Abstract: A compliant foil fluid film thrust bearing including a thrust disk rotor, fluid foils, spring foils, a thrust plate, and a housing thrust surface The non-rotating but compliant fluid foils, mounted on the thrust plate and/or housing thrust surface and positioned adjacent to the thrust disk, have open faced channels that induce regenerative vortex flow patterns in the process fluid. The multiple spring foils together provide a tilting pad support for the fluid foils but allow them to follow the axial and overturning motion of the thrust disk. The interaction of the tilting pad underspring supports and the circumferential fluid pressure gradients in the process fluid between the fluid foils and the thrust disk rotor assure that the fluid foils will assume hydrodynamically efficient convex shapes on the surfaces adjacent to the rotor regardless of the load applied to the thrust bearing.

Abstract: A multi-segment radial bearing including a bushing with an interior bore having a plurality of anti-rotation retainers which are equally spaced and extend the axial length of the interior bore. The generally T-shaped retainers divide the interior bore of the bushing into a like plurality of lobes, with each lobe having a compliant foil and a foil underspring disposed between adjacent generally T-shaped retainers.

Abstract: A turbogenerator/motor controller with a microprocessor based inverter having multiple modes of operation. To start the turbine, the inverter connects to and supplies fixed current, variable voltage, variable frequency, AC power to the permanent magnet turbogenerator/motor, driving the permanent magnet turbogenerator/motor as a motor to accelerate the gas turbine. During this acceleration, spark and fuel are introduced in the correct sequence, and self-sustaining gas turbine operating conditions are reached. The inverter is then disconnected from the permanent magnet generator/motor, reconfigured to a controlled 60 hertz mode, and then either supplies regulated 60 hertz three phase voltage to a stand alone load or phase locks to the utility, or to other like controllers, to operate as a supplement to the utility. In this mode of operation, the power for the inverter is derived from the permanent magnet generator/motor via high frequency rectifier bridges.

Abstract: A helical flow compressor/turbine or pump/turbine with integral permanent magnet motor/generator is disclosed which can be configured as a single stage, two stage or three stage rotary machine. The impeller blades for this machine can be either radial for ease of manufacture or curved, with the curve at the leading edge being greater than at the blade root, for maximum fluid dynamic head pressure and maximum efficiency. Tapered flow channels are utilized to maximize fluid-dynamic efficiency. The helical flow machine disclosed produces precisely controlled pressure changes and energy changes in the process fluid passing through the machine and provides information on fluid flow rates.

Abstract: A low emissions combustion system for a gas turbine engine, including a generally annular combustor with a plurality of tangential fuel injectors to introduce a fuel/air mixture. The annular combustor includes a skirt shaped flow control baffle from the inner liner and air dilution holes in the inner liner underneath the flow control baffle and also in the cylindrical outer liner. The fuel injectors extend through the recuperator housing and into the combustor through an angled tube and then through a tangential guide in the cylindrical outer liner of the combustor housing. The fuel injectors generally comprise an elongated injector tube with the outer end including a coupler having at least one fuel inlet tube. Compressed combustion air is provided to the interior of the elongated injector tube from either holes or slits therein which receive compressed air from the angled tube around the fuel injector which is open to the space between the recuperator housing and the combustor.

Abstract: A liquid fuel pressurization and control system is disclosed which utilizes either a helical flow pump, or a helical flow pump followed by a gear pump, to pressurize liquid fuel to precisely the pressure level required by a turbogenerator's combustor injectors. This eliminates the need to overpressurize the fuel then regulate the fuel pressure down using a flow control valve or a pressure control valve. The shaft torque and shaft speed of the pump are controlled by the turbogenerator's power controller so as to assure that the turbogenerator's speed is precisely controlled (e.g. within ten (10) rpm out of one hundred thousand (100,000) rpm), and that its turbine exhaust temperature is precisely controlled (e.g. within two (2) degrees Fahrenheit out of twelve hundred (1200) degrees Fahrenheit) over the full range of turbogenerator electrical output power.

Abstract: A low emissions combustion system for a gas turbine engine, including a generally annular combustor with a plurality of tangential fuel injectors (14) to introduce a fuel/air mixture. The annular combustor includes a skirt shaped flow control baffle (48) from the inner liner and air dilution holes (50-54) in the inner liner underneath the flow control baffle and also in the cylindrical outer liner. The fuel injectors (14) extend through the recuperator housing and into the combustor through an angled tube and then through a tangential guide in the cylindrical outer liner of the combustor housing. The fuel injectors generally comprise an elongated injector tube with the outer end including a coupler having at least one fuel inlet tube. Compressed combustion air is provided to the interior of the elongated injector tube from either holes or slits therein which receive compressed air from the angled tube around the fuel injector which is open to the space between the recuperator housing and the combustor.

Abstract: A gaseous fuel compression and control system is disclosed which utilizes one or more helical flow compressor/turbine integrated with a permanent magnet motor/generator and driven by a torque controlling inverter to compress or expand gaseous fuels, precisely control fuel pressure and flow, and precisely control the operations (speed, combustion temperature and output power) of a gaseous fuel fired turbogenerator.

Abstract: A system to hydrostatically augment the thrust load capacity of a bilateral compliant foil hydrodynamic fluid film thrust bearing for a turbomachine is disclosed. A plurality of channels and fixed orifices are provided in the bearing thrust plate to deliver and regulate compressor bleed air flow to the compressor side of the bilateral compliant foil hydrodynamic fluid film thrust bearing which includes additional channels and orifices to direct the bleed air against the bearing rotor thrust disk. After impinging on the rotor thrust disk, the bleed air flow exits the thrust bearing through a plurality of variable orifices comprised of the hydrodynamic thrust bearing elements which are controlled in their flow conductance by the axial position of the rotor thrust disk. The bleed air may then pass through the adjacent journal bearing which functions as a fixed orifice.

