Abstract: A steam raising apparatus for a gas turbine driven powerplant in which fuel and water are introduced into a heat exchanger at multiple pressures and steam/fuel mixtures are removed from the heat exchanger at multiple pressures, some of which are above the desired pressure for combustion and some of which are below. The higher pressure flows are reduced in pressure by using them to drive a steam turbine coupled to a steam compressor, and the lower pressure flows are increased in pressure by means of the compressor. The resultant flows are then be combined into a single flow at the required pressure and routed to the combustor. Alternatively, multiple steam jet ejectors forming a thermocompressor assembly are used instead of the steam turbine/steam compressor assembly.

Abstract: An injector for turbine engines which includes a shaped injector core fitted with an eccentric spinner inlet communicating with a cylindrical, annular fuel spinner chamber and a preheater or evaporator for preheating and vaporizing fuel, wherein the vaporized fuel is eccentrically injected into the fuel spinner chamber to effect a spinning fuel sequence around a fuel guidance pin extending through the center of the fuel spinner chamber. Compressed air from the turbine compressors flows through the primary nozzle of an air guidance nozzle surrounding the injector core into a shaped secondary nozzle, where the air mixes with the spinning fuel at a selected air flow angle to facilitate thorough mixing of the fuel and air as the combustible mixture is channeled into the annular turbine combustor.

Abstract: The apparatus for cooling intake air includes a heat exchanger for transmitting the cold energy of fuel to a heat medium through an intermediate heat medium having a different property from the heat medium, a pressure controller for controlling the pressure within the heat exchanger so that a temperature of the intermediate heat medium is kept higher than a solidifying point of the heat medium, and an intake air cooling system for cooling intake air to be introduced into the gas turbine using the heat medium cold energy. The intermediate heat medium may be condensable by the cold energy of the fuel and vaporizable by the heat medium or may have a solidifying point lower than the fuel.

Abstract: A combustor for a gas turbine engine is disclosed which is able to operate efficiently at inlet air flows having a high subsonic Mach Number. The combustor has an outer liner and an inner liner spaced therefrom, wherein a combustion chamber is defined therebetween. A dome inlet module is provided which is in flow communication with compressed air flow from a compressor upstream thereof. The dome inlet module has an outer member fixed to the outer liner and an inner member fixed to the inner liner, wherein a flow passage is defined by the outer and inner members for the compressed air flow to flow freely from a compressor to the combustion chamber. Fuel atomizers are then utilized to inject fuel into the flow passage so that the fuel is mixed with the compressed air stream to form a fuel/air mixture which enters the combustion chamber.

Abstract: A system is disclosed for regulating oil and fuel temperatures in a turbojet engine having an engine accessory driven at constant speed by a power transmission which is driven by the turbojet engine. The system has a first closed oil circuit for circulating oil through the turbojet engine, a second closed oil circuit for circulating oil through the power transmission, a fuel circuit for supplying fuel to the turbojet engine, an air/oil heat exchanger connected to the first closed oil circuit to pass oil in heat exchange relationship with air, an oil/fuel heat exchanger connected to the fuel circuit and to the first closed oil circuit downstream of the air/oil heat exchanger to pass oil and fuel in heat exchange relationship, and an oil/oil heat exchanger connected to the first and second closed oil circuits to pass oil in heat exchange relationship, the connection to the first closed oil circuit being downstream of the oil/fuel heat exchanger.

Abstract: An airblast fuel nozzle has an injector head with an extension or support strut. An annular valve spool with a fuel discharge orifice is fixed to the head and a metering assembly surrounds the valve spool. The metering assembly includes an axially-slidable annular valve sleeve and a metal bellows. The bellows, a compression spring, and one or more shims between the valve spool and the injector head provide a preset bias on the valve sleeve such that the valve sleeve initially closes or minimizes the fuel metering area through longitudinally-extending fuel swirl slots spaced about the valve spool at the discharge orifice. When fuel under pressure flows through the injector, the fuel pressure overcomes the preset bias of the sleeve and moves the valve sleeve axially with respect to the valve spool, thereby increasing the fuel metering area through the fuel swirl slots and allowing fuel to flow (with a swirling component) therethrough.

