Abstract: A multi-stage method and apparatus for cooling the inlet air of internal combustion engine and gas turbine prime movers with various load applications comprising: generating and providing a multi-stage refrigerated cooling system associated with the air inlet of internal combustion engine and gas turbine prime movers which provides thermodynamic efficiencies in accordance with a divided psychrometric inlet air cooling path enthalpy curve; cascading the cooled refrigerant from a first cooling stage as the liquid feed into a subsequent lower temperature cooling stage for cooling to the desired temperature; energizing power means to drive the prime mover and refrigerant cooling system; and adjusting the power means based on current energy costs to optimize net revenues to produce electricity or useful work from the prime mover application.

Abstract: A method for temperature control of an air supply in PFBC plants which comprise a low-pressure unit including a low-pressure compressor and a low-pressure turbine, a high-pressure unit including a high-pressure compressor and a high-pressure turbine, wherein air is sucked into the low-pressure compressor whereupon the air is passed via an intermediate cooler, which is traversed by water, into the high-pressure compressor and then into a boiler of the plant. The method includes measuring in a temperature control system a temperature of the air both upstream and downstream of the high-pressure compressor, comparing the two measured temperature values and corresponding set values for the respective upstream and downstream temperature, and activating, based only on one of the comparisons, a shunt valve of an intermediate cooler. The control signal of the shunt valve consists of the output signal from the temperature control system.

Abstract: Disclosed herein is a method of firing a gas turbine with LNG which is designed to store the "cold" of LNG in an the LNG vaporizer.

Abstract: The invention relates to a method for operating a turbocompressor (12) having at least two compressor stages and a cooler (14) to which water is applied as coolant, the heated cooling water having a pressure exceeding the saturation pressure, with the result that said cooling water is partially evaporated in an evaporation vessel (30) at an intermediate pressure level less than the saturation pressure. The steam thus produced evacuates by means of an ejector (34) a second evaporation vessel (32), in which a proportion of the residual water of the first vessel (30) is, in turn, evaporated and the remaining water is cooled below 100.degree. C.

Abstract: The present invention is an improvement to a process for the production of work to generate electricity or to drive a mechanical device using a gas turbine. In the process, feed air stream is compressed and combusted with a fuel gas to produce a combustion product. This combustion product is expanded in a gas turbine expander, thereby producing a hot exhaust gas and work. This produced work is used to generate electricity or to drive a mechanical device. The improvement to the process, which increases the work produced by the gas turbine expander, is characterized by cooling nitrogen product, produced by a cryogenic air separation unit to a subambient temperature and combining this subambient cooled, nitrogen product with the feed air stream prior to compression.

Abstract: A method and apparatus for a combined turbine installation includes a gas turbine group with a compressor having a water cooler, a combustion chamber and a gas turbine, and having a steam turbine installation with a waste heat boiler heated by the exhaust gas from the gas turbine. The waste heat boiler includes an evaporator, drum, enconomizer and superheater, a steam turbine downstream of the waste heat boiler and a combined feed water tank/flash evaporator unit. The feed water tank/flash evaporator is supplied with condensate from a condenser fitted downstream of the steam turbine. Cooling water heated by the compressed air is evaporated in at least one state and the steam produced is fed to the waste heat boiler for further heating, or directly to the steam turbine. In addition, the unevaporated residual water is fed to the feed water tank/flash evaporation unit, and after mixing with the condensate from the steam turbine, is supplied to the compressor cooler.

Abstract: An improved power plant employing a combination of compressed air storage and saturation (simultaneous heating and humidification) of compressed air is disclosed. The power plant includes a combustor which provides hot gas for driving a turbine. The turbine is used in conjunction with a generator to generate electrical power. The power from the turbine is accessible by a compressor system during low power demand periods. The compressor system is used to compress air which is stored in an air storage chamber. The compressed air from the air storage chamber is used by the combustor during high power demand periods, while the compressor system is shut down, to provide compressed combustion gas to the turbine. To enhance the efficiency of the plant, while further lowering the capital cost of the plant, a saturator is positioned between the storage chamber and the combustor. The saturator receives compressed air from the storage chamber and simultaneously heats and humidifies it.

