Abstract: The present invention relates to a hot gas recovery boiler comprising a substantially horizontal gas inlet duct, a gas deflection duct connected to the inlet duct and opening out into a generally vertical enclosure that contains a set of superposed and substantially horizontal heat exchange stages plus a flue gas exhaust duct at the top of the enclosure. At least one heat exchanger is disposed in the proximity of the outlet of said inlet duct.

Abstract: A hydrostatic rotary power transmission system that provides a stable rotation rate at very slow rotation speeds is provided. The system operates in two speed control modes, one being a normal mode for use in the rotation rate range of 50 rpm to the maximum rated speed and a second or fine speed control mode for use in the rotation range of <1.0 to 250 rpm. In the normal control mode, the rotation speed is a function of the displacement of the hydrostatic pump. In the fine speed control mode, the motor rotation rate is a function of the flow rate through a proportional-flow valve that is downstream of the motor.

Abstract: A low noise power plant (100) for providing thrust to a missile (102) having a solid fuel propellant (104) for generating a pressurized gas. A turbine (106) converts the pressurized gas to rotary motion and a drive shaft (108) transfers the rotary motion to a load (110). In a preferred embodiment, the power plant (100) is utilized to drive a projectile (102). A solid fuel stick (104) located within a combustion chamber (112) is ignited and burned to provide pressurized gas which is directed to the turbine (106) via an exhaust tube (114). The pressurized gas is at a relatively low pressure and volume which minimizes the generation of noise. The turbine (106) and the drive shaft (108) are each rotated by the pressurized gas. The gases expelled from the turbine (106) are near atmospheric pressure which further minimizes the generation of noise. The power of the rotating drive shaft (108) can be converted to useful power by a speed reduction gearbox (140).

Abstract: An industrial gas turbine engine includes in serial flow relationship a booster compressor, core engine, power turbine, and flow channel, with the power turbine having a first shaft, joined to the booster compressor, and an output shaft, and the flow channel having an outlet. Means for selectively varying flow area of the channel outlet are provided for controlling stall margin of the booster compressor in an exemplary embodiment of the engine and method of operation. The flow area varying means is effective for providing a minimum area of the channel outlet for controlling booster compressor stall margin at least at a synchronous speed associated with powering an electrical generator. In one embodiment, the flow area varying means effects a minimum horsepower from the output shaft for allowing lock-on and lock-off of the electrical generator at synchronous speed.

Abstract: An improved exhaust gas NO.sub.x removal system removes NO.sub.x from exhaust gas through a catalytic reduction process making use of ammonia or its precursor as a reducing agent. The system includes a vaporizer in which ammonia or its precursor is vaporized, and one or a plurality of nozzles provided in a flue upstream of an NO.sub.x removal catalyst layer. The number of nozzles corresponds to a cross-sectional area of the same flue. These nozzles eject the ammonia or its precursor, vaporized by superheated steam within the vaporizer, into the flue. The superheated steam to be used in the vaporizer for evaporating ammonia or its precursor can be taken from the exhaust gas boiler itself in which NO.sub.x removal is to be effected.

Abstract: A mixture of urea, ammonia, and water is injected into the exhaust of jet engines to lower the amount of NO.sub.x emitted from jet engines.

Abstract: An exhaust system for a gas turbine has a main axial duct which feeds a heat exchanger to make use of the residual heat in the exhaust gases. The heat exchanger may in some circumstances be overloaded so a branch duct is taken from the main duct conventionally by means of a T-junction with a flap valve closing off either the main (axial) outlet or the branch outlet. The branch duct is then taken to an exhaust stack. Turbulence at the T-junction causes poor flow upstream of the junction and corresponding poor turbine performance. The invention provides a junction in which the main axial duct (1) passes smoothly through a bypass chamber (15) which surrounds the axial duct (1). Slots (17) in the axial duct within the chamber (15) permit passage of the exhaust gases to the bypass duct (19). Rotating blade valves (13 and 23) in the two duct outlets control the relative flow of exhaust to heat exchanger and exhaust stack.

