Abstract: The present invention provides a turbo heater which utilizes a gas turbine engine and a heat exchanger assembly. The gas turbine engine is adapted to efficiently operate over a prolonged period of time and at varying power outputs without adverse or detrimental effects to the components thereof. For example, the gas turbine engine includes bearing assemblies and a fuel delivery systems which are uniquely designed for the demands of repeated cycling (i.e. starting and stopping), as well as operation at various power outputs without damage to the gas turbine engine. In addition, the use of exhaust gas from the gas turbine engine eliminates direct impingement of combustion on the heat exchanger element, thereby significantly increasing the durability and life span of the turbo heater.

Abstract: The present invention provides a turbo heater which utilizes a gas turbine engine and a heat exchanger assembly. The gas turbine engine is adapted to efficiently operate over a prolonged period of time and at varying power outputs without adverse or detrimental effects to the components thereof. For example, the gas turbine engine includes bearing assemblies and a fuel delivery systems which are uniquely designed for the demands of repeated cycling (i.e. starting and stopping), as well as operation at various power outputs without damage to the gas turbine engine. In addition, the use of exhaust gas from the gas turbine engine eliminates direct impingement of combustion on the heat exchanger element, thereby significantly increasing the durability and life span of the turbo heater.

Abstract: The present invention provides a turbo heater which utilizes a gas turbine engine and a heat exchanger assembly. The gas turbine engine is adapted to efficiently operate over a prolonged period of time and at varying power outputs without adverse or detrimental effects to the components thereof. For example, the gas turbine engine includes bearing assemblies and a fuel delivery systems which are uniquely designed for the demands of repeated cycling (i.e. starting and stopping), as well as operation at various power outputs without damage to the gas turbine engine. In addition, the use of exhaust gas from the gas turbine engine eliminates direct impingement of combustion on the heat exchanger element, thereby significantly increasing the durability and life span of the turbo heater.

Abstract: The present invention provides a turbo heater which utilizes a gas turbine engine and a heat exchanger assembly. The gas turbine engine is adapted to efficiently operate over a prolonged period of time and at varying power outputs without adverse or detrimental effects to the components thereof. For example, the gas turbine engine includes bearing assemblies and a fuel delivery systems which are uniquely designed for the demands of repeated cycling (i.e. starting and stopping), as well as operation at various power outputs without damage to the gas turbine engine. In addition, the use of exhaust gas from the gas turbine engine eliminates direct impingement of combustion on the heat exchanger element, thereby significantly increasing the durability and life span of the turbo heater.

Abstract: A gas turbine engine (20) comprises a diffuser (24) and a nozzle (26) affixed to a cylindrical housing member (22), a bearing assembly (34) including a support tube (36) affixed at one end (36a) in cantilever fashion to a radially inner portion (26c) of the nozzle, a compressor (28) and a turbine (30) affixed to axially spaced apart ends of a shaft (32) rotatably mounted therebetween in the support tube by antifriction bearings, and an annular combustion chamber (40) disposed between the compressor and turbine and concentric to the shaft. A fuel slinger (38), affixed to the shaft, receives fuel from an air/fuel annulus (96) defined by the support tube and shaft. An air/fuel mixture in the annulus also lubricates the bearings and cools a hub portion (30a) of the turbine. Movement of the mixture through the air/fuel annulus is enhanced by pumps (38c, 102, 104 and 312).

Abstract: A fuel injection fuel supply system for a combustion engine, having a plurality of combustion cylinders and pistons, has a single fuel injector valve effective for injecting all of the required fuel in equal amounts as to each of the combustion cylinders of the engine.

Abstract: An arrangement and method is disclosed for enabling hypergolic combustion of a fuel mixture in the combustion chamber of a combustion device such as an internal combustion engine by irradiation of the fuel and/or of the fuel-air mixture with a beam of ultraviolet radiation to produce disassociation of a relatively high proportion of the fuel molecules to enable hypergolic combustion. Various arrangements are disclosed for accomplishing UV irradiation of the fuel in the context of an internal combustion piston engine, and a mercury vapor lamp or a laser are alternatively employed as a UV beam generator.

