Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Abstract: A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream edge in an upstream direction.

Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Abstract: A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream edge in an upstream direction.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S–16S, 1R–17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: A tunnel thruster which is compact, quiet and can withstand the higher depth pressure encountered by a UUV. The UUV is usually a cylindrically shaped vessel and has a propulsor with control surfaces at one end. At two positions along the length of the body there are two cylindrical ports which pass through the body of the UUV. At each position one port is in the vertical plane while the other port is in the horizontal plane. These ports are four tunnel thrusters, which enable the maneuvering of the UUV. The tunnel thruster can be mounted in the ports of the UUV. The main components of the tunnel thruster includes a tunnel, motor assembly mounted in the tunnel, rotors on each end of the motor assembly and inlet ducts on each end of the tunnel. The tunnel thruster attempts to address the short comings of the commercial thrusters. The tunnel thruster is an all electrically powered thruster with all mechanical components contained within the tunnel. The rotors operate independently and are counter-rotating.

Abstract: A control method for controlling a controllable pitch propeller during gear shifting operations monitors the gear selector switch to determine a future or impending gear shifting operation, determines the current pitch setting of a controllable pitch propeller, saves the current pitch setting, moves the blades of the controllable pitch propeller to a minimal or zero pitch setting, implements the gear change operation, and then returns the blades of the controllable pitch propeller to the original setting or the current setting by minimizing the pitch of the blades of the controllable pitch propeller prior to the shifting operation, the impact shock load on the marine propulsion system can be decreased by minimizing the resistance to propeller hub rotation caused by the blades moving through the water.

Abstract: A control algorithm provides a method for selecting a pitch magnitude for a controllable pitch propeller. The pitch magnitude is selected as a function of the difference between a desired engine speed and an actual engine speed in addition to the actual pitch position of the controllable pitch propeller. The desired engine speed is selected as a function of the position of either a throttle control lever or the throttle plate of an internal combustion engine.

Abstract: A controllable pitch propeller is provided with a blade that naturally tends to rotate in a direction toward maximum pitch as a result of the hydrodynamic forces on the blade. As a result, the blade will move toward a pitch position of increased pitch magnitude in the event that a control system failure occurs. If the blades of a propeller move naturally toward their maximum pitch position in the event of a hydraulic, mechanical, or electrical failure in the pitch control system, the propeller will be operable and will allow a marine vessel operator to navigate toward port even with a propeller pitch control system that has malfunctioned.

Abstract: A tunnel thruster which is compact, quiet and can withstand the higher depth pressure encountered by a UUV. The UUV is usually a cylindrically shaped vessel and has a propulsor with control surfaces at one end. At two positions along the length of the body there are two cylindrical ports which pass through the body of the UUV. At each position one port is in the vertical plane while the other port is in the horizontal plane. These ports are four tunnel thrusters, which enable the maneuvering of the UUV. The tunnel thruster can be mounted in the ports of the UUV. The main components of the tunnel thruster includes a tunnel, motor assembly mounted in the tunnel, rotors on each end of the motor assembly and inlet ducts on each end of the tunnel. The tunnel thruster attempts to address the short comings of the commercial thrusters. The tunnel thruster is an all electrically powered thruster with all mechanical components contained within the tunnel. The rotors operate independently and are counter-rotating.

Abstract: A jet propulsion system is provided for a water craft in which the secondary flow channel allows water to flow around the impeller region and bypass the impeller blades under certain conditions. The bypass feature provided by the secondary flow channel decreases static inlet pressure and improves the operation of the marine propulsion device at high speeds. In addition, the secondary flow channel increases the total mass flow of water through the steering rudder and therefore improves steering when the propulsion system is being rapidly decelerated, such as during sudden stopping conditions. The secondary flow channel can incorporate one or more individual conduits that bypass the impeller region of the propulsion system or, alternatively, can comprise an annular channel completely surrounding the impeller region.

Abstract: A control mechanism is provided for a jet propelled watercraft that enables an operator to engage and disengage a braking gate with hand pressure using a lever on the handlebar of the watercraft. Hydrodynamic assist devices are provided to assist the operator during the engagement and disengagement of the brake by counteracting both rejecting forces and retaining forces exerted on the gate by the stream of water ejected from the nozzle of the jet propulsion device. During initial insertion of the gate into the stream of water, a first hydrodynamic assist device counteracts the rejection forces otherwise exerted by the stream of water against a deflecting surface of the gate. After full deployment of the gate within the stream of water, a second hydrodynamic assist device opposes the retaining forces exerted on the gate and reduce the magnitude of the force necessary to be exerted by the operator to move the gate out of the stream of water and disengage the brake.