Abstract: A method for reducing nitrogen oxide emissions of a gas turbine includes supplying a working medium produced in a combustion chamber with admixture of compressed air to a gas turbine, supplying a coolant to the gas turbine, and admixing a reducing agent with the coolant to reduce nitrogen oxides. A gas turbine plant includes a gas turbine, a combustion chamber connected upstream of the gas turbine, a compressor connected upstream of the combustion chamber, and a coolant line for delivering coolant to the gas turbine. A reducing agent is admixed with the coolant in the gas turbine for reducing nitrogen oxides.

Abstract: There is described a method and apparatus for reducing the infrared emissions from a tail-pipe section of a jet engine. The apparatus consists of a plurality of overlapping hollow panels each having a truncated cone shape supplied with a liquid coolant such that the coolant absorbs heat from the surfaces of the panels and converts the liquid to a vapor. The vapor created by this heat absorption is injected from an end opening of a panel between the panels and the exhaust gases of the jet engine to form a boundary layer. Surrounding the panels is an outer cowling defining a chamber with the overlapping panels and containing a liquid coolant.

Abstract: Combustion in a gas turbine is controlled through use of flame spectroscopy in order to achieve low NO.sub.x emissions in the exhaust. By monitoring the combustion flame in the turbine to determine intensity of non-infrared spectral lines, and dynamically adjusting the fuel/air ratio of the fuel mixture such that this intensity remains below a predetermined level associated with a desired low level of NO.sub.x emissions, the engine produces significantly reduced NO.sub.x emissions in its exhaust but at a sufficiently high combustion flame temperature to avoid any undue risk of flame-out, thereby assuring stable, safe and reliable operation.

Abstract: An arrangement to mask direct view of the discharge end of a turbine through an exhaust duct extending downstream from the turbine. The turbine has an annular outlet. Two annular rows of fixed vanes are mounted in the outlet, one immediately upstream of the other. The two sets of vanes are reversely cambered so that the overall turning effect is insignificant and they are so located that each set of vanes blocks sight of the turbine through the gaps between the vanes of the other set.

Abstract: During low-load operating conditions, preburner combustion products are supplied with a chemical reactant to reduce NO.sub.x. The preburner products of combustion are mixed with a hydrocarbon fuel in the presence of a combustion catalyst to ignite and initiate a catalytic combustion reaction. The preburner is then shut down. The fuel/air mixture supplied the catalytic reactor bed during the mid-load operating range of the turbine is sufficiently lean to produce a combustion reaction temperature too low to produce thermal NO.sub.x. Thus, at low-load conditions, preburner combustion occurs with NO.sub.x reduction by chemical reactant, while the catalytic combustion occurs at mid-range operating conditions at temperatures too low to produce NO.sub.x. For high-load operating conditions, the catalytic combustion occurs as previously described and additional lean fuel/air mixture is supplied the reaction zone whereby thermal NO.sub.x is likewise avoided.

Abstract: Improvements to diesel power hammers which allow the hammers to be operated smokelessly are disclosed. Kerosene and synthetic oil replace diesel fuel and mineral oil as fuel and lubricant, respectively, in hammers incorporating prior art design improvements by Makers thereof. Other combustibles such as gasoline may be added to the kerosene fuel to improve the quality of combustion and thereby further reduce the emission of smoke.

Abstract: A method and apparatus for recovering energy from a wet oxidation products stream flow includes channeling the stream flow to an energy recovery assembly (10). The assembly (10) includes a rotatable reaction barrel (32). The reaction barrel (32) is provided with a plurality of rocket nozzles (41). The stream flow is channeled to and expelled through the rocket nozzles (41), thus causing the reactor barrel (32) to rotate. Rotational energy is transferred from the reactor barrel (32) to a generator (43) where electrical power is produced.