Abstract: A method and apparatus are disclosed for pretreating fuel prior to its injection into a combustion chamber to a critical level of activation to enable negligible ignition delay and substantially instantaneous completion of the combustion process. Each quantity of fuel is treated in a plurality of phases to achieve the critical level of fuel activation by the combined effect of each, with fuel heating combined with one or more further activation treatment phases, including catalysis, UV irradiation, or passing each quantity of the fuel through an electrical discharge to thereby enable hypergolic combustion by a combination of the effects thereof.

Abstract: An apparatus and method are disclosed for pretreatment of fuel prior to injection into the combustion chamber of a combustion device such as an internal combustion engine comprising heating of the fuel to a sufficiently high temperature to activate the fuel molecules to a critical degree enabling "hypergolic" combustion, i.e., combustion without significant ignition or combustion delay. The fuel is circulated through a vessel passing through the combustion chamber which is insulated to reduce heat loss such as to regeneratively preheat the fuel to a temperature on the order of 1000.degree. F. Regenerative heating of the fuel is alternatively combined with a catalytic treatment of the heated fuel to partially activate the fuel molecules to reduce the heating necessary to achieve hypergolic combustion.

Abstract: A method and apparatus are disclosed for rapidly heating vaporized fuel to elevated temperatures prior to its injection into a combustion chamber to achieve negligible ignition delay and substantially instantaneous completion of the combustion process. Heating of the fuel is initiated by preheating each quantity of fuel with heat extracted from the engine exhaust, and the preheated fuel is vaporized and subsequently rapidly heated to a high temperature by being adiabatically compressed immediately prior to injection into the combustion chamber. The fuel activation effect of compressive heating is alternatively augmented by contact of the fuel with a catalytic material, to achieve hypergolic combustion by a combination of catalysis and heating.

Abstract: A fast acting mechanical valve (2) affords macroeffects with high speed, low mass, micromovement. A first microporous planar sheet-like electrically conductive film (4) has an electrically insulative face surface (6), and an array of microapertures (7-11) through the film and face surface. A second microporous planar sheet-like electrically conductive film (12) abuts the insulative face surface and has an array of microapertures (13-16) therethrough nonaligned with the first array. An electric circuit (26, 28 and 30) supplies electric current flow through the parallel films to effect relative transverse movement therebetween due to interacting electromagnetic fields, for actuating the valve between closed and open positions.

Abstract: A drivetrain (48) for an electric passenger vehicle (10) includes a battery (40) for energizing a single-phase A.C. traction motor (18) which drives a ground engaging wheel (12) through a multi-speed transaxle (20). The motor is characterized by an external ferrite permanent magnet rotor (26) drivingly engaging an input shaft (32) of the transaxle. The motor is controlled by an inverter circuit (44) and a control circuit (46) which generates switch command signals to reciprocally actuate power transistors (56 and 62) within the inverter circuit as a function of operator demand, rotor position and rotor speed. The control circuit includes a motor positioning circuit (442) which toggles the motor current when the rotor speed falls below a predetermined level to dither the rotor about a park position for a predetermined period. A pre-start rotor positioner (224) is provided to mechanically lock the rotor in its park position to ensure the availability of a high electrical starting torque.

Abstract: An energy storage device (10) is disclosed consisting of a stretched elongated elastomeric member (16), disposed within a tubular housing (14), which elastomeric member (16) is adapted to be torsionally stressed to store energy. The elastomeric member (16) is configured in the relaxed state with a uniform diameter body section, transition end sections, and is attached to rigid end piece assemblies (22, 24) of a lesser diameter. The profile and deflection characteristic of the transition sections (76, 78) are such that upon stretching of the member, a substantially uniform diameter assembly results to minimize the required volume of the surrounding housing (14). During manufacture, woven wire mesh sleeves (26, 28) are forced against a forming surface and bonded to the associated transition section (76, 78) to provide the correct profile and helix angle. Each sleeve (26, 28) contracts with the contraction of the associated transition section to maintain the bond therebetween.