Abstract: An improved technique is disclosed for a combustion-based power generation system that includes a combustion chamber having an exhaust, a source of input air for the combustion chamber, a source of fuel for the combustion chamber, and a turbine and generator communicating with the combustion chamber for obtaining power from the combustion. The method includes the steps of: heating and humidifying the input air; sensing a condition of the heated and humidified input air, and generating a control signal in response to the sensed condition; and cooling the heated and humidified input air before it is input to the combustion chamber. Humidified input air that is at too high a temperature, or which is not saturated, is sensed, and appropriate trim cooling is provided to obtain the desired condition for the humidified input air. In this manner, maximum humidification is achieved while avoiding overheating and maintaining operating temperature in a desired range.

Abstract: An electric power generation system including a power shaft assembly including a combustion turbine with a compressor, an expansion turbine, a combustor feeding the expansion turbine, an electrical generator, and a shaft for coupling the expansion turbine to drive the compressor and the electrical generator; an additional shaft assembly including an intercooler, a compressor, an expansion turbine, a combustor feeding the expansion turbine, and a driver for driving the compressor of the additional shaft assembly, the compressor of the additional shaft assembly being constructed and arranged to have a pressure ratio greater than a pressure ratio of the expansion turbine of the additional shaft assembly which is fluid connected to the power shaft assembly for pressure unloading the compressor of the power shaft assembly; a recuperator; and an exhaust stack.

Abstract: In order to augment the power produced by a gas turbine system of a type having an air compressor for producing compressed air, a combustor for heating the compressed air, and a gas turbine responsive to the heated air for driving the air compressor and the load, cooling air is supplied to the compressor by indirectly contacting the air with water that is chilled by flashing some of the water into a vapor.

Abstract: A method for cooling and eliminating temperature variations in a power plant for combustion of a fuel in a pressurized fluidized bed includes pressuring air in a compressor and supplying the pressurized air to the pressurized fluidized bed through air paths after the pressurized air is cooled and temperature variations in the pressurized air are substantially eliminated prior to supplying the pressurized air into the pressurized fluidized bed in at least one transfer surface provided in the air paths.

Abstract: In a combined gas/steam power station plant which consists essentially of a fossil-fired gas turbine group and a steam circuit, with an exhaust heat boiler (11) in between, intercooling and reheat are provided to maximize the efficiency. The gas turbine group consists of two compressors (1, 2), of two combustion chambers (7, 9) and of two turbines (8, 10). Downstream of the first compressor (1), there is an intercooler (3) and on the cool side of this is placed an evaporator (4) which is in effective connection with the intercooler. The steam quantity formed in the evaporator (4) is introduced into a turbine (6) of the steam circuit, the result of this being a first improvement in efficiency. Downstream of the first turbine (8), there is a second combustion chamber (9) in which the exhaust gases from the first turbine (8) are processed to produce hot gases for the second turbine (10) .

Abstract: Mechanical and electrical power are produced along with synthesis or fuel gas by the partial oxidation process with integrated combustion and steam turbines. By-product vaporized liquefied natural gas for feed to a pipeline for gas consumers is obtained by heat exchange with heat containing streams from the partial oxidation gasification and gas cleaning and purification zone; and optionally from heat containing streams from combustion and/or steam turbine zones which are integrated with said partial oxidation process. Heat from the combustion turbine exhaust gas is used as follows: (1) superheat steam for use in a steam turbine; (2) preheat water saturated clean sulfur-free synthesis or fuel gas with or without supplemental methane enrichment; (3) preheat oxygen gas for said partial oxidation zone; and (4) vaporize LNG. Pre, inter, and after stages of an air compressor are cooled by indirect heat exchange with LNG which is thereby warmed or vaporized.

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 pressurized fluidized-bed boiler power plant comprises: a pressurized fluidized-bed boiler including a fluidized-bed boiler and a pressure vessel containing the fluidized bed; a single-shaft gas turbine including a gas turbine, an air compressor and an electric generator; and a steam turbine unit in which steam generated by the pressurized fluidized-bed boiler drives a turbine so that electricity is generated. In the power plant, an air cooler is situated on a duct for conveying the compressed air from the compressor to the boiler or at an inlet of the compressor. Alternatively, there may be provided a device for conveying the compressed air from the compressor by way of the air cooler to a space formed by the fluidized-bed boiler and the pressure vessel of the pressurized fluidized-bed boiler. During operation, the compressed air is cooled to a temperature level allowable for the pressure vessel before it is supplied to the boiler.

