Abstract: A method of lowering fuel consumption and NOx levels in a two-stroke diesel engine having at least one piston disposed in at least one combustion chamber comprises the steps of providing a compression ratio within the combustion chamber between about 16.5:1 to about 19:1, providing a ratio of peak pressure to compressed pressure within the combustion chamber below about 1.4; and providing a trapped air charge density within the combustion chamber of at least 2.77 kg/m3. Combustion within the diesel engine results in NOx levels in exhaust gases below a predetermined amount and fuel consumption below a predetermined amount.

Abstract: A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.

Abstract: A high-density cable of a type suitable for transmitting ultrasound signals from an ultrasonic probe to multiplexing circuitry during a medical ultrasound procedure is provided. The cable includes one or more flexible circuits arranged within a flexible sheath that surrounds and confines the flexible circuits. Each flexible circuit includes an elongate flexible substrate with oppositely-disposed surfaces and multiple conductors on at least one of these surfaces. The opposing longitudinal ends of the substrate define integral connectors for connecting with respective output connectors and/or electronic devices, such as an ultrasonic probe or multiplexing circuitry.

Abstract: A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.

Abstract: A combustor for a gas turbine includes a dome assembly that facilitates extending a useful life of the combustor in a cost-effective and reliable manner. The dome assembly includes a dome plate and a heat shield coupled to the dome plate. The dome plate includes an impingement baffle and an opening extending therethrough and sized to receive a fuel injector. The impingement baffle also includes a plurality of cooling openings in flow communication with the heat shield that direct cooling airflow for impingement cooling and film cooling of the heat shield.

Abstract: A bearing assembly for a gas turbine engine rotor includes a damper bearing configured to support the rotor, a bearing centering sub-assembly configured to position the damper bearing relative to the rotor, and a retainer. The damper bearing includes a frame that defines a bearing bore, an inner race, and an outer race, said inner and outer races within said bearing bore. The bearing centering apparatus sub-assembly includes a plurality of first springs and a plurality of second springs. The retainer is coupled to the bearing housing and is configured to maintain an axial position of the bearing outer race with respect to the support structure.

Abstract: An engine tracking filter system that obtains information from two or more operating conditions to estimate health parameters P, performance parameters Yp, and sensor estimates Ys, is described. Such multipoint estimation of engine health enables estimation of all engine health parameters rather than only a few engine health parameters for use in engine component diagnostics, trending, and fault detection and isolation. In addition, such estimation is believed to provide improved estimates of sensed parameters for use in sensor redundancy management and sensor elimination, and also is believed to provide improved estimates of performance parameters for use in model based control to reduce required temperature, stall, and other margins.

Abstract: A gas turbine engine includes a compressor rotor assembly including a first rotor, a combustor configured to operate with a fuel/air mixture equivalence ratio less than one, and a water injection assembly. The water injection assembly includes a water delivery system including a first plurality of spray nozzles to supply water upstream from the first rotor. The water being supplied to the first rotor is atomized with the first plurality of spray nozzles prior to being supplied to the engine to lower the emissions generated by the combustor.

Abstract: A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for impingement cooling a portion of the flare cone portion to facilitate reducing an operating temperature and extending a useful life of the combustor.

Abstract: A flow meter including at least one flow valve used to performance test system compressors is described. The flow meter includes a pressure vessel including at least one exit port. A flow valve is coupled to each vessel exit port, and each flow valve discharges fluid from the vessel at a pre-determined flow rate. The flow valve includes a first end, a second end, and a bore extending therethrough. The bore includes an entrance portion and an exit portion. The bore entrance portion is frusto-conical and curves outwardly from the bore exit portion such that a diameter of the bore entrance portion is variable and larger than a diameter of the bore exit portion.

Abstract: An information tag is secured to an article worn or carried by a user and provides identification information about the user in a cost-effective and reliable manner. The tag includes a plurality of layers including a body and a protective layer. The body has a top surface and an opposing bottom surface. The protective layer includes a domed upper surface and a substantially planar lower surface that is attached to at least a portion of the body top surface. At least one opening extends through at least one of the body and the domed protective cover. The tag body bottom surface provides identification information about the user.

Abstract: A rotor assembly for a gas turbine engine including a bearing centering sub-assembly that facilitates reduces an effect of radial forces transmitted to a bearing assembly is described. The bearing assembly supports a rotor shaft with a rolling element positioned radially inward from an outer race. The bearing centering sub-assembly is coupled to the outer race and includes a plurality of first springs and a plurality of second springs extending circumferentially in rows. Each first springs is coupled between a second spring and the outer race such that each first spring is radially aligned with respect to each second spring.

Abstract: An apparatus removes a tamper-proof seal from a mouth of a container and retains the tamper-proof seal to prevent any of the seal from falling into the container. The apparatus includes a body having a top surface and a bottom surface. A sidewall circumscribes the body and extends substantially perpendicularly from the top surface of the body. A first projection extends substantially perpendicularly from the top surface and is disposed radially inward from the side wall. A plurality of second projections extend from the top surface of the body and are disposed circumferentially around body top surface.