Abstract: In order to reduce turbine engine exhaust noise while simultaneously reducing anti-surge airflow noise, a combination noise reduction apparatus or tube (10) is provided having a series of holes (26) in its side. The tube (10) is in communication with a source of anti-surge air through an anti-surge air outlet (22) to be delivered into the exhaust airflow in an exhaust duct (12). The tube (10) diffuses the anti-surge air, shields the noise of the anti-surge air by dissipating the acoustic energy within the tube (10), and provides for an even distribution of the anti-surge air into the exhaust airflow. As a result, a temperature discontinuity is created in the exhaust duct (12) which results in an acoustic impedance that reflects acoustic noise back to the source of the noise.

Abstract: This disclosure describes an arrangement for cooling the exhaust nozzle of a gas turbine engine by selectively diverting the unheated total engine air flow directly to the exhaust nozzle of the engine. After the total air flow impinges on the back surface of the exhaust nozzle to rapidly cool the nozzle, the air is redirected back to the fan and the core engine for supporting combustion and to provide cooling in a generally conventional manner.

Abstract: A process for low NOX cogeneration to produce electricity and heat which involves combusting fuel to produce a gaseous stream of combustion products, passing the gaseous stream through a turbine to generate electricity, and to produce a gaseous exhaust stream, adding additional fuel to the exhaust stream, to provide a gas stream having fuel in excess of the oxygen in the fuel-rich gas stream, catalytically treating the gas stream in a reducing atmosphere to produce a treated gaseous stream, converting at least a portion of the heat in the treated stream into steam, adding air to the treated stream to produce a stoichiometric excess of oxygen in the resultant stream relative to fuel present in the resultant stream, passing the resultant stream over an oxidizing catalyst to produce an oxidized gaseous stream, removing heat from the oxidized stream, and venting the resultant cooled stream. An apparatus system for carrying out this process is also provided.

Abstract: A combined gas turbine plant comprises an air compressor, a combustor including a combustion chamber, a gas turbine, a steam turbine, and an exhaust heat recovery device having a denitration device and arranged at a location through which an exhaust gas passage for leading exhaust gas from the gas turbine to the atmosphere extends. An air extraction pipe equipped with a valve is provided for extracting a part of the air from the air compressor to prevent surging of the air compressor during starting of the plant, and another air extraction pipe equipped with a valve is provided for extracting a part of the air from an air passage extending from the compressor to the combustion chamber to improve stability of a flame and combustibility in the combustion chamber during the plant starting. The extraction pipes extend to and hence lead the extracted air into a portion of the exhaust gas passage located downstream of the denitration device.

Abstract: An exhaust system having a protective arrangement includes a plurality of spaced overlapping inclined armor plate blockers providing a ballistic shield over the entire exhaust area. A louvered grate is provided extending between the tops of the blockers to permit egress of gases from the engine but to block destructive elements from being thrown into the interior of an engine. Cooling air is supplied to the blockers and is caused to move along a path which carries it across the surfaces of the blockers so as to materially reduce the temperature of these surfaces. Further, this cooling air is directed not only over surfaces of the blockers which are directly visible externally of the vehicle, but also over a surface which, while not directly visible from the exterior of the vehicle, is a potential source of reflected heat which could be sensed exteriorly of the vehicle.

Abstract: An exhaust nozzle extends from an engine nacelle and has an opening disposed at an acute angle such that the exhaust stream is blown over a length of the propeller blade. The opening has a plurality of guide vanes disposed therein to shape the exhaust stream most effectively. By spreading the exhaust stream over the length of a propeller, mixing of the exhaust stream with ambient air is maximized, thereby lowering the temperature of the exhaust stream to tolerable levels.

Abstract: A structure and method for sensing oxides of nitrogen in a gas. The gas is first passed through an oxidation catalyst and any reducing species in the gas are oxidized. The output gas from the oxidation catalyst is received by a sensor which generates an output responsive to oxides of nitrogen because the sensor has been isolated from any reducing species in the gas.