Abstract: A gas turbine driven powerplant having one or more compressors for producing a down stream air flow, a heat exchanger positioned down stream of the compressors followed by a side stream flow coolant line, a regenerator positioned down stream of the heat exchanger and side stream coolant line, a combustor positioned down stream of the regenerator, one or more turbines positioned down stream of the combustor and mechanically coupled to the compressors, and a power turbine positioned down stream of the turbines. Combustible effluent flows through the heat exchanger and to the combustor, and air discharged from the compressors flows through the heat exchanger and to the coolant line and regenerator. Heat is transferred from the compressor discharge air to the combustible effluent, thereby producing cooling air and heating the combustible effluent. The heat exchanger can be a heat exchanger or a methane/steam reformer which produces a hydrogen-rich, low NO.sub.x, steam diluted combustible effluent.

Abstract: A small gas turbine, in particular for powering airplane models, provided with a casing (3), a compressor rotor (1, 2), a combustion chamber (15-17) and a turbine rotor (5), the turbine rotor (5) driving the compressor rotor(1, 2) by a shaft positioned in a shaft tunnel extending through the combustion chamber (15-17) and surrounded by a helical fuel feed and vaporizing tube (22, 23), the combustion chamber (15-17) being defined by a cylindrical outer wall (15) and a frusto-conical inner wall (16) provided with combustion air intake orifices (19-21)the outlet side of the inner wall (16) of the combustion chamber extending into a cylindrical flow element (6, 7) forming an annular gap therewith, which in turn extends into the center opening of the turbine side guide vane ring (4) and is supported by the end (9) of the shaft tunnel (8), and the other end of the shaft tunnel (8) being secured to the casing (3) between the compressor rotor (1, 2) and the front wall (17) of the combustion chamber.

Abstract: A gas turbine driven powerplant having one or more compressors for producing a down stream air flow, a heat exchanger positioned down stream of the compressors followed by a side stream flow coolant line, a regenerator positioned down stream of the heat exchanger and side stream coolant line, a combustor positioned down stream of the regenerator, one or more turbines positioned down stream of the combustor and mechanically coupled to the compressors, and a power turbine positioned down stream of the turbines. Combustible effluent flows through the heat exchanger and to the combustor, and air discharged from the compressors flows through the heat exchanger and to the coolant line and regenerator. Heat is transferred from the compressor discharge air to the combustible effluent, thereby producing cooling air and heating the combustible effluent. The heat exchanger can be a heat exchanger or a methane/steam reformer which produces a hydrogen-rich, low NO.sub.x, steam diluted combustible effluent.

Abstract: An anti-icing system to prevent the formation of ice on, or to remove ice from selected portions of a gas turbine engine is disclosed that is not directly dependent upon the mode or speed of operation of the gas turbine engine. The system has a heat exchanger into which flows a tapped portion of air from the compressor and fuel from the engines fuel supply system. The fuel supply system includes a fuel return circuit which connects the fuel pump outlet to the fuel pump inlet so as to return or recycle fuel to the fuel pump inlet when the engine demand for fuel is low, such as under lower power operating conditions. This recycling of the fuel raises the temperature of the fuel such that, in the heat exchanger, heat is transferred to the tapped portion of the air from the compressor thereby raising the temperature of such tapped air such that it may be directed onto selected portions of the gas turbine engine to either prevent formation of ice, or to remove ice from these portions.

Abstract: A method for managing the energy produced by a gas turbine engine, which includes utilizing an endothermic fuel to cool the combustion products in the exhaust section of the gas turbine engine prior to burning the fuel in the combustion section of the engine.

Abstract: A method for providing both starting power and thermal management requirements of a vehicle incorporating a gas turbine engine by using the same unit to alternately provide both starting power and cooling air.

Abstract: An improved system for recovering waste heat from a combustion turbine in a combined cycle power plant of the type that includes at least one combustion turbine and at least one steam turbine includes a first heat recovery system for heating condensate in the steam turbine cycle with heat from the hot exhaust gases from the combustion-type turbine, and a second heat recovery system for heating the fuel that is used in the combustion turbine with heat from the exhaust gases. The second system permits recovery of heat energy that is not recovered by the first system, thereby improving plant efficiency.