Abstract: A gaseous fuel compression and control system is disclosed which utilizes a helical flow compressor/turbine integrated with a permanent magnet motor/generator and driven by a torque controlling inverter to compress or expand gaseous fuels, precisely control fuel pressure and flow, and precisely control the operations (speed, combustion temperature and output power) of a gaseous fuel fired turbogenerator.

Abstract: A thrust load compensating system for a compliant foil hydrodynamic fluid film thrust bearing is disclosed. The system includes an end cap over the free end of a rotary machine shaft, a compliant foil hydrodynamic fluid film journal bearing located at the free end of the shaft, and a source of air whose pressure varies with the square of turbomachine speed. The compliant foil hydrodynamic fluid film journal bearing located at the free end of the shaft serves as a non-contacting rotary shaft seal and, together with the end cap and free end of the shaft forms a thrust piston chamber. The thrust load compensating system of the present invention can be utilized in high speed rotary machines that have a compressor wheel and a turbine wheel that generate large axial aerodynamic forces that increase with speed.

Abstract: A liquid fuel pressurization and control system is disclosed which utilizes either a helical flow pump, or a helical flow pump followed by a gear pump, to pressurize liquid fuel to precisely the pressure level required by a turbogenerator's combustor injectors. This eliminates the need to overpressurize the fuel then regulate the fuel pressure down using a flow control valve or a pressure control valve. The shaft torque and shaft speed of the pump are controlled by the turbogenerator's power controller so as to assure that the turbogenerator's speed is precisely controlled (e.g. within ten (10) rpm out of one hundred thousand (100,000) rpm), and that its turbine exhaust temperature is precisely controlled (e.g. within two (2) degrees Fahrenheit out of twelve hundred (1200) degrees Fahrenheit) over the full range of turbogenerator electrical output power.

Abstract: A compound shaft for a three journal bearing turbomachine which includes a first stiff shaft supported by two journal bearings, a second stiff shaft supported by one journal bearing and by one bi-directional thrust bearing, and a flexible disk shaft that operably connects the first and second stiff shafts. The flexible disk shaft utilizes a flexible disk to function as a low hysterisis joint in parallel with a non-linear trunion clock spring such that the flexible disk shaft transfers overturning support from the first stiff shaft to the second stiff shaft and transfers thrust bearing support from the second stiff shaft to the first stiff shaft. The flexible disk shaft allows the compound shaft to tolerate extremely large misalignments of the three journal bearings from a straight line axis.

Abstract: The present invention is directed to a catalytic combustion system having a gas turbine engine recuperator and an annular catalytic combustor. The annular catalytic combustor includes a pre-burner/pre-mixer which functions as a pre-burner during startup and as a pre-mixer for the fuel and air during catalytic operation. This pre-burner/pre-mixer includes a plurality of primary tangential air-fuel venturis each having a fuel injector, and a plurality of secondary tangential air dilution holes. The pre-burner/pre-mixer is joined to the annular in-line catalytic canister by a transition section which includes a plurality of tertiary air dilution holes which introduce air radially into the transition section from the inner liner thereof. The in-line annular catalyst canister includes a large plurality of microlith catalyst elements positioned between support tings and held at the open end thereof by a plurality of support spokes.

Abstract: A compliant foil hydrodynamic fluid film thrust bearing is disclosed which is comprised of a two sided thrust disk rotating element, compliant fluid foil members that axially enclose the rotating element, compliant spring foil members that axially enclose the fluid foil members, a spacer ring that coaxially surrounds the thrust disk and is axially disposed between the fluid foil members, and a compliantly mounted and spring preloaded thrust plate element and a foil retaining bearing housing with an inwardly facing thrust surface that together axially enclose the spring foil members, the fluid foil members and the spacer ring. The foils have self shimming rings at their peripheries and are formed by chemical etching from flat sheets. The fluid foils are subsequently coated with a wear resistant coating and then cold stamped to imboss compound curve profiles into the fluid foil to form wedge channels which induce vortex fluid flow patterns in the bearing's working fluid.

Abstract: A fluid film foil bearing having a resilient trailing edge support.

Abstract: A method of forming an underspring for a foil thrust bearing from a uniform thickness sheet. The underspring is formed by chemically etching a plurality of slots in the disk and then stamping the tabs formed by the slots.

Abstract: A conditioning circuit for use with a pressure transducer is disclosed which provides a digitally readable electronic output signal indicative of capacitance sensed by the pressure transducer. The circuitry of the present invention utilizes an R-C charge/discharge circuit, thereby enabling the circuitry to be substantially more compact than previously utilized L-C circuits. The circuitry is usable with either pressure transducers having a single capacitance or those including a reference capacitance, and the circuitry provides a high resolution, high precision output.

Abstract: A two pole permanent magnet rotor which utilizes a single cylindrical two pole permanent magnet mounted between two end pieces and surrounded by a retaining hoop. The cylindrical two pole permanent magnet, which is made of high energy product material, is "straight through" diametrically magnetized to provide a sinusoidal air gap flux distribution which eliminates losses due to harmonics. The cylindrical two pole permanent magnet may be made of a plurality of smaller magnet blocks which are stacked and machined to form cylindrical configuration.

Abstract: A heat exchanger of the type characterized by a plurality of heat exchanger tubes separated by cooling fins. The ends of the tubes being inserted into a leadless header plate and thereafter brazed thereto. The overall depth of the heat exchanger being approximately equal to the width of the heat exchanger tube plus twice the thickness of the material of the header plate. Heat exchange tube ends being inserted into slots formed in the header plate by use of an alignment tool.