Abstract: In a gas turbine process in which hot moist gas produced by combusting natural gas and injecting steam to the combustion device, the relative moisture content of the gas is reduced after the turbine by adiabatic absorption by means of an absorbent liquid the only evaporating component of which is water. The condensation heat of the aqueous steam condensed in the absorption is to a large extent conveyed to the gas the temperature of which is thereby raised. The heat is recovered by known methods for use e.g. in district heating. The diluted absorbent liquid is regenerated for example by arranging it in the heat recovery stage before the absorption in indirect heat exchange contact with the gas.

Abstract: A process for low NOX cogeneration to produce electricity and heat which involves combusting fuel to produce a gaseous stream of combustion products, passing the gaseous stream through a turbine to generate electricity, and to produce a gaseous exhaust stream, adding additional fuel to the exhaust stream, to provide a combustible gas stream having fuel in excess of the oxygen in the combustible gas stream, combusting the combustible gas stream in a reducing atmosphere to produce a heated oxygen-depleted gaseous stream, converting at least a portion of the heat in the oxygen depleted stream into steam, adding air to the oxygen-depleted stream to produce a stoichiometric excess of oxygen in the resultant stream relative to fuel present in the resultant stream, passing the resultant stream over an oxidizing catalyst to produce an oxidized gaseous stream, removing heat from the oxidized stream, and venting the resultant cooled stream. An apparatus system for carrying out this process is also provided.

Abstract: Successful flight of high altitude military aircraft is dependent, in part, pon the ability of the aircraft to remain undetected during flight. Against the highly sophisticated infrared sensors developed during recent years, particularly for miliary use, an aircraft powered by a gas turbine engine is at a particular disadvantage. Hence infrared emissions from gas turbine engines have been reduced by use of a variety of infrared radiation (IR) suppressor designs. But in these designs aerodynamic problems are difficult to analyze and geometrical parameters are very critical, and nearly impossible to maintain. The IR suppressor herein provides the best blend of simple aerodynamics, heat transfer, and geometry.

Abstract: A power recovery expander for use with a motive fluid of hot gas with entrained particulates is disclosed. Means for removal of entrained particulates and for cooling portions of the turbomachine are provided. Additionally, cooling fluid is directed to a separate cooling chamber, said cooling fluid being used to draw additional particulate matters from the motive fluid.

Abstract: In a chemical process plant or the like, of the type having a gas turbine driven compressor and a fired heater for heating the process medium, and of the type which hitherto used the exhaust (GTE) of one or more gas turbines as an oxidizing medium input for oxidizing the fuel in the radiant section of the fired heater, the GTE is instead now diverted from the radiant section to a heat exchanger and air at substantially atmospheric pressure and ambient temperature is forced through the heat exchanger by a fan so as to be heated by the heat energy derived from the GTE and is then fed to the said oxidizing medium input of the heater radiant section. The GTE which has passed through the heat exchanger is exhausted to atmosphere.

Abstract: A gas turbine exhaust device installed at the outlet from the guide vane stage (5) of the turbine and upstream from an exhaust duct (10), said device comprising a jet diffuser (20) having orifices (25) perforated therethrough, with the axis of the diffuser being the same as the axis of the turbine.

Abstract: A power plant with combustion of a fuel in a fluidized bed (14) enclosed within a combustion chamber in a bed vessel (11). A gas outlet from the bed vessel (11) is formed as a centrifugal separator (20) intended to primarily separate coarse material containing unburnt fuel leaving the bed (11) together with the combustion gases. Suitably the separator (20) extends into the bed vessel (11) and separated material is returned to the bed (14) through a return conduit (34), which is preferably located close to the bed vessel wall. This conduit (34) opens into the bed vessel (11), near the bottom (12) thereof. For the return transport an ejector (35) may be used to overcome the pressure difference existing between the separator (20) and the orifice of the conveying conduit (34). The propellent gas may consist of combustion air from the space (16).