Abstract: A gas turbine engine having a compressor and an air-cooled turbine is provided with a cooling system for decreasing the temperature of the turbine cooling air. A heat exchanger, mounted on the compressor casing, receives a portion of the pressurized air which is bled from the compressor. A heat sink medium is pumped through the heat exchanger into heat exchange relationship with the pressurized air, thereby cooling the air. The cooled air is then further pressurized and routed to and circulated through the turbine rotor blades to provide improved cooling thereof. The intercooling of the compressor bleed air permits a reduction in the quantity of compressor air required for turbine rotor blade cooling or allows an increase in turbine entry temperature and thus provides an improvement in engine power and performance. In the case where the heat sink medium is engine fuel, the heat extracted from the compressor bleed air is returned to the engine operating cycle in the form of heated engine fuel.

Abstract: A thermal management system for a propulsion engine of a supersonic or hypersonic aircraft is provided that uses a single flow of endothermic fluid as engine fuel and as a heat sink for engine cooling. The system includes a plurality of heat exchangers in flow series arrangement. Each heat exchanger has a reactor portion, containing a catalyst, in heat exchange relation with a heat source portion. The single fluid flow flows through each of the reactor portions and heat source portions. The heat for the reaction in the reactor portions is provided by the fluid in the heat source portion which as a result is cooled. This cooled fluid is then reheated by flowing it past a hot portion of the engine after which the fluid can flow to another reactor portion or to the engine's combustor where it is ignited.

Abstract: A cooling arrangement for the cooling air of hypersonic jet engines comprises a heat exchanger in which the temperature of the cooling air is reduced by means of the fuel to be burnt in the engine. In order to keep the operating temperatures of the heat exchanger within controllable limits, a partial flow of the cooling air is branched off downstream of the heat exchanger and is admixed to the cooling air upstream of the heat exchanger for reducing the temperature.

Abstract: A combustor includes radially spaced apart outer and inner liners joined together at upstream ends through an annular dome disposed coaxially about a longitudinal centerline axis. A plurality of circumferentially spaced apart fuel injectors are disposed adjacent to an arcuate a splashplate for injecting fuel thereagainst, the splashplate being arcuate about the centerline axis. Primary air is channeled along the splashplate for mixing with the injected fuel for forming a fuel/air mixture dischargeable from the splashplate into a combustion zone defined between the liners and the dome.

Abstract: A heat regenerative external combustion engine is disclosed herein. The ene includes fuel inlet means which extends along the exhaust passage and/or combustion chamber in order to preheat the fuel. To provide for preheating by gases in both the combustion chamber and the exhaust passage, the combustion chamber is arranged annularly around the drive shaft and between the cylinders. This configuration also is advantageous in that it reduces the noise of combustion. The engine of the invention is particularly well-suited for use in a torpedo.

Abstract: A heat exchange apparatus to heat hydrocarbon liquid fuel that is particularly useful for a combustion system and method of operation that by fuel in a heat exchanger and avoids undesirable thermal fuel deposits that would otherwise reduce the effectiveness of the heat exchanger. The invention provides a means to mix a relatively large amount of non-condensable gas with the fuel prior to gasification heating thus reducing the residence time of the fuel adjacent to the hot surface. The non-condensable gas may be air, a cryogenic such as methane, or a chemical fraction of the gasified fuel which by itself does of promote the formation of significant amounts of gums or coke deposits.

Abstract: A program-controlled heat management system for an aircraft's bypass gas turbine (turbofan) engine installation, in which the engine's fuel system is put into direct heat exchange relationship with the engine's own oil system, and with an engine-driven electrical generator's oil system, by means of respective fuel/oil heat exchangers and also into selective indirect heat exchange relationship with a variable proportion of the engine's bypass air means of an engine oil/air heat exchanger. The fuel system is switchable between four different fuel flow configurations in order to vary the heat flows between the fuel system and the oil systems, two of the fuel flow configurations also involving recirculation of fuel from the engine's fuel system to a fuel tank in the aircraft wing in order to put the fuel system into selective heat exchange relationship with the tank and hence with the airstream passing over the wing.

