REGISTER now for FREE 
|
FREE patent keyword monitoring and additional FREE benefits. REGISTER now for FREE
|
|
|
Power Plants > Reaction Motor (e.g., Motive Fluid Generator And Reaction Nozzle, Etc.) > Interrelated Reaction Motors > Air And Diverse Fluid Discharge From Separate Discharge Outlets (e.g., Fan Jet, Etc.) Air And Diverse Fluid Discharge From Separate Discharge Outlets (e.g., Fan Jet, Etc.)Air And Diverse Fluid Discharge From Separate Discharge Outlets (e.g., Fan Jet, Etc.) patent applications listed are from June 2005 to current and include Date, Patent Application Number, Patent Title, Patent Abstract summary and are linked to the corresponding patent application page.01/17/08 - 20080010970 - Turbofan case and method of making A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed. ... 11/01/07 - 20070251210 - Liquid injection in a gas turbine during a cooling down phase The invention relates to a method for cooling a gas turbine comprising a rotor, said method being carried out after the operation of the gas turbine and whereby the rotor is driven at least intermittently during a cooling phase at a reduced nominal speed. To provide a gas turbine with ... 10/25/07 - 20070245710 - Optimized configuration of a reverse flow combustion system for a gas turbine engine An apparatus is provided for a gas turbine engine. The gas turbine engine comprises a high pressure compressor, a single-stage high pressure turbine, a multi-stage low pressure turbine, and a reverse flow combustor unit. The reverse flow combustor comprises a combustor liner assembly, a combustor dome, and a plurality of ... 10/25/07 - 20070245709 - Relighting a turbofan engine The method and apparatus for in-flight relighting of a turbofan engine involve in one aspect selectively controlling an accessory drag load on one or more windmilling rotors to permit control of the windmill speed to an optimum value for relight conditions. ... 10/11/07 - 20070234706 - Turbofan jet engine with an ancillary-connecting arm, and the ancillary-connecting arm The invention concerns a turbofan jet engine that includes an external casing, connected by radial arms to an annular internal device, downstream of which is mounted, opposite to the external casing, a shell forming a fairing, ancillaries on the outside of the external casing, and ancillaries on the inside of ... 08/16/07 - 20070186535 - Double bypass turbofan A variable cycle turbofan engine includes first and second fans independently joined to respective turbines. A first bypass duct surrounds a core engine disposed in flow communication with the second fan. A second bypass duct surrounds the first bypass duct in flow communication with the first fan. A first exhaust ... 07/19/07 - 20070163229 - Gas turbine engine inlet with noise reduction features A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, ... 07/12/07 - 20070157597 - Aircraft engine The invention relates to an aircraft engine, particularly a gas turbine engine. The aircraft engine comprises at least one fan (11) and a core engine (12). The fan (11) comprises a fan housing (13) which encloses a fan flow channel and at least one fan wheel (15). The core engine ... 07/05/07 - 20070151228 - Fixed nozzle thrust augmentation system A thrust augmentation system for a mixed exhaust turbofan engine comprises an augmentation duct, a combustion system and a fixed area exhaust nozzle. The augmentation duct receives primary and secondary air of the turbofan engine and is positioned co-axially with an exhaust case of the turbofan engine. The combustion system ... 06/28/07 - 20070144141 - Pulsed combustion fluidic nozzle A propulsion system for producing thrust includes a turbine engine. The engine has a compressor, a combustor downstream of the compressor along a flow path, and a turbine downstream of the combustor along the flow path. A plurality of combustion conduits have outlets positioned to discharge combustion gas to form ... 06/21/07 - 20070137175 - Compact booster bleed turbofan A Turbofan engine includes a fan mounted to a fan frame inside a fan nacelle. A booster compressor is joined to the fan inboard a flow splitter. A booster bleed system is disposed inside the splitter, and includes an inlet at the compressor outlet, and an outlet joined to the ... 06/21/07 - 20070137174 - Axial flow positive displacement worm gas generator An axial flow positive displacement engine has an inlet axially spaced apart and upstream from an outlet. Inner and outer bodies have offset inner and outer axes extend from the inlet to the outlet through first, second, and third sections of a core assembly in serial downstream flow relationship. At ... 