Abstract: A pressurized cyclonic combustion method and a cylindrical burner apparatus for pressurized combustion of particulate solid fuels to produce a pressurized clean effluent gas. In the burner, the particulate solids such as wood chips are fed tangentially into a primary combustion chamber at its inlet end and flow at high tangential velocity in a helical path through the burner. Oxygen-containing combustion gas such as air is supplied tangentially at high velocity through multiple ports spaced along the burner length to maintain and/or increase the high tangential velocity and produce high centrifugal forces on the particulate solids and provide for prolonged combustion and produce high burner volumetric heat release rates exceeding about 400,000 Btu/hr ft.sup.3. A choke opening is provided centrally located at the combustion chamber outlet end for promoting prolonged combustion of solid fuel particles upstream of a quench zone. A secondary combustion chamber is provided downstream of the choke opening.

Abstract: A helicopter with a turbine power unit on which fluid flow from the turbine exhaust nozzle, from a turbine bypass duct, from a duct communicating with the compartment housing the turbine engine, and from one or more ducts for cooling internal parts on the helicopter, converges inside a single manifold the output of which is connected to the input of a tubular screening device extending outwards from the manifold and provided with tubular transverse wing contours communicating externally and arranged in such a manner as to prevent the turbine exhaust nozzle from being directly visible from outside, and in such a manner as to define a number of ejectors for activating the fluid streams converging inside the manifold, and for mixing them together with outside air.

Abstract: A waste heat recovery boiler for a turbine including two denitrating devices disposed in the boiler to reduce the NOx concentration in an exhaust gas below a pre-determined value even when a turbine load changes. The overall denitration efficiency distribution of the boiler with respect to the turbine load can be set arbitrarily by selecting suitable positions of the denitrating devices and the amounts of a catalyst, and any adverse effects resulting from the change of the turbine load can be avoided.

Abstract: Disclosed is a method for non-catalytically reducing the amount of NO emitted from gas turbines. The method involves contacting condition effluents of the gas turbine with ammonia, replacing at least a portion of the secondary air used to dilute and cool the combustion effluents with an inert gas, such as exhaust gas from the gas turine. The temperature of the combustion effluents, the time between contacting the combustion effluents with ammonia and passage through the turbine blades, and the amount of ammonia employed is determined by the solution of the set of simultaneous equations derived from the kinetic model disclosed herein.

Abstract: A working vehicle having a working device mounted on a swivel base rotated by a hydraulic motor. There is provided a control system which causes the swivel base to start and stop smoothly at highest possible standard speeds which are preset for an entire swivelling range.

Abstract: The assembly comprises a collector nozzle which is fixed to a turbine engine and which is elbowed laterally towards the exterior and which debouches into injection nozzles which are also elbowed and which open into a mixer masked laterally by means of a fairing, of which a shaped forward section defines, with an internal shaped screen and a central plug, a semi dynamic principal air inlet. The aspirated air dilutes the gas in the mixer which is terminated by means of an elbow directed upwardly and which can pivot about a transverse axis. In the position of maximum deviation upwardly this elbow masks the hot parts of the assembly from the rear. The assembly is particularly useful for equipping helicopters with lateral exhaust gas turbine engines, and it can be original equipment or retrofitted. The assembly serves to reduce the infra red emission from the helicopter, to defeat infra red homing missiles.

Abstract: Engine monitor/control microprocessor primarily effective to automatically adjust the engine power setting in a transmission power train in which the transmission drive reduction is variable in ratio, by step change or continuously so, such as for use in farm tractors. The microprocessor adjusts the position of the setting so that engine power set at all levels is produced at the right brake specific fuel consumption for substantially minimum pounds of fuel per horsepower hour, or within a band width thereof if not all that sensitive. Preferably, the microprocessor has a higher priority primary function of also automatically adjusting the transmission drive reduction ratio, for the same purpose but with high sensitivity.

Abstract: A constant speed hydraulic drive comprising a variable displacement hydraulic pump controlled to maintain a constant flow of hydraulic fluid even though a prime mover therefor is subject to speed variations. The constant flow rate delivered by the hydraulic pump is at a rate sufficient to drive a load hydraulic motor at a predetermined speed when the load hydraulic motor is subject to any given load. A pilot operated relief valve proportionally bleeds hydraulic fluid from ahead of the hydraulic motor in accordance with the speed and load of the hydraulic motor.