Abstract: A fluid pumping system that maintains the temperature rise at a minimum value of the fluid being recirculated in the pumps during a given operating condition in the pumping system's operating envelope be disclosed. A pair of positive displacement pumps judiciously sized at different capacities are driven by a differential pumping or gearing system that is driven by a single source and cooperates with a fluid circuit delivering flow to a receiver so that the relationship of the pressure in the fluid circuit bears a given relationship to the flow capacity produced by each pump at given operating points in the operating envelope.

Abstract: A high efficiency/low nitric oxide emission gas turbine engine includes an interchanger for cooling a compressed air side stream which is used for cooling the turbine section. The heated fuel is then mixed with steam for injection into a combustor, thereby reducing nitric oxide emissions, while preventing condensation during mixing. Where water is used for injection instead of steam, both the fuel and water are preheated by interchange with the hot compressed gas stream. Preheating the fuel and/or water prevents steam condensate or water from entering the combustor, and does so using heat available within the gas turbine cycle thereby increasing overall turbine efficiency. In addition, utilizing a fuel/air interchanger reduces the size of the heat exchanger and the need for other auxiliary equipment, reducing costs while increasing turbine efficiency.

Abstract: A reflexive fuel heating system for fuel entering the fuel filter of an engine comprises a heat exchanger disposed between a fuel tank and the fuel filter for transferring heat generated in a gear type fuel pump to the fuel.

Abstract: A gas turbine engine that can operate at a very high efficiency over a wide range of load conditions. In one important feature of the invention, combustion gases are discharged along two paths, one with constant energy and the other with energy that varies in accordance with the engine load. The constant energy discharge drives a turbine that, in turn, operates a compressor for the engine at a constant, high efficiency. Alternatively, the compressor is driven at a speed that varies inversely with the engine load such that the engine operates at a high efficiency for all loads. In another, independent feature of the invention, the combustion occurs at a stoichiometric ratio of fuel and air, with the turbine blades being protected from the vastly increased combustion gas temperatures by an internal array of passageways through which cooling liquid, e.g., liquid fuel, and air are channeled.

Abstract: A secondary power generating system and method is provided that can drive an aircraft's accessories, and deliver cooling flow and fuel flow to a propulsion engine such as a turbojet, ramjet or turboramjet. This system and method employs a heat exchanger in which high pressure, endothermic, liquid fuel absorbs heat from the air exiting the engine's compressor and as a result is transformed into a high pressure, gaseous fuel. The high pressure gas is expanded across a motor which extracts the pressure energy and converts this energy into mechanical power for driving accessories. The gas is then fed into the engine's combustor where it is ignited. The cooled air exiting the heat exchanger is returned to the propulsion engine and is used for cooling various components such as blades and shafts therein.

Abstract: A fuel control valve arrangement is provided, which when connected to a number of fuel flow paths in the fuel system of a turbofan aeroengine, is capable of interconnecting them in several different fuel flow configurations as necessary to vary transport of heat around the fuel system. The valve arrangement has fuel ports as necessary to connect it to the fuel flow paths and transfer fuel between a diverter valve component and a fuel spill control valve component, each of which has independently translatable valve elements which are positionable to selectively prevent communication between the fuel ports. The spill control valve element is controllable to move progressively over a range of positions to throttle fuel flow to one of the ports and the connected fuel flow path which spills fuel back to a fuel supply tank.

Abstract: A drive for buses and similar motor vehicles comprises a gas motor (14) which is provided to drive a generator (25) which in turn drives electric motors (27) which preferably are directly coupled to the drive wheels of the vehicle. The gas motor is driven by natural gas which is carried by the vehicle contained in containers (1) which maintain the natural gas at a temperature of about -163.degree. C. The natural gas is brought into gaseous condition by being transported through a first heat exchanger (7) where the liquid natural gas is exposed to the exhaust gases of the gas motor to attain a partial evaporation of the LNG. The partly evaporated liquid thereupon passes through a second heat exchanger where it is exposed to the cooling liquid of the gas motor and as a consequence thereof the LNG changes to a gaseous state and is finally supplied to the gas motor.

