Abstract: A hydrogen/oxygen generation system includes an electrolyzer cell, a servo integrated controller, a power control module, a voltage/current feedback device and a temperature feedback device. Servo closed loop control is used to efficiently and effectively produce hydrogen and oxygen gases.

Abstract: The engine (10) includes at least one firing tube (12) wherein an exhaust stream (32) from the firing tube (12) drives a turbine (30). A scroll ejector attenuator (40) is secured between and in fluid communication with an outlet end (28) of the firing tube (12) and an inlet (76) of the turbine (30). The attenuator (40) defines a turning, narrowing passageway (72) that extends a distance the exhaust stream (32) travels before entering the turbine (30) to attenuate shockwaves and mix the pulsed exhaust stream (32) into an even stream with minimal temperature differences to thereby enhance efficient operation of the turbine (30) without any significant pressure decline of exhaust stream (32) pressure and without any backpressure from the attenuator (40) on the firing tube (12).

Abstract: A rotor blade for a turbine engine includes an airfoil section which extends from a platform section opposite a root section, the airfoil section defines a cavity which extends from an airfoil tip section toward a root section.

Abstract: A method for cooling components of a gas turbine engine, having first and second sets of components that require cooling, includes removing thermal energy from cooling air, directing the cooling air from which thermal energy has been removed to the first set of components of the gas turbine engine, and transferring thermal energy away from the second set of components of the gas turbine engine using a vaporization cycle of a vapor cooling assembly. Use of the vaporization cycle offsets thermal energy removed from the cooling air.

Abstract: A lens-based switched beam antenna system including a beam-forming lens, and a beam port router coupled to the beam-forming lens, including a plurality of beam ports, and configured to transmit beams via corresponding ones of the beam ports, wherein a first group of the beam ports corresponds to a first signal, and wherein a second group of the beam ports corresponds to a second signal.

Abstract: A cooling system for cooling a fluid reaction apparatus of a gas turbine engine includes a vapor cooling subsystem and a film cooling subsystem. The vapor cooling subsystem has a vaporization section and a condenser section for cooling a portion of the fluid reaction apparatus. The condenser section is cooled by a fluid. The film cooling subsystem is configured for cooling a portion of the fluid reaction apparatus by discharging fluid out of openings defined in the fluid reaction apparatus. At least a portion of the fluid used to cool the condenser section of the vapor cooling subsystem is discharged out of the openings of the film cooling subsystem.

Abstract: A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing.

Abstract: A rotor blade for a turbine engine includes an airfoil section which extends from a platform section opposite a root section, the airfoil section defines a cavity which extends from an airfoil tip section toward a root section.

Abstract: A method for cooling components of a gas turbine engine, having first and second sets of components that require cooling, includes removing thermal energy from cooling air, directing the cooling air from which thermal energy has been removed to the first set of components of the gas turbine engine, and transferring thermal energy away from the second set of components of the gas turbine engine using a vaporization cycle of a vapor cooling assembly. Use of the vaporization cycle offsets thermal energy removed from the cooling air.

Abstract: A hybrid cooling system for a gas turbine engine includes a vapor cooling assembly and a cooling air cooling assembly. The cooling air cooling assembly is configured to remove thermal energy from cooling air used to cool a first component of the gas turbine engine. The vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly. The vaporization section is located at least partially within a second component of the gas turbine engine, and the condenser section is located outside the second component.

Abstract: A hydrogen/oxygen generation system includes an electrolyzer cell, a servo integrated controller, a power control module, a voltage/current feedback device and a temperature feedback device. Servo closed loop control is used to efficiently and effectively produce hydrogen and oxygen gases.

Abstract: A cooling system for a gas turbine engine includes a non-rotating component extending into an engine flowpath, a vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly, wherein the vaporization section is located at least partially within the non-rotating component, and wherein the condenser section is located outside the non-rotating component and away from the engine flowpath.

Abstract: A cooling system for a gas turbine engine includes a non-rotating component extending into an engine flowpath, a vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly, wherein the vaporization section is located at least partially within the non-rotating component, and wherein the condenser section is located outside the non-rotating component and away from the engine flowpath.

Abstract: A portion of cooling air for cooling the turbine section of a gas turbine engine is tapped and passed through a heat exchanger. The portion of the cooling air is cooled in the heat exchanger, and the heat taken out of the portion of the cooling air is utilized to generate electricity.

Abstract: An apparatus for a gas turbine engine includes an airfoil defining a leading edge and a trailing edge, a root located adjacent to the airfoil, a vapor cooling system, and a film cooling system for cooling the airfoil in conjunction with the vapor cooling system. The vapor cooling system includes a vaporization section located within the airfoil and a condenser section located within the root.

Abstract: A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing.

Abstract: A hybrid cooling system for a gas turbine engine includes a vapor cooling assembly and a cooling air cooling assembly. The cooling air cooling assembly is configured to remove thermal energy from cooling air used to cool a first component of the gas turbine engine. The vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly. The vaporization section is located at least partially within a second component of the gas turbine engine, and the condenser section is located outside the second component.

Abstract: An apparatus for a gas turbine engine includes an airfoil defining a leading edge and a trailing edge, a root located adjacent to the airfoil, a vapor cooling system, and a film cooling system for cooling the airfoil in conjunction with the vapor cooling system. The vapor cooling system includes a vaporization section located within the airfoil and a condenser section located within the root.

Abstract: A support system includes a support post and support means for adjustably supporting a member to the support post. The support means includes a locking mechanism movable between a first position for press-fitting the support means, directly or indirectly, against the support post and a second position for releasing the press-fitting. The locking mechanism has a surface that abuts the support post, or a wedge member associated with the support post, when in the first position thereby to effect the press-fitting and that is released from the support post when moved to the second position to release the press-fitting.

Abstract: A support system includes a support post and support means for adjustably supporting a member to the support post. The support means includes a locking mechanism movable between a first position for press-fitting the support means, directly or indirectly, against the support post and a second position for releasing the press-fitting. The locking mechanism has a surface that abuts the support post, or a wedge member associated with the support post, when in the first position thereby to effect the press-fitting and that is released from the support post when moved to the second position to release the press-fitting.