Abstract: An exhaust pipe outlet is surrounded by a jacket part having an inlet of ger diameter, permitting air to be drawn into the jacket part to isolate it from contact with the hot exhaust gases. Blocking air may be injected at the downstream end of the jacket part.

Abstract: A method of reducing the visible flash caused from afterburning of a rocket otor by injecting a fire extinguishing suppressant material into the exhaust gases from the rocket motor and injecting the fire extinguishing suppressant material near the exhaust end of the rocket motor nozzle and about an internal periphery of the exhaust nozzle. An effective fire extinguisher suppressant includes fluoro halogenated carbon compounds and specifically CBrF.sub.3.

Abstract: In a coal-fired combined plant, finely powdered coal is burned at high temperature in a pressurized coal-melting combustion furnace to obtain combustion gas substantially free of dust to drive a gas turbine in order to generate electric power. Waste gas from the gas turbine is used to produce steam which drives a steam turbine for additional electric power generation. Primary dust removal from the combustion gas is carried out by removing most of the resulting coal ash in a molten state. In a secondary dust removal, the dust is removed from the combustion gas by a cyclone disposed in the combustion furnace. In a tertiary dust removal, the dust is removed from the combustion gas which is discharged through an outlet at the combustion furnace by a precision dust-removing device.

Abstract: A gas turbine engine infra-red radiation suppressor comprising an exhaust nozzle which is surrounded by a duct having a plurality of diffuser vanes at its downstream end. The exhaust nozzle and duct constitute an ejector which is powered by the exhaust efflux from the exhaust nozzle and draws ambient air into the duct through a gap between the exhaust nozzle and the duct. The air serves to cool the exhaust efflux and thereby reduce its infra-red radiation emission, and the diffuser vanes prevent direct line of sight of the hot exhaust nozzle.

Abstract: A heat recovery system for supplementing the exhaust mass flow from a gas turbine with additional flow of preheated air to provide greater steam output from a heat recovery unit such as a steam generator. The supplemental preheated air is ambient ventilation air which is used to cool the outer enclosure of the gas turbine. A diverter valve is employed to selectively add to the mass flow from the gas turbine any appropriate mass flow of the ventilation air between zero and a maximum amount. An eductor may be used to aid a blower for moving the supplemental air. A duct burner upstream from the heat recovery unit is employed to raise the temperature of a mixture of turbine exhaust gases and ventilation air being supplied to the heat recovery unit. In a similar fashion, supplemental preheated air may be taken from air used for cooling a generator or other primary load being driven by the gas turbine.

Abstract: Jet propulsion powerplant comprising a gas producer 11 having a first flow duct 12 for receiving the output of the gas producer 11. The flow duct 12 includes a nozzle 13 having a center body 16 which has an upstream part 17 and a downstream part 20. Motors 22 are provided for expanding and contracting the downstream part 20 relative to the upstream part 17. A second flow duct 33 having an inlet 30 openable to airflow and connected to the interior of said upstream part 17 is provided. An outlet 24 from the interior of the upstream part 17, is provided at the downstream end of the upstream part 17. The outlet 24 opens into the interior of the first flow duct 12 by contracting the downstream part 20 relative to the upstream part 17. By such an arrangement, infrared radiation may be suppressed when necessary by opening the inlet for air flow and controlling the upstream and downstream parts so that there can be a mixing of air with exhaust gases which reduces the mean temperature of the exhaust gases.

Abstract: Aircraft engine exhaust is mixed with air and fuel and recombusted. Air is drawn into the secondary combustion chamber from suction surfaces on wings. Exhaust of the secondary combustion chamber is blown over wing and fuselage surfaces.