06/21/07 - 20070137173 - Axial flow positive displacement gas generator with combustion extending into an expansion section An axial flow positive displacement engine has an inlet axially spaced apart and upstream from an outlet. Inner and outer bodies have offset inner and outer axes extend from the inlet to the outlet through first, second, and third sections of a core assembly in serial downstream flow relationship. At ... 06/14/07 - 20070130912 - Shrouded turbofan bleed duct A bleed duct is configured for bleeding fan air from the fan bypass duct in a turbofan aircraft engine. The bleed duct includes a tubular conduit having an inlet and outlet at opposite ends. The conduit is configured in flow area for recovering pressure from speeding fan air bled therethrough. ... 06/07/07 - 20070125066 - Turbofan engine assembly and method of assembling same A method for assembling a gas turbine engine includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, coupling a counter-rotating fan assembly to the core gas turbine engine such that air discharged from the counter-rotating fan assembly is channeled directly into an inlet ... 05/31/07 - 20070119150 - Turbofan gas turbine engine with variable fan outlet guide vanes A turbofan gas turbine engine includes a forward fan section with a row of fan rotor blades, a core engine, and a fan bypass duct downstream of the forward fan section and radially outwardly of the core engine. The forward fan section has only a single stage of variable fan ... 03/08/07 - 20070051091 - Turbofan arrangement A bypass turbofan engine comprises a first propulsion system and a second propulsion system. The first propulsion system comprises a first fan rotor, a core engine, a first low pressure turbine and a first fan shaft drivingly connecting the first turbine and the first fan rotor. The second propulsion system ... 03/01/07 - 20070044451 - Cooling systems Apparatus for maintaining the temperature of a component of a gas turbine engine below a predetermined maximum working temperature comprises a reservoir for a cooling fluid having a boiling point below the working temperature and in which the component is immersed or with which it is in contact. At least ... 02/22/07 - 20070039310 - Compressor comprising a plurality of cells reconstituting an annular volume of separation of flows in a turbine engine This turbine engine compressor comprises a separating nose extended by inner and outer annular walls defining in cooperation an annular volume (V) of separation of a primary flow (F1) and a secondary flow (F2). This volume (V) comprises a plurality of annular segments in the form of cells separated in ... 02/22/07 - 20070039309 - Stiffener for low pressure compressor for an aircraft engine Advantageously, the stiffeners (20) are made of two parts fixed to each other; their manufacturing is optimized to limit the additional weight due to their presence. ... 02/08/07 - 20070028595 - High pressure gas turbine engine having reduced emissions A gas turbine engine having a longitudinal centerline axis therethrough, including a fan section at a forward end of the gas turbine engine for producing a first compressed air flow; a first compressor positioned downstream of the fan section and in flow communication with at least a portion of the ... 02/01/07 - 20070022739 - Methods and apparatus for operating gas turbine engines A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine. The method also comprises coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the ... 02/01/07 - 20070022738 - Reinforcement rings for a tip turbine engine fan-turbine rotor assembly A fan-turbine rotor assembly includes a diffuser mountable to the outer periphery of a multitude of fan blade sections to provide structural support to the outer tips of the fan blade sections and to turn and diffuse the airflow from the radial core airflow passage toward an axial airflow direction. ... 01/18/07 - 20070012026 - Nested core gas turbine engine A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section. ... 01/11/07 - 20070006569 - Turbomachine with contrarotating fans A turbomachine comprising: a gas generator for producing combustion gas; a turbine section through which the combustion gas passes and comprising first and second rows of contrarotating turbine rotor blades respectively driving first and second low-pressure shafts in rotation; and a fan section comprising a first row of fan blades ... 