Abstract: A program-controlled heat management system for an aircraft's bypass gas turbine (turbofan) engine installation, in which the engine's fuel system is put into direct heat exchange relationship with the engine's own oil system, and with an engine-driven electrical generators's oil system, by means of respective fuel/oil heat exchangers and also into selective indirect heat exchanger relationship with a variable proportion of the engine's bypass air means of an engine oil/air heat exchanger. The fuel system is switchable between four different fuel flow configurations in order to vary the heat flows between the fuel system and the oil systems, two of the fuel flow configurations also involving recirculation of fuel from the engine's fuel system to a fuel tank in the aircraft wing in order to put the fuel system into selective heat exchange relationship with the tank and hence with the airstream passing over the wing.

Abstract: A high efficiency/low nitric oxide emission gas turbine engine includes an interchanger for cooling a compressed air side stream which is used for cooling the turbine section. The heated fuel is then mixed with steam for injection into a combustor, thereby reducing nitric oxide emissions, while preventing condensation during mixing. Where water is used for injection instead of steam, both the fuel and water are preheated by interchange with the hot compressed gas stream. Preheating the fuel and/or water prevents steam condensate or water from entering the combustor, and does so using heat available within the gas turbine cycle thereby increasing overall turbine efficiency. In addition, utilizing a fuel/air interchanger reduces the size of the heat exchanger and the need for other auxiliary equipment, reducing costs while increasing turbine efficiency.

Abstract: A gas turbine engine having a series intercooler positioned between a first and a second compressor. The intercooler has a first fuel heating system which has a heated fuel outlet and the heated fuel outlet is coupled to a combuston region of the engine. The intercooler also has a second feedwater intercooler stage which heats feedwater and the heated feedwater is input into a turbine exhaust heat exchanger. At least one turbine is positioned downstream of the combustor region and the turbine exhaust heat exchanger is downstream of the turbine. The intercooler may also include the first fuel heating system having the heated fuel outlet coupled to the combustor region and a second intercooler stage having a water input port.

Abstract: The efficiency of a combined cycle power plant is improved by preheating fuel supplied to a combustion turbine. The flow rate of feed water through an economizer section of a heat recovery steam generator is increased, and the excess flow, over that required to sustain saturated steam production in an evaporator section, is flowed through a heat exchanger to preheat the fuel.

Abstract: Carbon build-up in a hot gas generator is avoided in a construction including a vessel 24 having a narrow inlet end 26, a narrow outlet end 28 and an intermediate, relatively wide, combustion chamber 30 by either disposing a heat shield 50 on the interior surface 48 of the combustion chamber 30 or locating a flow path 54 for coolant about the exterior surface 52 of the vessel 24, or both.

Abstract: A rotor bearing on the turbine side of a gas turbine is surrounded by a concentric cavity through which fuel is routed from its source to the turbine combustion chamber. The fuel of the gas turbine is used as the coolant for the rotor bearing and at the same time the concentric cavity surrounding the bearing forms a hydraulic "compression" film damping device.

Abstract: The externally vaporizing system of the present invention incorporates an auxiliary burner which is supplied with compressor discharge air at a rate which is regulated to the main fuel flow rate. The auxiliary burner is operated at approximately stoichiometric fuel-air ratio, in order to provide very-hot, nearly-inert gases for vaporizing the main fuel supply. The main fuel is sprayed in the auxiliary burner exit gas stream where rapid mixing and evaporation occur. The resulting vaporized fuel/inert gas mixture (at about 800.degree. F., preferably) is then ducted and distributed to the individual main combustor fuel injectors where it is injected into the premixing ducts.