Abstract: The invention presented relates to a process and system for removing the moisture from the intake air of a gas turbine. More particularly, the process involves passing the intake air flow through a mesh pad to reduce the moisture level thereof downstream from the means used to cool the air prior to entering the gas turbine compressor.

Abstract: The present invention provides means for significantly increasing the available power from an aircraft turbine engine, especially a turboprop or turboshaft engine. This is achieved by including a heat exchanger intermediate the compressor and the combuster; to significatnly reduce the temperature of the compressed gases fed to the combustor; the temperature drop ratio across the combustor air precooler must be greater than the pressure drop ratio across the precooler. This provides an increase in density of the air fed to the combustor with a resultant increase in mass flow through the combustor and the turbine, which increases available power, especially at higher altitudes.

Abstract: A high performance turbine engine includes refrigeration apparatus powered by the engine and effective upon a fractional air flow received from the engine compressor to provide chilled air for cooling of internal engine components. The refrigeration process facilitates rejection of unwanted heat to ambient air despite high stagnation temperatures at high flight speeds. The invention allows increased turbine inlet temperature and improved fuel efficiency or thrust per pound of engine weight with present-day metals and cooling technology being used for engine construction.

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: A compression intercooled gas turbine and vapor bottoming combined cycle system with the gas turbine operating at 30 to 65 atmospheres is disclosed. A twin spool hot gas generator incorporates compression intercooling at the optimum intercooler pressure ratio to (a) minimize intercooler heat rejection degradation, (b) raise the overall cycle pressure ratio, (c) increase gas generator core mass flow and (d) to increase the gas turbine power output. The gas turbine can operate in either the simple cycle or the reheat cycle mode for optimum combined cycle efficiency. A combined cycle efficiency upwards of 60 percent can be realized.

Abstract: An air liquification system for a combustor or the like, including a condenser having an air intake and a heat exchanger for cooling the air to substantially a liquid state. A first conduit conducts the liquid air to the combustor. A source of hydrogen in a liquid state is provided, and a second conduit conducts the liquid hydrogen to the heat exchanger whereby the hydrogen acts as the cooling medium therein. A third conduit conducts the hydrogen from the heat exchanger to the combustor and includes a compressor for compressing the hydrogen up to a given combustor pressure. A second combustor may be provided for operating at ambient air pressure, with a portion of the hydrogen from the condenser being conducted to the second combustor upstream of the compressor. An air precooler may be provided upstream of the heat exchanger for passing the liquid air therethrough to act as a regenerative cooling medium therein prior to conducting the air to the first combustor.

Abstract: An apparatus for optimizing blade and sealing slots of a compressor of a gas turbine comprising a rotor including a plurality of axially spaced discs and rotor blades on the discs and a stator casing surrounding the blades and forming clearance slots therewith. The blades and stator casing form a path for flow of air in a main stream in which the air is compressed and discharged at a discharge end of the compressor. A seal at the last of the discs opposes outflow of compressed air thereat and forms sealing slots through which leakage air can flow from the main stream. The leakage air is conveyed from the compressor and a portion thereof is diverted as a secondary stream in a direction opposite the main stream of air flow in the compressor, and discharged towards the last rotor disc and at least the next adjacent rotor disc to flow thereon.

Abstract: An ultrasonic fog generator can be used to advantage in injecting a fog into the input air of a combustion chamber, in order to improve efficiency and reduce the noxious emissions in the exhaust. In accordance with one form of the disclosure, a heat exchange is utilized to advantage in a turbine system in reheating compressed air that has been cooled as the air was fogged, the reheated air being input to the combustion chamber. In another form of the disclosure an adjustable heat exchange is used to controllably heat input air before the fogging thereof, the level of heat exchange depending on properties of the input air and the level of fogging to be implemented.