12/28/06 - 20060288687 - Grommeted bypass duct penetration A bypass duct sealing grommet, for sealing between an opening in a gas turbine engine bypass duct wall and an external surface of a projection extending through the opening, where the grommet has an annular body with a central aperture having an internal periphery adapted to sealingly engage the external ... 12/28/06 - 20060288686 - Counterrotating turbofan engine A turbofan engine includes a fan, compressor, combustor, high pressure turbine, and low pressure turbine joined in serial flow communication. The high pressure turbine includes two stages of rotor blades to effect corresponding exit swirl in the combustion gases discharged therefrom. A transition duct includes fairings extending between platforms for ... 12/07/06 - 20060272314 - Integrated counterrotating turbofan A turbofan engine includes a fan, compressor, combustor, single-stage high pressure turbine, and low pressure turbine joined in serial flow communication. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation. First stage stator vanes in the ... 11/23/06 - 20060260293 - Blade containment structure The resulting free end of composite liner (24) wraps round the striking end of the blade part, thus blunting the cutting action of the blade part and spreading the generated forces to the extent that the blade part is de-energised sufficiently to prevent it penetrating the fan case (20). ... 11/16/06 - 20060254255 - Aircraft propulsion system To provide an aircraft propulsion system which can secure the optimum thrust and thrust vector for flight conditions, as well as the optimum sectional area for the engine, and which is highly compatible with the environment. An electrical generator is coupled to a turbofan engine, the electrical generator is driven ... 11/02/06 - 20060242941 - Fladed supersonic missile turbojet A turbojet engine includes a core engine, afterburner, and converging-diverging exhaust nozzle disposed in serial flow communication. A bypass duct surrounds the core engine and afterburner and terminates in flow communication with the exhaust nozzle. The compressor includes first stage fan blades having integral flades at the tips thereof disposed ... 10/26/06 - 20060236675 - Jet engine with compact arrangement of fan A jet engine includes a fan arranged upstream of a core engine having a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine, and a low pressure turbine. The high pressure turbine is drive-connected to the high pressure compressor. The low pressure turbine is drive-connected ... 09/28/06 - 20060213180 - Augmenter swirler pilot A turbofan gas turbine engine augmenter includes a fuel/air swirler disposed between an axially extending bypass flowpath and an axially extending exhaust flowpath. A swirler inlet is axially open to and positioned substantially normal to the bypass flowpath and a swirler outlet is open to and positioned substantially parallel to ... 09/14/06 - 20060201135 - Composite containment case for turbine engines A composite fan casing for a gas turbine engine includes, in an exemplary embodiment, a core having a plurality of core layers of reinforcing fiber bonded together with a thermosetting polymeric resin. Each core layer includes a plurality of braided reinforcing fiber tows. The braids of reinforcing fiber tows are ... 09/07/06 - 20060196164 - Dual mode turbo engine A dual mode gas turbine engine includes a dual mode fan and low pressure compressor section upstream of radially inner and outer gas generators which include radially inner and outer combustors disposed in radially inner and outer working fluid flowpaths, respectively, in fluid flow communication with the dual mode fan ... 08/17/06 - 20060179818 - Jet engine inlet-fan system and design method A supersonic aircraft engine axial fan that includes a rotating blade row having blades that receive a supersonic entry flow in the absolute frame and decelerate the flow to a lower supersonic or subsonic velocity exit flow while adding work to the flow to increase stagnation pressure. It is preferred ... 08/17/06 - 20060179817 - Nacelle assembly for a gas turbine engine A nacelle assembly 40 adapted for mounting on a ducted fan gas turbine engine 20 comprising a generally annular body 46 having an air inlet 42 and an air outlet 44, the generally annular body 46 encircling a region of the engine 20 when working in operative association with the ... 06/22/06 - 20060130456 - Turbine engine rotor stack A turbine engine has a first disk and a second disk, each extending radially from an inner aperture to an outer periphery. A coupling, transmits a torque and a longitudinal compressive force between the first and second disks. The coupling has first means for transmitting a majority of the torque ... 