Abstract: A piloting fuel injector assembly for a supersonic ramjet engine has a cowl 24, 70 confining a pilot air portion of the airstream. A conical member 34, 74 produces a subsonic recirculation zone 30, 76 and a shock wave falling within the cowl. Pilot fuel injected 40, 82 upstream of the recirculation zone burns stoichiometrically. The exhaust 38, 86 from the cowl is sonic, producing a shock wave which facilitates ignition of the main fuel injected 46, 84 upstream of the cowl exhaust.

Abstract: A thruster system has a main bipropellant propulsion unit including a propulsion engine (50) and bipropellant supply having a tank (3) for an oxidizing agent and a tank (4) for a fuel. An auxiliary cold propellant thruster (21) uses propellant supplied by bleeding off vapor from the contents of the oxidizing agent tank (3).

Abstract: A three fluid heat exchanger in which first (fuel) and second (oil) fluids are in a normally flowing heat transfer relation, with flow of a third fluid (compressor bleed air) being dependent on a changing condition of one of the first or second fluids. Tubular heat exchanger cores are comprised in a unitary body with one being perpendicular to the other for space conservation and to simplify fluid flow patterns. The described one core is in the path of flow of one of the first or second fluids and provides a flow path for the third fluid. A valve influenced by a changing pressure condition of one of the first and second fluids controls flow of the third fluid.

Abstract: An arrangement that uses aircraft fuel as a heat sink for aircraft auxiliary oil systems for an aircraft having at least one engine operated by fuel and having an engine interface limit and including a fuel/oil heat exchanger for removing heat from the aircraft auxiliary oil systems and having a fuel outlet temperature, a temperature sensing for determining temperature of the fuel leaving the fuel/oil heat exchanger, a recirculating flow control valve having variable positions including an open and a closed position controlled by the temperature sensor, the fuel always going to the aircraft engine but also going through the flow control valve when the flow control valve is in the open position so that recirculation is minimized and maximum heat is rejected to the engine by the fuel outlet temperature of the fuel/oil heat exchanger when the fuel outlet temperature of the fuel/oil heat exchanger is controlled by the engine interface limit, a ram air heat exchanger for removing heat from the fuel leaving the rec

Abstract: A heat management system is provided for a gas turbine engine (10) having first and second oil cooling loops (14, 16). The system distributes excess fuel flow from a main fuel pump (44) among a plurality of upstream locations (58, 60, 68) for managing the transfer of heat between the oil loops (14, 16) and the flowing fuel. A diverter valve (62) regulates the distribution of the bypass fuel responsive to engine heat generation, oil temperature, and/or fuel temperature. A passive fuel distribution configuration using one or more fuel flow restrictors (72, 74, 76) is also disclosed.

Abstract: Snap-action operation of a servo diverter valve (70) and an associated pressure responsive switch (115) is achieved by controlling the pressurization and depressurization of the valve with a nozzle (140) operated by a pressure responsive bellows actuator (160) disposed in a chamber 145 having a flow restrictor 220 in an outlet thereof.

Abstract: An improvement in the design of a staged-combustion-cycle rocket engine. The preburner 16 (or preburners) is operated at a higher temperature than that above which turbine blades will be damaged. A heat-exchanger unit 40 through which the output flow of the cooling jacket 18 of the engine is passed is placed inside the preburners 16, or in close proximity to its output flow, so that heat energy is transferred from the output flow of the preburners 16 to the output flow of the cooling jacket 18. This lowers the preburners output flow to a temperature which will not damage turbine blades and raises the cooling-jacket output flow temperature. Since the output flow of the cooling jacket 18 is fed to the low-pressure turbines 22, the increased temperature raises the pressure of the low-pressure turbines 22 so that their output of flow rate is increased and the flow rate to the engine is increased, thereby increasing engine output power and efficiency.

Abstract: An energy recovery system is provided for an aircraft gas turbine engine of the type in which some of the pneumatic energy developed by the engine is made available to support systems such as an environmental control system. In one such energy recovery system, some of the pneumatic energy made available to but not utilized by the support system is utilized to heat the engine fuel immediately prior to the consumption of the fuel by the engine. Some of the recovered energy may also be utilized to heat the fuel in the fuel tanks. Provision is made for multi-engine applications wherein energy recovered from one engine may be utilized by another one of the engines or systems associated therewith.

