Abstract: A gas sensor includes: a sensor element including a bottomed tubular solid electrolyte, a detection electrode, and a reference electrode; and a heater for heating the solid electrolyte. The reference electrode includes an inner detection section on an entire periphery in a circumferential direction at an endmost position on a tip side on the reference electrode, an inner connecting section on an entire periphery in the circumferential direction at an endmost position on a base end side on the reference electrode, and an inner lead section on a part in the circumferential direction at a position where the inner detection section is connected to the inner connecting section. A formation region in the circumferential direction of the inner lead section is reduced stepwise from the inner detection section toward the inner connecting section.

Abstract: According to the invention, a drive device for an aircraft is provided, which has a shaft turbine coupled to an impeller via a shaft. The impeller has an intake side and a thrust side. The shaft turbine is mounted in the area of the intake side of the impeller. The drive device is also designed for mounting externally on an aircraft fuselage and/or inside an aircraft fuselage and/or in a casing on a wing.

Abstract: A multiple fuel capable, pre-mixed, low emission injector is provided which is particularly suited for burning high flame speed fuels. The fuel injector includes an injector body having a preliminary pre-mixing chamber, an intermediate pre-mixing chamber and a final pre-mixing chamber. A fuel distributor separates the preliminary pre-mixing chamber from the intermediate pre-mixing chamber. A guide vane separates the intermediate pre-mixing chamber from the final pre-mixing chamber.

Abstract: A scroll compressor includes fixed and movable scrolls, a crank shaft and a housing. An outer peripheral portion of a top surface of the housing has an accommodation portion recessed and accommodating an Oldham coupling preventing rotations of the movable scroll around an axis. The housing has inner and outer seal ring grooves in a top surface. Inner and outer seal rings are fitted in the grooves. A portion of the top surface of the housing defined by the inner and outer seal ring grooves is higher than a surface that is closer to the inner periphery of the housing than the inner seal ring groove, and a surface that is closer to an outer periphery of the housing than the outer seal ring groove. The portion of the top surface serves as a tilt limiting surface.

Abstract: An engine control system performs a first control in the first place at the time of acceleration. Then, when an actual supercharging pressure is increased to a specified supercharging pressure, the engine control system performs a second control. In this way, at the time of acceleration, a turbine capacity and a valve overlap amount of an intake valve and an exhaust valve of an engine are optimized in correspondence to a driving state of an engine, whereby the intake valve and the exhaust valve of the engine can be made to overlap each other on the condition that a scavenging effect is larger than the effect of an exhaust interference during a valve overlap period.

Abstract: A hanger for a gas turbine exhaust system includes an exhaust duct attachment structure associated with an exhaust duct and a liner attachment structure associated with a liner spaced radially inwardly of the exhaust duct. The exhaust duct attachment structure and the liner attachment structure cooperate to suspend the liner within the exhaust duct such that the exhaust duct and liner are movable relative to each other. At least one resilient member generates a resilient biasing force between the exhaust duct attachment structure and the liner attachment structure.

Abstract: An electrospray thruster and methods of manufacturing such thrusters are provided. The micro-electrospray thruster increases the thrust density of conventional electrospray thrusters by miniaturizing the individual components of the thruster thereby allowing for the increase in the number and density of the charged particle emitters.

Abstract: A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. A set of aerodynamic vanes may be used to shape a supersonic airflow within a bypass around an engine. The vanes may be capable of directing the subsonic airflow around the engine, and then expanding the subsonic airflow into a supersonic exhaust. The vanes may shape the airflow by reducing sonic boom strength, cowl drag, and airframe interference drag.

Abstract: A liquefied natural gas (LNG) transport vessel for transporting liquefied natural gas (LNG) is disclosed which is capable of storing excess boil off gas BOG until needed for combustion in one or more combustion apparatus on the vessel. A method for managing the delivery of the BOG to the combustion apparatus is also described. The LNG vessel includes at least one insulated LNG storage tank which stores LNG. A first stage LNG receiver receives and stores BOG from the at least one LNG storage tank. A second stage or high pressure BOG storage tank receives compressed BOG from the receiver and stores the BOG as needed for combustion by one or more combustion apparatus of the vessel. A pressure regulator allows BOG gas to be delivered to the combustion apparatus if there is sufficient pressure in the high pressure storage tank to passively deliver the BOG at a predetermined delivery pressure.

Abstract: A method for determining the speed of at least one rotating fan, such as a propeller, through sensing pressure waves generated by the blades of the fan. An apparatus operable to execute the method is also disclosed. The apparatus includes a fan having a hub portion and a plurality of blades extending radially outward from the hub portion. The apparatus also includes an engine operable to rotate the fan about an axis of rotation. The apparatus also includes a sensor spaced from the fan along the axis of rotation. The sensor is positioned to sense at least one physical condition that is external of the engine and is changed by rotation of the plurality of blades. The sensor is operable to emit a signal corresponding to at least one physical condition. The apparatus also includes a processor operably engaged with the engine and the sensor. The processor is operable to receive the signal from the sensor and change the operation of the engine in response to the signal to change a speed of the fan.

Abstract: A new micro electro-mechanical system (MEMS) satellite thruster is described. An example of the new MEMS thruster includes a propellant layer on a flexible substrate to make a rolled propellant that can be mounted on a reel-to-reel system. Sections of the rolled propellant are rolled over a separate activation blast plate to initiate the propellant on that section, providing thrust. The new MEMS thruster can also be made with segmented propellant sections. The new MEMS thruster can be made in a variety of configurations and as a modular system that can be attached to existing satellites.

Abstract: Axially spaced apart counter-rotatable forward and aft rows of forward and aft propellers mounted on forward and aft rotatable frames includes a flowpath passing through the forward and aft rotatable frames. Hydraulic rotary forward and aft pitch change actuators mounted on the aft rotatable frames are connected to and operable for controlling and setting pitch of the aft propellers. The pitch change actuators are mounted radially inwardly of the flowpath in a one to one ratio with forward and aft rotatable struts extending radially across the flowpath. One or more rotatable shafts extend through one or more of the rotatable struts and connect one or more of the pitch change actuators to one or more of the propellers. The pitch change actuators may be ganged together by unison rings having ring teeth engaging gear teeth on gears connected to the pitch change actuators or connected to the rotatable shafts.