Abstract: A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.

Abstract: A device capable of collecting a condensate from a working fluid is disclosed. The condensate can take the form of a liquid and can be injected into a flow path of an engine. In one form the engine is a gas turbine engine and the liquid is injected upstream of a combustor. The liquid can be produced using a component that cools the working fluid to condense a vapor within it. In one non-limiting form the component is part of a refrigeration system. In addition to producing condensate, the refrigeration system can cool the working fluid to be used as cooled cooling air to a turbine of a gas turbine engine. In another non-limiting embodiment a liquid derived from a blackwater containing waste from an organism can be delivered in whole or in part to a flow path of the engine.

Abstract: A gas turbine engine is disclosed having a particle separator and an ejector disposed downstream of the particle separator and structured to entrain a dirty flow from the separator. A container of working fluid can be placed in flow communication with the ejector to provide an ejector flow to entrain the dirty flow from the particle separator. Alternatively and/or additionally, the ejector can be configured to use a flow of working fluid from the gas turbine engine as an ejector flow.

Abstract: A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The transmission is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: An aircraft powerplant is disclosed that can be operated in at least three modes including as a gas turbine engine, as an engine having a ramburner, and as an engine having a forward compression combustor engine such as a ramjet and/or scramjet. An airflow valve is provided to direct air to a downstream portion of the aircraft engine and can be positioned as a function of the aircraft operating modes. The valve can be used to cocoon the gas turbine engine.

Abstract: A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

Abstract: A turbine vane cooling system operably coupling a cooling fluid source to a turbine vane assembly is disclosed herein. A plurality of turbine vanes having an airfoil shaped surface forming a substantially hollow body is connected to the turbine vane assembly. An inlet can be operably connected to each turbine vane to form a fluid communication path between a cooling fluid source and an interior of the hollow body of each turbine vane. At least one outlet fluidly communicating with the interior of said hollow body can be formed in the vane. A regulating member can variably block a portion of an inlet of each of the turbine vanes in response to a temperature of each turbine vane.

Abstract: An inductive battery charger is incorporated with a power source that in one embodiment is a genset. A charging surface can be provided that in some forms is hinged, separable, or includes a pocket. In some forms resonant inductive coupling can be used to charge a battery through inductive charging. A battery can be charged within an area such as a perimeter of a military post (e.g. an observation post) using techniques described herein. A battery can also be charged remotely by inductive techniques such as through the use of a passing vehicle, etc.

Abstract: A combined cycle engine is used to provide power to a vehicle. In one form the combined cycle engine includes two engines coupled through a gearbox. The engines can include a gas turbine engine, reciprocating engine, and a rotary engine. In one embodiment the combined cycle engine includes a gas turbine engine coupled to a gearbox along with either a reciprocating or rotary engine also coupled to the gearbox. One or more clutches can be provided to selectively couple the gas turbine engine and the reciprocating or rotary engine to the vehicle through the gearbox. In one embodiment the diesel engine can provide power to the vehicle during an idle condition and then also provide power to the gas turbine engine to assist the starting of the gas turbine engine.

Abstract: A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.

Abstract: A gas turbine engine is disclosed having a particle separator and an ejector disposed downstream of the particle separator and structured to entrain a dirty flow from the separator. A container of working fluid can be placed in flow communication with the ejector to provide an ejector flow to entrain the dirty flow from the particle separator. Alternatively and/or additionally, the ejector can be configured to use a flow of working fluid from the gas turbine engine as an ejector flow.

Abstract: A device provides a radiant electromagnetic energy output. During standby operation of the device, the output is provided at one or more frequencies selected to dissipate excess power through atmospheric absorption. Circuitry is included to tune the output of the device to a second frequency different than the first frequency for various directed energy applications that make use of the excess power. The circuitry can be arranged to further utilize frequency agility for power dissipation, to provide different operating modes involving a radiant output, or the like.

Abstract: A device capable of collecting a condensate from a working fluid is disclosed. The condensate can take the form of a liquid and can be injected into a flow path of an engine. In one form the engine is a gas turbine engine and the liquid is injected upstream of a combustor. The liquid can be produced using a component that cools the working fluid to condense a vapor within it. In one non-limiting form the component is part of a refrigeration system. In addition to producing condensate, the refrigeration system can cool the working fluid to be used as cooled cooling air to a turbine of a gas turbine engine. In another non-limiting embodiment a liquid derived from a blackwater containing waste from an organism can be delivered in whole or in part to a flow path of the engine.

Abstract: An aircraft powerplant is disclosed that can be operated in at least three modes including as a gas turbine engine, as an engine having a ramburner, and as an engine having a forward compression combustor engine such as a ramjet and/or scramjet. An airflow valve is provided to direct air to a downstream portion of the aircraft engine and can be positioned as a function of the aircraft operating modes. The valve can be used to cocoon the gas turbine engine.

Abstract: A device provides a radiant electromagnetic energy output. During standby operation of the device, the output is provided at one or more frequencies selected to dissipate excess power through atmospheric absorption. Circuitry is included to tune the output of the device to a second frequency different than the first frequency for various directed energy applications that make use of the excess power. The circuitry can be arranged to further utilize frequency agility for power dissipation, to provide different operating modes involving a radiant output, or the like.

Abstract: One embodiment of the present invention is a unique augmented gas turbine engine propulsion system. Another embodiment is a gas turbine engine power augmentation system. Yet another embodiment is a system for augmenting power in an engine powered air vehicle. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for fluid driven actuation systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.