Abstract: A novel heat management system for aircraft is provided which is based on the aircraft fuel as the heat exchange medium and comprises a dedicated thermal reserve fuel tank for containing refrigerated aircraft fuel (or other expendable liquid) which is cooled by heat exchange with the primary aircraft fuel flow to the engines, a fuel line loop for conducting fuel through a plurality of heat exchangers associated with cooling loops for heat generating aircraft systems, and a central microprocessor based controller for controlling fuel flow and temperature throughout the fuel loop system and into the aircraft engine.

Abstract: A fuel combustor consists of an elongated casing 16 with an air inlet conduit portion 27 at one end, and having an opposite exit end 18. The casing is formed with an intermediate combustion space 19. An elongated heat pipe 29 is mounted longitudinally in the casing and is offset from and extends alongside the combustion space 19. The heat pipe 29 is in heat-transmitting relationship with the air intake conduit 27 for heating incoming air. Guide conduit structure 25 is provided for conveying the heated air from the intake conduit into the combustion space. A fuel discharge nozzle 26 is provided to inject fuel into the combustion space 19. A fuel conduit 32 from a fuel supply source 37 has a portion 33 engaged in heat transfer relationship of the heat pipe for preheating the fuel. The downstream end of the heat pipe 29 is in heat transfer relationship with the casing and is located adjacent to the downstream end of the combustion space.

Abstract: A turbine engine having a combustor premix system for mixing fuel and air to provide increased efficiency by reducing temperature peaks in the combustor. The system includes a primary mixing chamber for mixing compressed air and atomized fuel and a secondary mixing chamber located between the primary mixing chamber and the combustor for mixing additional compressed air to the fuel-air mixture. The secondary mixing chamber comprises a plurality of tubes with air metering ports in the walls thereof and a control assembly to vary the air flow to the ports for off design engine operating conditions, and optimizes fuel-air mixtures for the combustor at all engine operating speeds improving fuel economy and exhaust pollution control. The primary mixing chamber is located adjacent to and between the compressor for the air and the combustor so that the fuel-air mixture flowing therethrough tends to cool the compressor and the chamber itself shields the compressor from radiant heat from the combustor.

Abstract: A system and method provides for burning wood particles or other combustible fibrous particles at a continuous high rate in which the particles are at least partially pyrolyzed as they are being fed into a combustion chamber, complete combustion of the particles and pyrolysis products occuring within the combustion chamber. Pyrolysis is enabled by mixing the particles with air having a temperature of at least 600.degree. F. The system enables the burning of green wood in existing large boiler systems as well as in gas turbine systems; the latter operatable with a high pressure combustion chamber. In a boiler system, air for pyrolysis of the particles may be heated by the boiler, in a turbine system, air for pyrolysis of the particles may be heated by a compressor driven by a turbine.

Abstract: A gas turbine utilizing the spontaneous ignition of preheated fuel, said gas turbine including a series of combustion chambers supplied with fuel from pumping and preheating subassemblies.

Abstract: To accommodate fuel having higher freezing points the continuous bypass flow of fuel from the fuel control is selectively diverted to pick up the rejected heat from the engine's lubrication system to heat the fuel in the aircraft fuel tank.

Abstract: A gas turbine engine is disclosed which has an integral steam power system consisting of heat absorbing boilers which convert an unpressurized liquid into an expanded and heated steam by utilizing heat normally lost through component cooling systems and the exhaust system. Upon completion of the steam power cycle, the steam is condensed back to a liquid state through a condensing system located within the compressor and other functional components of the gas turbine engine. A system of high pressure air and friction seals restrict steam or liquid condensate within designed flow bounds. The gas turbine engine disclosed is designed to give improved fuel efficiency and economy for aircraft and land use applications.

Abstract: This invention relates to improvements in the art of liquid fuel combustion and, more particularly, concerns a method and apparatus for the controlled gassification of liquid fuels, the thorough premixing of the then gassified fuel with air and the subsequent gas-phase combustion of the mixture to produce a flame substantially free of soot, carbon monoxide, nitric oxide and unburned fuel.