Abstract: An underwater vehicle has a generally longitudinally extending housing terminating in at least one blunt end. Adjacent to and inboard of the blunt end of the longitudinally extended housing there is provided a compartment, and disposed in the compartment there is provided a folded, flexible bladder secured to a portion of the housing adjacent the blunt end and having a tapering configuration when pressurized or inflated. At or after launch of the underwater vehicle, or selectively at any other time in which it is desired to do so, an inboard mounted water pump which communicates with the interior of the bladder is operated to pressurize the bladder with regard to the surrounding ambient water, causing the tapered bladder to unfold and be extended outboard of the housing blunt end, thus streamlining the underwater vehicle.

Abstract: An improvement in a thermal barrier coating for superalloy turbine engine components subjected to high operating temperatures, such as turbine airfoils, e.g., vanes and blades, is disclosed which eliminates the expensive MCrAlY oxidation resistant bond coating underlayer for a columnar grained ceramic thermal barrier coating. In accordance with my present invention, a relatively low cost thermal barrier coating system for superalloy turbine components is provided which utilizes a diffusion aluminide coating layer as the oxidation resistant bonding surface for the columnar grained ceramic insulating coating.

Abstract: A thermal barrier coating for superalloy turbine engine vanes and blades that are exposed to high temperature gas is disclosed. The coating includes a ceramic layer applied to an Aluminide or MCrAlY bond coat by electron beam physical vapor deposition. The ceramic layer has a first portion having unstabilized porosity, a second portion, overlying the first portion, with stabilized porosity, and an outer portion wherein the pores are coated with a noble metal. The stabilized porosity portion along with the noble metal coating reduce the thermal conductivity of the ceramic layer. Stabilizing the porosity renders it more resistant to sintering densification at high temperatures.

Abstract: An aircraft subsystem provides the aircraft with all its electrical and conditioned air requirements without requiring the extraction of either shaft power and/or pressurized air from the aircraft's main engines. At the core of this subsystem are two rotating assemblies journaled on non-oil lubricated bearings to a housing. One assembly includes a cooling turbine, a starter/generator, a core compressor, and a high pressure stage of a two stage axial turbine, all mounted on a single shaft. A combustor is disposed between the core compressor and the turbine. The other assembly is comprised of the low pressure stage of the axial turbine coupled to a load compressor via a second shaft. The high pressure turbine stage and cooling turbine are sized to drive the core compressor and starter/generator which provides all the aircraft's electrical needs both on the ground and inflight.

Abstract: An oil scavenge assembly for small gas turbine engine. The assembly includes a rolling element bearing, for supporting a rotating shaft, slip fit within a bearing liner. The bearing liner has a plurality of helical grooves along its surface. A plurality of circumferentially spaced scoops extend inward from the liner and direct the oil expelled from the bearing into the helical grooves.

Abstract: A turboprop engine has in flow series arrangement a crescent shaped inlet, an annular plenum, a compressor, a combustor, and a turbine. The plenum is defined by inner and outer annular walls. A support member referred to as a "boat tail" extends between the walls and is circumferentially positioned 180 degrees from the inlet. A strake extends downstream from the support member and is angled in a direction opposite the rotational direction of the compressor. Thus air entering the engine with either positive or negative swirl is forced to enter the impeller with negative swirl.

Abstract: A launching device with a work-controlled gas generator employs a dampening piston in combination with an accumulator volume to provide substantially uniform acceleration of a launching piston.

Abstract: A gerotor pump having reduced drag torque at low temperatures is disclosed. The pump includes a shaft journalled in the housing. Mounted on the shaft are a pair of axially space metallic port plates and disposed therebetween are metallic interior and exterior gears. A ceramic eccentric ring circumscribes the exterior gear to define a diametral clearance.

Abstract: An exhaust housing having an eductor is provided. The eductor includes an outer annular casing circumscribing an inner annular casing to define a flow path therebetween for receiving the exhaust gas from the turbine section of an engine. A plurality of struts are integral with both casings. The struts have passages that extend from the exterior of the outer casing to the interior of the inner casing. A non-oil lubricated bearing is mounted within the interior of the inner casing for journaling a rotating shaft. During operation, the kinetic energy of the high velocity exhaust gas flowing between the casings and into a tailpipe induces cooling airflow from the exterior of the exhaust section, through the passages, across the bearing, and then out to the tailpipe.