Abstract: Thermal barriers (10, 26) fixed to mushroomed heads (12, 28) of poppet valves intended for diesel engines are disclosed. Thermal barrier (10) includes an insulating material (18) bonded to a face portion (12a) of mushroom head (12), a sheet metal shield (20) covering the insulating material, and a flange (22) clamped over the outer periphery of the shield and welded to the valve head. Thermal barrier (26) includes an insulating material encapsulated in a sheet metal sheath defining an evacuated chamber (32) which covers a face portion (28a) of the mushroom head (28), a sheet metal shield (30), and a flange portion (28b) integrally formed with the mushroom head and spun over the shield during final assembly to clamp the shield over the encapsulated insulating material. The flanges in both embodiments make line contact with the shield to minimize heat flow from the shields to the flanges and hence to the valve head.

Abstract: A liquid containing a solvent to be evaporated is fed to a concentration chamber which is fluidly connected to an evaporation chamber maintained at a reduced pressure. A vapor compression means withdraws solvent vapor from the evaporation chamber, compresses the vapor and forces the compressed vapor to a liquification chamber. Regulator means responsive to the density of the liquid remaining within the concentration chamber will regulate the rate of solvent evaporation to provide a concentrate suitable for recycling.A method of operating the still of this invention utilizes the technique of increasing the compressor capacity until the compressor begins to surge and then reducing the capacity a fixed amount to provide the desired efficiency.

Abstract: A small gas turbine engine having a small, high speed shaft assembly including a central shaft member, a radial outflow compressor rotor secured to one end of the central shaft member with its inlet end disposed outboard of the shaft assembly, and a radial inflow turbine rotor secured to the other end of the central shaft member with its discharge end disposed outboard of the shaft assembly. The shaft assembly is supported at its ends, outboard of the rotors, by a pair of bearings which are axially secured but allow limited radial movement of the shaft assembly. An annular combustor is disposed between the turbine and compressor rotors in encircling relation to the central shaft member. Fuel is supplied to the combustor chamber from the exhaust end of the turbine through an axial passage in the shaft assembly opening at one end outboard of the exhaust end bearing and communicating at its other end with radial ports in the central shaft member arranged to sling fuel into the combustor chamber.

Abstract: A small gas turbine engine having a small, high speed shaft assembly including a central shaft member, a radial outflow compressor rotor secured to one end of the central shaft member with its inlet end disposed outboard of the shaft assembly, and a radial inflow turbine rotor secured to the other end of the central shaft member with its discharge end disposed outboard of the shaft assembly. The shaft assembly is supported at its ends, outboard of the rotors, by a pair of bearings which are axially secured but allow limited radial movement of the shaft assembly. An annular combustor is disposed between the turbine and compressor rotors in encircling relation to the central shaft member. Fuel is supplied to the combustor chamber from the exhaust end of the turbine through an axial passage in the shaft assembly opening at one end outboard of the exhaust end bearing and communicating at its other end with radial ports in the central shaft member arranged to sling fuel into the combustor chamber.

Abstract: A small gas turbine engine having a small, high speed shaft assembly including a central shaft member, a radial outflow compressor rotor secured to one end of the central shaft member with its inlet end disposed outboard of the shaft assembly, and a radial inflow turbine rotor secured to the other end of the central shaft member with its discharge end disposed outboard of the shaft assembly. The shaft assembly is supported at its ends, outboard of the rotors, by a pair of bearings which are axially secured but allow limited radial movement of the shaft assembly. An annular combustor is disposed between the turbine and compressor rotors in encircling relation to the central shaft member. Fuel is supplied to the combustor chamber from the exhaust end of the turbine through an axial passage in the shaft assembly opening at one end outboard of the exhaust end bearing and communicating at its other end with radial ports in the central shaft member arranged to sling fuel into the combustor chamber.

Abstract: A small gas turbine engine having a small, high speed shaft assembly including a central shaft member, a radial outflow compressor rotor secured to one end of the central shaft member with its inlet end disposed outboard of the shaft assembly, and a radial inflow turbine rotor secured to the other end of the central shaft member with its discharge end disposed outboard of the shaft assembly. The shaft assembly is supported at its ends, outboard of the rotors, by a pair of bearings which are axially secured but allow limited radial movement of the shaft assembly. An annular combustor is disposed between the turbine and compressor rotors in encircling relation to the central shaft member. Fuel is supplied to the combustor chamber from the exhaust end of the turbine through an axial passage in the shaft assembly opening at one end outboard of the exhaust end bearing and communicating at its other end with radial ports in the central shaft member arranged to sling fuel into the combustor chamber.