Abstract: An assembly for producing wet compression of gas being compressed in a centrifugal-type, multistage gas compressor having an impeller, a diffuser "downstream" of the impeller, and a cross-over channel connected to the downstream end of the diffuser includes a plurality of liquid jets for injecting a vaporizable liquid such as water into a gas stream undergoing compression. The liquid jets are positioned axisymmetrically about the longitudinal axis of the compressor shaft and are adapted to inject liquid into the diffuser substantially upstream of the cross-over channel, and, in a preferred embodiment, have a radial spacing from such axis of about 1.05 to 1.1 times the maximum radius of the compressor impeller. The invention attains a marked increase in vaporization of the injected liquid, providing better compressor performance and reduced wear of compressor internal parts.

Abstract: A gas compressor is provided having a source of supersonic velocity gases acting to accelerate inlet gases through a mixing region and diffuser. The inlet gas is introduced into the mixing chamber through a converging-diverging nozzle, causing said gas to accelerate to supersonic velocity. An injection of coolant is provided into the resulting gas stream to cause a decrease in its stagnation temperature and an increase in its stagnation pressure. Also provided is a means for modifying the nuclear spin orientations of the gases involved in the mixing region upstream of the combustion chamber to increase the stagnation pressure and decrease the stagnation temperature of the gas flowing into the combustion chamber. The gas compressor can be utilized in a jet engine for producing a flow of pressurized gases which may be expanded through a thrust producing nozzle.

Abstract: A gas turbine is disclosed, in which a portion of compressed air from a compressor of the turbine is cooled by water and the cooled compressed air is utilized for cooling a region at or about the turbine inlet, and in which the interior of a combustor chamber into which the compressed air from the compressor is introduced is divided by a partition wall into a combustor part and a transition piece part and air cooling pipes are provided through the partition wall, each air cooling pipe being provided with nozzles through which to jet water to positively and effectively cool the compressed air while it passes through the air cooling pipe.

Abstract: A regenerative gas turbine cycle wherein heat recovery is carried out by a mixture of air/steam which is obtained by contact between water and compressed air, the compressed air being compressed by a compressor for compressing gas using air or air based gas as a combustion supporting/working medium gas. The cycle includes the improvement whereby mixture of air/steam and liquid phase cooled water is obtained through contact between the compressed air and heated water which is used as heat recovering medium; the cooled water being used as heat recovering medium not only for heat recovery of turbine exhaust gas but also, for(a) intercooling of the compressor, and/or(b) precooling of compressed air for the contact operation.Water corresponding to the amount of water which contacts the compressed air and is lost by evaporation is added to the liquid phase water for contact or heat recovery as it is or after use as a heat recovering medium.

Abstract: A compression intercooled gas generator operating at high-cycle pressure ratios of 35 to 65 atmospheres to furnish hot pressurized gas sequentially to a diffuser, to a reheat combustor and then to a power turbine. An associated method of compression intercooling with an optimum intercooling pressure ratio to minimize overall combined-cycle efficiency degradation when said gas generator, diffuser, reheat combustor and power turbine are operating in conjunction with a heat-recovery boiler and a steam or vapor turbine. A coaxial shafting arrangement for driving the low-pressure and high-pressure compressor sections. A pressure-retaining casing arrangement enclosing the high-pressure portion of said gas generator to contain the higher than normal pressure of said gas generator.

Abstract: A reheat gas and double reheat steam turbine combined cycle is provided in which the outer compressor shell and gas generator turbine are cooled with steam to control tip clearance of the rotating blades of the compressor and gas generator turbine with the respective shells which confine the blading. Steam cooling of the gas generator turbine blading as well as the low and high pressure gas generator shafts are also provided.

Abstract: The gas turbine power station, which is of the type utilizing an air reservoir, and is operated in accordance with the method for reducing the amount of NO.sub.x and for raising output, possesses an intermediate condensate-vessel and a main condensate-vessel for receiving the condensate which is produced in the compressor-air coolers. From the main condensate vessel, the condensate is introduced into the combustion chambers of the gas turbine, optionally after passing through a recuperator.

Abstract: A reheat gas and double reheat steam turbine combined cycle is provided in which the outer compressor shell and gas generator turbine are modified for steam cooling to control tip clearances of the rotating blades of the compressor and gas generator turbine with the respective shells which confine the blading.