Abstract: This invention relates to an alkaline scrubber for condensate stripper off-gases. In particular, this invention relates a process for selectively removing hydrogen sulfide and methyl mercaptan from a gas stream containing these compounds and methanol. Such gas streams are commonly generated during pulp and paper production.

Abstract: An environmental control system has an air cycle machine that includes a compressor, a cooling turbine, a motor/generator, and a power turbine all mounted on a single shaft. The power turbine receives bleed air from the aircraft's engine and has a variable geometry inlet nozzle that adjusts the air flow rate therethrough without significant throttling. Downstream of the nozzle the power turbine extracts the expansion energy from the bleed air while cooling it. This is used to drive the other components of the air cycle machine, and in particular the motor/generator which generates electricity.

Abstract: A method for preparing a machined surface of a composite article for diffusion bonding is provided. The method includes removing most of the exposed fibers by shot peening followed by acid etching. The acid etch may be followed by grit blasting and then another acid etch. After the method is applied to the surface, the article can be diffusion bonded to other composite article to form complex shapes.

Abstract: A stator vane assembly for a gas turbine engine that includes a plurality of circumferentially spaced ceramic vanes, each of which has an inner and outer ceramic shroud, and a ceramic post extending from one of the shrouds, and a metallic platform having a plurality of circumferentially spaced recesses. The posts are inserted into a metallic sleeve and then brazed. The brazed sleeves are then mounted in the recesses. A method for assembling these components to form the stator assembly is also described.

Abstract: A multifunction secondary power system (10) for use aboard an aircraft or other vehicle provides the functions both of an auxiliary power unit and of an emergency power unit. The power system (10) includes two turbine engines (12, 22) operable under differing conditions, a gearbox (34) receiving power from the two engines (12, 22) selectively through overrunning clutches (74,84), and a plurality of accessory devices (36, 38, 40) receiving shaft power from either of the two engines (12, 22) through the gearbox (34). The gear box (34) includes a third clutch (64) operably interposed between the clutches (74, 84) which selectively delivers shaft power from the engine (22) to the engine (12) to affect the start thereof.

Abstract: A metallic regenerator seal is provided having multi-layer coating comprising a NiCrAlY bond layer, a yttria stabilized zirconia (YSZ) intermediate layer, and a ceramic high temperature solid lubricant surface layer comprising zinc oxide, calcium fluoride, and tin oxide. Because of the YSZ intermediate layer, the coating is thermodynamically stable and resists swelling at high temperatures.

Abstract: A multifunction integrated power unit (MIPU) for use aboard aircraft provides the functions both of an auxiliary power unit and of an emergency power unit while being smaller, lighter, and less expensive than the two units it replaces. Additionally, the integration of both functions in a single unit allows elimination of duplicated service devices and a further reduction in size, cost, and weight in the aircraft itself. The MIPU includes two turbine engines operable under differing conditions, an integrating gear box receiving power from the two engines selectively, and a plurality of accessory devices receiving shaft power from either of the two engines via the gear box.

Abstract: A vibration cancellation system having a fluidic driver providing fluid pressure differential and flow to an actuator having a reaction mass. The pressure differential drives the reaction mass so that the actuator's oscillations cancel any vibrations emanating from a vibrating structure mounted thereto.

Abstract: A composite article is manufactured by preparing a machined surface of the composite article for diffusion bonding. The method includes removing most of the exposed fibers by shot peening followed by acid etching. The acid etch may be followed by grit blasting and then another acid etch. After the method is applied to the surface, the article can be diffusion bonded to other composite article to form complex shapes.

Abstract: A method and apparatus for eliminating vortex whistle noise in a radial-to-axial compressor intake uses a plurality of vortex-disturbing tabs mounted to the trailing edges of inlet guide vanes and extending into the flow path between adjacent vanes. The tabs are mounted to the guide vane so that the tab is always perpendicular to the guide vane, regardless of the vanes angular position.

Abstract: A metallic regenerator seal is provided having multi-layer coating comprising a NiCrAlY bond layer, a yttria stabilized zirconia (YSZ) intermediate layer, and a ceramic high temperature solid lubricant surface layer comprising zinc oxide, calcium fluoride, and tin oxide. An array of discontinuous grooves is laser machined into the outer surface of the solid lubricant surface layer making the coating strain tolerant.