| Entries |
| Document | Title | Date |
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| 20080245050 | 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, coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the propelling gas turbine engine, such that at least a portion of the airflow entering the propelling gas turbine engine is extracted from the propelling gas and channeled to the auxiliary engine for generating power, and coupling a modulating valve in flow communication to the propelling gas turbine engine to control the flow of airflow from the propelling gas turbine engine to the auxiliary engine, wherein the modulating valve is selectively operable to control an extraction point of airflow from the propelling gas turbine engine. | 10-09-2008 |
| 20090000265 | Gas Turbines with Multiple Gas Flow Paths - An representative gas turbine includes: a first annular gas flow path; a second annular gas flow path located radially outwardly from the first gas flow path; in series order, a multi-stage fan, radially inboard portions of a first set of high pressure compressor blades, a second set of high pressure compressor blades, a combustion section and a high pressure turbine, positioned along the first gas flow path; and in series order, the multi-stage fan and radially outboard portions of the first set of high pressure compressor blades, positioned along the second gas flow path such that the inboard portions of the first set of high pressure compressor blades, the second set of high pressure compressor blades, the combustion section and the high pressure turbine are not positioned along the second gas flow path. | 01-01-2009 |
| 20090025364 | Multi-Stage Compressor, Air-Separating Apparatus Comprising Such a Compressor, and Installation - A multi-stage compressor, for an air separation unit comprising such a compressor and to an installation is provided. | 01-29-2009 |
| 20090056302 | COMPONENT VENTILATION AND PRESSURIZATION IN A TURBOMACHINE - A dual-flow turbomachine ( | 03-05-2009 |
| 20090173056 | METHODS AND APPARATUS FOR OPERATING GAS TURBINE ENGINES - A gas turbine engine assembly includes at least one propelling gas turbine engine and an auxiliary engine used for generating power. The propelling gas turbine engine includes a fan assembly and a core engine downstream from said fan assembly. The core engine includes a compressor, a high pressure turbine, a low pressure turbine, and a booster turbine coupled together in serial-flow arrangement such that the booster turbine is rotatably coupled between the high and low pressure turbines. The auxiliary engine includes at least one turbine and an inlet. The inlet is upstream from the high pressure turbine and is in flow communication with the propelling gas turbine engine core engine, such that a portion of airflow entering the propelling engine is extracted for use by the auxiliary engine. | 07-09-2009 |
| 20090193782 | POWER GENERATING TURBINE SYSTEMS - A power generating turbine system that may include an axial compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through a turbine. The turbine may include a high-pressure turbine section and a low-pressure turbine section. The high-pressure turbine section may be coupled via a first shaft to the axial compressor such that in operation the high-pressure turbine section drives the axial compressor. And, the low-pressure turbine section may be coupled via a second shaft to a low-speed generator such that in operation the low-pressure turbine section drives the low-speed generator. | 08-06-2009 |
| 20090193783 | POWER GENERATING TURBINE SYSTEMS - A power generating turbine system that may include: 1) a turbine that includes two sections, a high-pressure turbine section and a low-pressure turbine section that each reside on a separate shaft; 2) an axial compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through the turbine, the axial compressor comprising a low-pressure compressor section and a high-pressure compressor section; 3) a four-pole generator; 4) a first shaft that couples the high-pressure turbine section to the high-pressure compressor section such that, in operation, the high-pressure turbine section drives the high-pressure compressor; and 5) a second shaft that couples the low-pressure turbine section to the four-pole generator and the low-pressure compressor such that, in operation, the low-pressure turbine section drives the four-pole generator and the low-pressure compressor. | 08-06-2009 |
| 20090193784 | POWER GENERATING TURBINE SYSTEMS - A power generating turbine system that may include: 1) a turbine that includes two sections, a high-pressure turbine section and a low-pressure turbine section that each reside on a separate shaft; 2) an axial compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through the turbine; 3) a two-pole generator; 4) a four-pole generator; 5) a first shaft that couples the high-pressure turbine section to the axial compressor and the two-pole generator such that, in operation, the high-pressure turbine section drives the axial compressor and the two-pole generator; and 6) a second shaft that couples the low-pressure turbine section to the four-pole generator such that, in operation, the low-pressure turbine section drives the four-pole generator. | 08-06-2009 |