06/08/06 - 20060117734 - Supplemental oil cooler airflow for gas turbine engine A gas turbine engine is provided with an oil cooler which receives cooling air from a turbo fan. At times when the turbo fan is operating at lower speeds, the volume of cooling air is also lowered. At such times, a supplemental airflow is provided over heat exchangers in the ... 05/18/06 - 20060101804 - Aircraft engine arrangement In order to avoid external bulging (5) to accommodate accessory mechanisms (27) and gearboxes (30) to drive these mechanisms (27) in accordance with the present invention splitter fairings (26) are located within a bypass duct (23) of an engine (20). The bypass duct (23) is defined between a casing (21) ... 05/04/06 - 20060090451 - Counter-rotating gas turbine engine and method of assembling same A method for assembling a gas turbine engine includes providing a first fan assembly including a plurality of rotor blades that are configured to rotate in a first rotational direction at a first rotational speed, rotatably coupling a second fan assembly axially aft of the first fan assembly, wherein the ... 05/04/06 - 20060090450 - Counter-rotating turbine engine and method of assembling same A method for assembling a gas turbine engine that includes providing a first fan assembly configured to rotate in a first rotational direction, rotatably coupling a second fan assembly to the first fan assembly, wherein the second fan assembly is configured to rotate in a second rotational direction that is ... 05/04/06 - 20060090449 - Counter-rotating turbine engine and method of assembling same A method for assembling a gas turbine engine includes providing a first fan assembly configured to rotate in a first rotational direction, rotatably coupling a second fan assembly to the first fan assembly, wherein the second fan assembly is configured to rotate in a second rotational direction that is opposite ... 05/04/06 - 20060090448 - Gas turbine engine and method of assembling same A method of assembling a gas turbine engine that includes rotatably coupling a first low-pressure turbine rotor to a high-pressure turbine, rotatably coupling a second low pressure turbine rotor to the first low-pressure turbine rotor, and rotatably coupling the second low-pressure turbine rotor to a turbine rear-frame such that a ... 04/27/06 - 20060086078 - Universal carnot propulsion systems for turbo rocketry Turbofan jet engines utilizing the Carnot cycle for improved performance with isothermal compression of combustion air and, in part, isothermal expansion of thermally heated air, the engines having a turbofan compressor rotor with hollow fan blades in a core bypass passage through the engine and an annular, peripheral thermal chamber ... 04/20/06 - 20060080950 - Methods and apparatus for cooling gas turbine engines A method for assembling a gas turbine engine assembly that includes mounting a gas turbine engine including an inlet and an exhaust within a module that includes an inlet area, an exhaust area, and an engine area extending therebetween, such that the gas turbine engine is housed within the module, ... 03/23/06 - 20060059889 - Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine A method and apparatus for improving fan case containment in a gas turbine jet engine employs a containment ring and a heat resistance ring which are shrink interference fit on the inside diameter of the fan case, the containment ring where the large fan blades turn, and the heat resistance ... 03/16/06 - 20060053769 - Chevron-type primary exhaust nozzle for aircraft turbofan engine, and aircraft comprising such a nozzle A primary exhaust nozzle for a turbofan engine of the double, separated air-flow type for aircraft comprises: an inner coat, within which there circulates a primary air flow (FP), comprising chevrons at an external end and an outer coat at least partially surrounding the inner coat and along which there ... 03/16/06 - 20060053768 - Aerodynamic fastener shield for turbomachine A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced fasteners. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned ... 03/02/06 - 20060042228 - Pulse detonation system for a gas turbine engine having multiple spools A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of the fan section, the booster compressor including ... 