Abstract: The present application provides a flexible combustor fuel nozzle. The flexible combustor fuel nozzle may include a main passage in communication with a source of natural gas and a source of low BTU fuel, a secondary passage surrounding the main passage and in communication with the source of low BTU fuel and a source of purge air, and a tertiary passage surrounding the secondary passage and in communication with the source of low BTU fuel, the source of purge air, and a source of diluent.

Abstract: An example core nacelle for a gas turbine engine includes a core cowl positioned adjacent an inner duct boundary of a fan bypass passage having an associated discharge airflow cross-sectional area. The core cowl includes at least one translating section and at least one flap section. The translating section of the core cowl is selectively moveable to vary the discharge airflow cross-sectional area.

Abstract: A bellows includes a flexible section including a series of convolutions extending between a first end and a second end. The convolutions are formed of a nano-grained aluminum alloy.

Abstract: The invention is a Hall thruster that incorporates a discharge chamber having a variable area channel including an ionization zone, a transition region, and an acceleration zone. The variable area channel is wider through the acceleration zone than through the ionization zone. An anode is located in a vicinity of the ionization zone and a cathode is located in a vicinity of the acceleration zone. The Hall thruster includes a magnetic circuit which is capable of forming a local magnetic field having a curvature within the transition region of the variable area channel whereby the transition region conforms to the curvature of the local magnetic field. The Hall thruster optimizes the ionization and acceleration efficiencies by the combined effects of the variable area channel and magnetic conformity.

Abstract: A lower cost combustor is formed from a series of sheets of metal that are secured by mechanical fasteners. An increase in diameter of the combustor is achieved through the provision of securing rings to which the sheets of metal are secured.

Abstract: An aircraft gas turbine engine includes a counter-rotatable generator driven by a turbine includes a generator stator and counter-rotatable radially inner pole and outer magnet rotors. A gearbox may be used for counter-rotating the pole and magnet rotors. Counter-rotatable first and second sets of booster stages may be co-rotatable with corresponding ones of the pole and magnet rotors. The generator and the gearbox may be disposed within a booster cavity or a tail cone of the engine. The magnet rotor, the pole rotor, and the stator may be concentric. A particular embodiment of generator includes the magnet rotor encircling the pole rotor, the pole rotor encircling the stator, a rotor air gap between the magnet and pole rotors, and a transformer air gap between the pole rotor and the stator. The counter-rotatable generator may be driven directly by a counter-rotatable turbine.

Abstract: A collapsible flow control structure for an axisymmetric inlet employs trapezoidal alternating actuated and non-actuated strips having leading edges hinged to a missile forebody and free trailing edges extending into an inlet aperture, the strips positionable to form a variable angle frustum of a cone. An interengagement mechanism secures adjacent strips and actuators are attached to an inner surface of the actuated strips for urging the strips between a collapsed, retracted position for a first angle frustrum to an extended position for a second angle frustrum for aerodynamic flow control.

Abstract: A turbofan engine includes a fan variable area nozzle, which includes a louver system having a multiple of slats generally transverse to the engine axis. Each of the louver slats are pivotally mounted to the fan nacelle to vary the effective area of the fan nozzle exit area and permit efficient engine operation at predefined pressure ratios.

Abstract: A tip turbine engine assembly includes an engine support structure with a rear case, exit guide vanes, an exhaust mixer, and engine mounts. The rear case is disposed about an engine centerline. The exit guide vanes extend radially inwardly from the rear case. The exhaust mixer extends in a flow path of a combustor to mix a high energy gas stream from the combustor with bypass air from a bypass fan. The engine mounts are located on the periphery of the rear case for mounting the engine to an aircraft. The rear case, exit guide vanes, exhaust mixer, and engine mounts form a unitary engine support structure which is installable as a single piece into an engine.

Abstract: A turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.

Abstract: An engine accessory system for a gas turbine engine includes a first accessory component mountable to an accessory gearbox along a first accessory axis transverse to a layshaft axis of rotation.

Abstract: A downhole tool pumping apparatus comprising a body and an active valve block. The body comprises a cavity housing a reciprocating piston defining first and second chambers within the cavity. The active valve block comprises a plurality of active valves, wherein the plurality of active valves includes a first active valve fluidly connected to the first chamber of the body, the plurality of active valves includes a second active valve fluidly connected to the second chamber of the body, and each of the plurality of active valves is configured to be actively actuated between open and closed positions.

Abstract: An InfraRed Suppression System (IRSS) includes a double-walled exhaust duct and double walled septum. The double walled structure provides a flow path for secondary (non-exhaust gas) cooling air flow to slots along the surfaces exposed to exhaust gases. Exhaust gas flow past these slots draws cooling air across the duct and septum surfaces. This flow cools the surfaces close to the slots and mixes with exhaust gasses downstream to cool the exhaust plume. The septum in the shape of a helix rotating 360° fully blocks line-of-sight to the turbine exit from the aft of the aircraft. The exhaust duct is intended to be shrouded by an aerodynamic fairing which provides an aerodynamic contour which minimizes aerodynamic impact on the aircraft.

Abstract: A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

Abstract: An electricity generation system is presented. The electricity generation system includes a solar preheater for preheating compressed discharge air, a combustor to receive the heated compressed air from the solar preheater, burn a fuel using the heated compressed air to generate hot burned gas, a first turbine to receive the hot burned gas from the combustor, expand the hot burned gas to generate exhaust gas, a heat recovery steam generator to receive the exhaust gas from the first turbine, generate vapor by heating a condensed fluid using the exhaust gas, a solar evaporator/superheater to receive a heated working fluid from the heat recovery steam generator, generate solar vapor by heating the heated working fluid, and a second turbine to drive a second generator using vapor and the solar vapor.

Abstract: A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

Abstract: Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.

Abstract: In a method of operating a gas turbine during shut down, the gas turbine is decelerated and closure of compressor inlet guide vanes (1) is initiated at a shaft speed at least 5% above the shaft speed where a vibration peak occurs. The compressor inlet guide vanes (1) are closed by an angle in the range from 15°-35°, preferably at a rate between 5° and 10° per second. The method effects a reduction of the risk of rotational stall.

Abstract: The present invention relates to novel oblong, preferably bilobular, sump containers or reservoir housings for containing sump pump stands and two or more sump pumps, which containers are more narrow, side-to-side, than conventional circular, frustroconical larger volume sump containers, and only slightly longer or wider lengthwise than such conventional standard-size containers, to provide a substantially larger interior integrated oblong cross-sectional floor area for the containment of two or more sump pumps without interference with each other. The present housings preferably have a top oblong reinforcing rim and a reinforcing bridge connecting the reinforcing rim across the width of said container. The present sump pump reservoir housings also have a two-piece oblong or bilobular cross-section cover which is attachable to the reinforcing rim to enclose the housing and which includes ports for the extension of pump discharge conduits from pumps within the housing through the cover to a discharge area.

Abstract: A controller for a system having at least one variable-capacity, pulse-width modulated compressor and at least one fixed-capacity compressor is provided. The controller may include processing circuitry that modulates the at least one variable-capacity, pulse-width modulated compressor to any capacity substantially between ten percent capacity and one hundred percent capacity. The processing circuitry may determine a desired capacity of the at least one variable capacity, pulse-width modulated compressor based on a load sensor signal and a current run percentage of the at least one variable capacity, pulse-width modulated compressor and may toggle the at least one fixed-capacity compressor between a run mode and a shutdown mode based on the desired capacity of the at least one variable-capacity, pulse-width modulated compressor.