Abstract: A compression intensified thermodynamic gas process that includes a compressor rotor having a series of passage forming blades between which a process gas is conducted during compression. A coolant metering system is contained within the rotor structure which is arranged to introduce a liquid coolant directly into the gas flow as the gas is being compressed. Coolant nozzles are strategically positioned throughout the rotor so that coolant droplets that are introduced into the flow stream will pass freely out of the rotor without impacting the rotor blades.

Abstract: A method and system for operating a regenerative gas turbine in which a compressed gaseous medium is saturated with steam from untreated water having impurities in a first contact chamber and then supplied to a second chamber where the mixture is washed with pure water to remove impurities. The resulting mixture is mixed with fuel and combusted to supply gas to the turbine. Exhaust gas from the turbine is supplied to two serially connected regenerators which transfer heat to the recirculating untreated and pure water.

Abstract: System for waste heat recovery, comprising a combustion machine (2,3) with a compressor (4) for the combustion air (30) and means (7) like a heat exchanger (13) and/or a recirculation duct (14), to transfer heat, contained in the combustion gases (37,38,39) after their expansion in the machine (3), to the combustion air flow (33) before its entry into the compressor (4). Water (8,8') is introduced into the (to be) heated combustion air flow (30,33) cooling it by its evaporation, and the vapor is partially condensed again in a cooler (6) fitted in the compressed flow (34) after leaving the compressor (4). The condensation can take place at higher temperature, thus the system acts as heat pump for the waste heat. The compressed air flow (35) enters extra cooled into the combustion chamber (2) which provides an additional advantage. For the compressor (4), combustion chamber (2) and turbine (3) a normal gas turbine may be used.

Abstract: Apparatus for improving the operating efficiency of a gas turbine engine includes a heat pump and a pair of heat exchangers for use in conjunction with the engine. The first heat exchanger is disposed in the flow path of the engine upstream of its compressor section, while the second heat exchanger is disposed in the engine flow path downstream of the compressor section and upstream of the combustor section of the engine. A portion of the work output of the engine is used to operate the heat pump so as to cause cooling of air in the flow path at the first heat exchanger and heating of air in the flow path at the second heat exchanger.

Abstract: A system for cooling, cleaning and humidifying air entering an air breathing gas turbine. The air is first cooled on the dry side of an indirect evaporative heat exchanger and then moistened and cleaned by a fine water spray of distilled water obtained from a boiler heated with excess heat from the gas turbine and condensed by the moist cool air leaving the wet side of the heat exchanger.

Abstract: A gas turbine engine of simple construction having a compressed air cooler between the first and second stages of compression. A turbine with a heat recuperator is arranged to transfer heat from the exhaust gas stream to the combustion inlet. The air cooler and recuperator are of tubular type, formed by a plurality of small diameter tubes uniformly distributed forming coaxial cylindrical bodies placed one within the other. Heat exchange flanges are joined to each other and are situated in the same plane. The stator parts of the engine constitute a shell assembly having plural shells arranged one within the other with their free ends supported on the flanges of the heat exchangers, hermetically sealing the annular spaces and forming inlet and outlet areas of compressed air in the cooler and in the recuperator.

Abstract: Part of high-pressure air is extracted from the vicinity of the final stage of a compressor and is introduced into a water spraying chamber, and water at the normal temperature is injected into the high-pressure air from a nozzle installed in the water spraying chamber, to prepare a cooled coolant. The coolant sometimes contains water drops. The cooled coolant is fed into coolant passageways which are provided inside a moving blade in a manner to extend from the root part to the tip of the moving blade. When the coolant passes through the passageways, the moving blade is cooled by the coolant, and after the cooling, the coolant is emitted into a turbine main gas passageway. In case where the water drops are contained in the coolant, they vaporize during the cooling of the moving blade, to cool the air of the coolant, to suppress the temperature rise of the coolant and to enhance the cooling effect.