03/02/06 - 20060042227 - Air turbine powered accessory An aircraft accessory system includes an aircraft engine powered direct air turbine driven accessory and an air turbine drivingly directly connected by an air turbine shaft to the accessory. The air turbine includes a variable geometry turbine nozzle in selectable direct flow communication with at least two compressed engine air ... 01/26/06 - 20060016173 - Securing arrangement A securing arrangement for securing a manifold to a casing (surrounding a rotary assembly) is disclosed the securing arrangement comprises a bracket defining a recess co-operable with a radially extending part of the casing. Securing means, provide to secure the bracket to the aforesaid radially outwardly extending part. ... 01/26/06 - 20060016172 - Gas turbine engine A gas turbine engine (2) comprises a fan unit (4, 18, 36, 42, 44, 46) in flow relationship with an engine core and a bypass duct, of which said engine core and bypass duct (16) are in parallel flow relationship with each other. The engine core comprises a compressor (6), ... 01/12/06 - 20060005529 - Blade clearance control A turbine engine has a circumferentially segmented shroud within a case structure. Each shroud segment is mounted for movement between an inboard position and an outboard position. One or more springs bias the shroud segments toward their inboard positions. One or more valves are positioned to vent one or more ... 12/15/05 - 20050274103 - Gas turbine engine inlet with noise reduction features A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, ... 11/17/05 - 20050252195 - Noise reduction assembly for aircraft turbojet A noise reduction assembly located at a junction plane between an air intake structure and a fan casing of an aircraft turbojet has improved acoustic properties since the alternation of acoustic and non-acoustic zones is displaced or eliminated. In particular, the inner wall of the air intake structure includes a ... 11/17/05 - 20050252194 - Methods and apparatus for assembling gas turbine engines A method facilitates assembling a gas turbine engine including a compressor and a rotor assembly coupled in axial flow communication downstream from the compressor. The method comprises coupling a bypass system in flow communication with the compressor to channel a portion of flow discharged from the compressor towards the rotor ... 11/10/05 - 20050247043 - Turbojet engine comprising a connector arm for ancillary systems, and the connector arm for ancillary systems The present invention concerns a turbofan jet engine comprising an outer fan duct, an inner fan duct, fluid-conveying ancillaries located outside the outer fan duct, fluid-conveying ancillaries located inside the inner fan duct, characterized by the fact that at least one removable modular arm forming a connection for ancillaries is ... 11/10/05 - 20050247042 - Turbofan jet engine with ancillaries distribution support This invention concerns a turbofan jet engine comprising an outer casing supported by arms, an inner casing facing the casing and ancillaries. An ancillaries distribution support is formed along the axis of an arm, on the inner casing, comprising a first sole plate for reception of ancillaries on the outer ... 11/03/05 - 20050241293 - Method and device for measuring airflows through hvac grilles A fan powered by a controlled external energy source and a flow measurement device measure the airflow exiting or entering grilles/registers of an HVAC system without impeding the airflow being measured. A flow straightening element is preferably employed to overcome any effects of a non-uniform or swirled airflow profile on ... 11/03/05 - 20050241292 - Turbine engine arrangements A turbine engine arrangement is provided in which contra rotating shafts 104, 105 are respectively secured to a fan and a gearbox 106 which is also coupled to the shaft 104. In such circumstances the relative rotational speed ratio between the shafts 104, 105 can be determined with a first ... 11/03/05 - 20050241291 - Three-spool by-pass turbojet with a high by-pass ratio The invention relates to aerodynamically matching the rear fan of a turbojet having two fans and a low-pressure compressor at the front of the intermediate casing, said fans being driven by two independent shafts. Said compressor is disposed between the blades of the two fans and includes at least one ... 11/03/05 - 20050241290 - Turbofan engine with the fan fixed to a drive shaft supported by a first and a second bearing The centring function of the second bearing (7) after decoupling of the first bearing (6) is thus provided without introducing excessive stresses in the bearing (7). ... 