Abstract: A shipboard engine system and method of operating includes two compressors with an intercooler, a compressor turbine, a power turbine, a combustor for combining fuel, air and water. Heat exchangers remove heat from the exhaust and use it to preheat the water to the combustor. Spray condensers recover water from the exhaust for reuse. Water purification apparatus is used to remove acid from the water. The system is designed for stoichiometric operation at full load and run with increased efficiency at part load to give a total lower fuel consumption.

Abstract: To limit the power output of a hydraulic assembly consisting of plural driven hydraulic motors, hydraulic pumps driving said motors, a single pump driving motor and control means for controlling the hydraulic flow to said drive hydraulic motors, a controller is provided which is supplied with an input signal from a subtractor which in turn is supplied with signals from a reference value setting device and an actual value setting device, the actual value setting device sensing the speed of the driving motor. An output signal of the controller is applied to all of the control means and is multiplied in each control means by a signal proportional to the setting of said control means, in order to obtain the flow control signal.

Abstract: A waste heat recovery boiler for generating steam by utilizing a flue gas discharged from a gas turbine as a heat source comprises an economizer for preheating feedwater by the flue gas, an evaporator for evaporating the preheated feedwater, and a superheater for generating a steam for driving a steam prime mover by heating the evaporated feedwater. The economizer, the evaporator and the superheater are successively arranged in the direction from a downstream side to an upstream side of flue gas passage. The evaporator itself is divided into two sections and an apparatus for removing NO.sub.x is provided in a space between the divided two sections of the evaporator in the flue gas passage to remove NO.sub.x from the flue gas. An NO.sub.x concentration of a flue gas discharged from a combined cycle power plant including the gas turbine can be stably abated at any of full and partial loads.

Abstract: An arrangement for the protection of vehicles against IR-IMAGING equipment by cooling air, in which the hot or warm exhaust gases are surrounded by a laminar flow of cooling air. The outside air which is drawn in by the cooling mechanism or the motor ventilation system, is first moved over the thermally radiating areas of the vehicle, and then to the cooling unit or the motor itself for combustion. Part of the outside air which is drawn in, serves as the laminar cover stream of the transferred heated-up cooling air and/or the exhaust gases. These exhaust gases, the heated up cooling air and the surrounding outside air represents a coaxial system of gas flows. In the center of this system, flow the exhaust gases, and the heated-up cooling air flows in the central annular portion. The outside air is directed through the outside annular flow portion of the coaxial system.

Abstract: In a fluid flow machine comprising a compressor including a compressor diffuser and a turbine including an exhaust gas diffuser compressed air from boundary layers or vortex flows in the compressor diffuser, or leakage air from the compressor, is bled off and used as a driving medium for removing exhaust gas from boundary layers or vortex flows in the exhaust gas diffuser. Since the pressure of the exhaust gas to be removed from the exhaust gas diffuser is below the ambient pressure a suction has to be established to remove the desired gas from the boundary layers or vortex flows. This suction is established by an ejector or a pump which is driven by the energy of the compressed air bled from the compressor regions.

Abstract: A hybrid propulsion system particularly for automotive application including a subambient pressure cycle gas turbine engine having a primary turbine-compressor rotor assembly connected to a load shaft and a secondary turbine-compressor rotor assembly gas coupled with the primary rotor assembly, a flywheel rotatable with the secondary rotor assembly, and variable geometry nozzles at the turbines operative during engine operation at a steady state power output level to effect partial motive fluid expansion at the primary turbine to drive the load and the primary compressor and partial motive fluid expansion at the secondary turbine to drive the secondary compressor which maintains subambient pressure and during engine operation at a peak power output level to effect substantially total motive fluid expansion across only the primary turbine for increased power at the load shaft, the flywheel being operative during peak power level operation to drive the secondary compressor to maintain total motive fluid expansi

Abstract: The temperature of heated exhaust gases from a gas turbine is increased to value sufficient to vaporize fog oil to form smoke. The turbine itself is unmodified and requires no bleed air control valve at the air inlet to the compressor to regulate exhaust gas temperature.