Abstract: A power conversion system comprising a combination of a liquefied natural gas vaporizing plant and a fuel burning power generating facility is disclosed. The liquefied natural gas vaporizing plant utilizes the cryogenic capacity of the liquefied natural gas to produce liquid air which is pumped to a high pressure by a liquid air pump. The liquid air is then brought into a heat exchanging relationship with air drawn into the vaporizing plant so that the high pressure liquid air is converted to high pressure gaseous air. The high pressure gaseous air which represents recovered reversible energy of the liquefied natural gas is fed into a combustion chamber of the fuel burning power generating plant. Since the power generating facility requires no significant output of power to drive a compressor to compress ambient air prior to its entry into the combustion chamber, the power generating facility is operated at a high efficiency.

Abstract: An annulus formed in the nut of a fuel nozzle to collect, distribute and atomize water droplets fed into the fuel nozzle for increased thrust produced by a turbine type power plant powering aircraft is discretely formed adjacent the discharge juncture point and discharged angularly into and with respect to the fuel spray emitted into the combustion zone for smoke reduction purposes.

Abstract: A turbine engine operates at high pressure and at relatively low temperatures and revolutions per minute through the use of special carburetion, compressor, combustion unit, and turbine arrangements. The system is characterized by the use of water which is vaporized and concurrently reduces the temperature of the vaporized fuel and air mixture as compression occurs, and is not physically intermixed with the combustion gases until after initial combustion takes place. The compressor includes a pair of back-to-back, four stage composite compressors to which synchronized dual carburetion or meter-flow arrangements separately supply water and gasoline or other fuel, along with air. The water absorbs heat from the compression of both of the two compressors, and the resultant vaporous product gases are routed to the jacket of a combustion chamber in which the compressed fuel and air mixture is burned.

Abstract: A ramjet powered vehicle having a bleed slot in the subsonic diffuser, for the ramjet combustor, which supplies air to a turbine for supplying power to vehicle accessories. A vortex tube is provided between the bleed slot and the turbine to provide a cool air supply. Radar absorbing material is positioned adjacent ramjet inlet with a cooling duct provided to supply cooling air from the vortex tube to the ramjet inlet cowl lip to provide cooling for the radar absorbing material.

Abstract: The method of energy conversion consists in burning a fuel in an oxidizing gas in order to admit the combustion gases into an expansion machine for delivering mechanical energy, in previously compressing the oxidizing gas in a positive-displacement compressor driven by the expansion machine, in injecting into the compressor a sealing and/or lubricating auxiliary liquid which is continuously cooled and separated from the compressed gas, then re-injected into the compressor. The auxiliary liquid is cooled by vaporization of water and the steam produced is entrained in the stream of compressed oxidizing gas.

Abstract: An air-to-air heat exchanger is provided for a gas turbofan engine to significantly reduce the quantity of cooling air that is presently needed to effectively cool the hot turbine parts. Typically, the turbine is internally cooled with air bled from the compressor which, though cooler than the turbine, has been heated due to the work done on it by the compressor. In accordance with the present invention, the heat exchanger is located internally of the bypass duct to place in heat exchange relationship a captured portion of the relatively cool bypass flow and this warmer compressor bleed air, thereby cooling the turbine coolant and significantly reducing the amount of such coolant required. This results in a decrease in engine specific fuel consumption.

Abstract: A gas turbine plant including a compressor section and a turbine section housed within a multipart casing with the shafts of each section co-axial, the compressor section including a double-sided low pressure radial compressor, a high pressure radial compressor and an inter-cooler, while the turbine stage includes a first stage axial turbine on the same shaft as the compressor and at least an additional turbine stage; a heat exchanger or regenerator being included in the turbine exhaust.

Abstract: An engine particularly adapted to travel at high supersonic and hypersonic velocities. The engine has a forward turbine positioned at the engine inlet and a rearwardly positioned compressor driven by the turbine through an interconnecting longitudinal shaft. In a first embodiment, a cryogenic fuel, such as hydrogen, is introduced into the engine at a location between the turbine and the compressor, with vaporization and heating of the fuel causing a reduction in the compressor inlet temperature and a consequent increase in compressor discharge for a given turbine power shaft input. The resulting fuel/air mixture passes through the compressor and then into a rearwardly positioned combustion chamber where it is ignited, with the combustion products then being expanded from the compressor discharge pressure to atmospheric pressure through an outlet nozzle as jet exhaust.