10/20/05 - 20050229586 - Variable area nozzle An exhaust nozzle assembly for a gas turbine engine, the assembly comprises a main axis, an inner nozzle, an outer nozzle, a translatable centre-body and a means for translating the centre-body between a forward position and a rearward position. The centre-body is disposed radially inwardly of the inner nozzle thereby ... 10/20/05 - 20050229585 - Gas turbine engine exhaust nozzle A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which extend in a generally axial direction from a downstream portion of the nozzle wherein the nozzle further comprises ... 10/20/05 - 20050229584 - Aircraft structure that includes a duct for guiding fluid flow therethrough An aircraft structure includes a duct having an inlet for fluid flow into the duct and a first outlet for fluid flow out of the duct. The duct is configured to guide fluid flow out of the duct through the first outlet in an at least partially reversed direction relative ... 10/13/05 - 20050223693 - Engine cooling Cavities 4 are defined within an engine nacelle 1 with an inner surface 2 and an outer surface 3. Within these cavities 4, an evaporatable liquid 5 is arranged such that a proportion of the liquid 5 is in a gaseous phase in order to facilitate heat transfer between the ... 10/13/05 - 20050223692 - Apparatus and method for reduction of jet noise from turbofan engines having separate bypass and core flows An exhaust flow system for use with a turbofan jet engine that provides separate fan flow and core flow streams that are not mixed. The system includes a fan nozzle and a primary flow nozzle. The primary flow nozzle includes a downstream edge portion that is either beveled with one ... 09/15/05 - 20050198941 - Turbojet architecture with two fans at the front The invention relates to a turbojet having a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. Said compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the ... 09/08/05 - 20050193716 - Jet exhaust noise reduction system and method A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft end of the nozzle. There ... 08/18/05 - 20050178105 - Compressor and gas turbine engine A compressor having a front fan, which rotates to compress intake air, a single-stage low-pressure compressor which is disposed behind the front fan to compress intake air, and a single-stage high-pressure compressor which compresses the compressed air compressed by the low-pressure compressor; a ratio (RH/RL) of a pressure ratio (RH) ... 08/11/05 - 20050172610 - Turbojet having two counter-rotatable fans secured to a counter-rotatable low-pressure compressor The invention relates to a turbojet having two counter-rotatable fans (3, 5) at the front of an intermediate casing (2), said fans being secured to a counter-rotatable low-pressure compressor (7). The blades (14) of the rear fan (5) extend into the by-pass air flow (F2) from a wheel (15) that ... 08/11/05 - 20050172609 - Turbojet having a large bypass ratio A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its downstream end to an exhaust casing, the jacket serving to transmit forces between the intermediate casing and the exhaust ... 08/11/05 - 20050172608 - Turbo-jet engine with fan integral with a drive shaft supported by first and second bearings The present invention pertains to a turbo-jet engine comprising a fixed structure, a fan rotor integral with a drive shaft supported by a first bearing and a second bearing. It is characterized in that it comprises means forming axial retaining means for the fan rotor and/or forming an emergency bearing, ... 08/04/05 - 20050166575 - Gas turbine engine exhaust nozzle A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which extend in a generally axial direction from a downstream portion of the nozzle wherein the nozzle further comprises ... 07/21/05 - 20050155342 - Methods and apparatus for assembling gas turbine engines A method for assembling a fan platform for a gas turbine engine is provided. The method includes determining an area of vulnerability to impact and erosion damage across the platform, forming a sheet of cladding metal to substantially conform to a contour of the identified area of vulnerability of the ... 06/30/05 - 20050138914 - Turbo rocket with real carnot cycle Engine embodiments primarily designed for aircraft propulsion and power generation incorporating the Carnot cycle for efficient combustion with typical embodiments including air compressors having one or more stages with isothermal compression and including combustion and expansion chambers having in part isothermal expansion before final adiabatic expansion. ... ### FreshPatents.com Support |