented panel, such as that of a combustor liner for a gas turbine engine, to the outer shell of the combustor, a clip characterized by having two distinctly different spring rates depending on the magnitude of the load which the clip must support.

Abstract: A gas turbine engine liner assembly is disclosed having uniformly spaced rows of cooling orifices oriented perpendicular to the combustion gas flow of the engine. The orifices within each row are spaced equidistant from adjacent orifices within the same row, thereby providing a uniform, uninterrupted pattern of cooling orifices over the hot side of the liner. The liner is secured to a component of the gas turbine engine by a plurality of fasteners which are secured to the liner without affecting the uniform pattern of the cooling orifices.

Abstract: A divergent flap assembly having a divergent flap connected to a sync-ring by first and second divergent struts that cross adjacent the center portions thereof providing a linkage arrangement that produces a uniform vectoring of all of the divergent flaps for a given angle of rotation of the sync-ring about the center thereof.

Abstract: The present invention is a brush seal for use between two components which move relative to each other. The brush seal has multiple layers of bristles, and the bristles within a particular layer have the same cross-sectional area or "thickness". The layers are arranged in the order of increasing thickness, with the bristles of the layer that forms the high pressure face of the brush seal having the smallest cross-sectional area. The larger bristles support the smaller bristles, and a backing plate supports the larger bristles.

Abstract: A combustor element face plate made of a thermally highly conductive material, such as copper, has a plurality of cooling holes extending therethrough. Some of the cooling holes are located about the injector openings, while other cooling holes are located adjacent the peripheral edge of the face plate.

Abstract: The space between a pinion and starter case in an electric starter is sealed by a flexible disk. This disk rotates on the pinion. The pinion contains a circular slot for the disk, which has a central cut-out portion in the profile of the pinion teeth, which hold the disk in place in the slot once the disk is installed. The disk is installed by lightly forcing it over the teeth on the pinion. This seal blocks path for particulate and contaminants into the interior of the starter through the space between the pinion and the starter case.

Abstract: Disclosed is a hinged fluid passage assembly having seal members which allow fluid to flow from a first component to a second component hinged thereto through a passage between seal members extending from the components and the hinge.

Abstract: A modular headliner includes an assist strap for mounting to the modular headliner to the vehicle body structure and includes an assist strap fastening means. The fastening means extends to engage a vehicle body adjacent an opening defined by a vehicle body structure. A mandrel may then be inserted between the fastening means to lock the fastening means to the vehicle body structure to thereby mount the assist strap and headliner to vehicle body structure.The assist strap may include a pivotally mounted handle having a preassembly position such that upon displacement of the handle, the mandrel is displaced to the locking position. Additionally a breakaway tab means may secure the handle to the assist strap base such that until sufficient force is applied to the handle to rupture the breakaway tab the handle will not be displaced. The tab is tuned to require that a sufficient force be sufficient to drive the mandrel to the locking position.

Abstract: Disclosed is a gas turbine engine which incorporates a vertical thrust nozzle which diverts working fluid from the engine to selectively provide vertical thrust or a combination of vertical and forward thrust.

Abstract: Disclosed is a two-dimensional nozzle for a gas turbine engine which, through the use of divergent flaps mounted on pivot shafts eccentric to the side disks in which they are received, provides thrust vectoring and low observability flight operation.

Abstract: Disclosed is an apparatus and a method for cooling a rotatable convergent side disk in a two-dimensional nozzle for a gas turbine engine, in which coolant is supplied and exhausted through concentric conduits, the cooling requirements of a liner assembly are reduced by use of a thermal barrier coating, and exhaust gas from the nozzle is prevented from aspirating into the side disk by use of a liner which is impervious to the exhaust gas.

Abstract: Disclosed is a device for cooling the trailing edge segment of a liner on a convergent flap of a nozzle on a gas turbine engine. The trailing edge cooling device enhances the cooling of the liner without introducing turbulence into the coolant, thereby allowing the coolant to be used to film cool downstream components. In addition, the present invention increases the longitudinal rigidity of the trailing edge of the liner to provide support for the trailing edge without significantly reducing the lateral flexibility of the liner required for thermal expansion.

Abstract: Disclosed is a continuous fluid pressure seal for use between two members that move relative to each other, that can withstand high temperatures, and that is separately loaded so as not to rely solely on a pressure differential across the seal for correct seating and orientation. The present invention further provides a seal which is effective between to movable members despite the presence of an obstruction therebetween.

Abstract: The invention discloses a liner hanger assembly which is mechanically attached to the component to which the liner is secured, thereby allowing hanger materials to be selected based on other than weldability considerations, and allowing the hanger to be removed and repaired when worn or damaged.

Abstract: The tapered core/shell lock includes notches which, in conjunction with protrusions from the shell mold, prevent axial slip of the core main body. In addition, the core/shell lock provides a tapered core print area which is much larger, and extends further into the shell mold, then the conventional "T" bar core/shell lock. By increasing the axial length of the core print area, shifting at the tip of the core main body is reduced, while tapering of the core print eliminates the need to lacquer slip the end of the core/shell lock, eliminating addtional sources of core shift.