| 20090193785 | POWER GENERATING TURBINE SYSTEMS - A power generating turbine system that includes: a turbine that includes three sections, a high-pressure turbine section, a mid-pressure turbine section, and a low-pressure turbine section that each reside on a separate shaft; 2) an axial compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through the turbine, the axial compressor comprising a high-pressure compressor section and a low-pressure compressor section; 3) a two-pole generator; 4) a four-pole generator; 5) a first shaft that couples the high-pressure turbine section to the high-pressure compressor section such that, in operation, the high-pressure turbine section drives the high-pressure compressor section; 6) a second shaft that couples the mid-pressure turbine section to the high-pressure compressor section and the two-pole generator such that, in operation, the mid-pressure turbine section drives the high-pressure compressor section and two-pole generator; and 7) a third shaft that couples the low-pressure turbine section to the four-pole generator such that in operation the low-pressure turbine section drives the four-pole generator. | 08-06-2009 |
| 20090293445 | Gas turbine engine with intermediate speed booster - A gas turbine engine having speed an intermediate stage booster configured to provide speed change to a boost compressor. The boost compressor and fan stage are driven by a low pressure turbine; the fan stage rotates with the low pressure turbine shaft and the boost compressor rotates counter to the low pressure turbine shaft. The intermediate speed booster has an epicyclic gear train that includes an outer annulus, a sun gear, and a planetary gear, and may be engaged by a clutch in some embodiments. | 12-03-2009 |
| 20090301054 | TURBINE SYSTEM HAVING EXHAUST GAS RECIRCULATION AND REHEAT - While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims. | 12-10-2009 |
| 20090320438 | TWO-SHAFT GAS TURBINE - Provided is a two-shaft gas turbine with improved reliability that improves output power and efficiency and is stably operated by establishing a balance between the driving force of a compressor and the output power of a high-pressure turbine in the case where the two-shaft gas turbine is applied to a system in which the flow rate of fluid flowing into a combustor is increased compared with a simple cycle gas turbine. | 12-31-2009 |
| 20100024380 | SYSTEM AND METHOD FOR USE IN A COMBINED CYCLE OR RANKINE CYCLE POWER PLANT USING AN AIR-COOLED STEAM CONDENSER - A system for use in a combined cycle or rankine cycle power plant using an air-cooled steam condenser is provided and includes a steam turbine from which first and second steam supplies are outputted at high and low respective pressures, an air-cooled condenser configured to fluidly receive and to air-cool at least the first steam supply via a supply of air, a cooling tower from which a first water supply is cycled, a chilling coil through which a second water supply water is cycled to thereby cool the supply of air, and a vapor-absorption-machine (VAM) configured to fluidly receive the second steam supply and the first water supply by which a refrigeration cycle is conducted to thereby cool the second water supply. | 02-04-2010 |
| 20100058731 | ASSISTANCE DEVICE FOR TRANSIENT ACCELERATION AND DECELERATION PHASES - A turbine engine, for example for a helicopter, including a gas generator and a free turbine driven in rotation by the gas flow generated by the gas generator. The turbine engine further includes a motor/generator coupled to a shaft of the gas generator, to provide a quantity of additional rotational kinetic energy to the shaft during a stage of turbine engine acceleration, or to draw a quantity of rotational kinetic energy from the shaft during a stage of turbine engine deceleration. | 03-11-2010 |
| 20100083631 | Hybrid propulsive engine including at least one independently rotatable turbine stator - One aspect relates to a hybrid propulsive technique, comprising providing a flow of a working fluid through at least a portion of an at least one jet engine. The at least one jet engine includes an at least one turbine section, wherein the at least one turbine section includes at least one turbine stage. The at least one turbine stage includes an at least one turbine rotor and an at least one independently rotatable turbine stator. The hybrid propulsive technique further involves extracting energy at least partially in the form of electrical power from the working fluid, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique further comprises rotating an at least one at least one independently rotatable turbine stator at least partially responsive to the converting the at least a portion of the electrical power to torque. | 04-08-2010 |
| 20100089019 | GAS TURBINE ENGINE - A gas turbine engine having three shafts connecting respective high, intermediate and low-pressure turbines and compressors is characterised by an intermediate pressure turbine that includes two rotor stages. | 04-15-2010 |
| 20100115912 | PARALLEL TURBINE ARRANGEMENT AND METHOD - Disclosed is a parallel turbine arrangement including a compressor and a first turbine in operable communication with the compressor and a second turbine in operable communication with the compressor. | 05-13-2010 |
| 20100199627 | Gas Turbo Set and Method for Controlling a Gas Turbo Set - A gas turbo set including a first turbine, a second turbine, and a combustion chamber connected between the first and second turbines and operated by auto-ignition is provided. The turbines and the combustion chamber are located on a common shaft that may be rotated about an axis. To increase the efficiency of the gas turbo set, the outer periphery of the second turbine is at a greater distance from the axis than that of the first turbine, leading to a reduction in the size and/or the number of turbine blades. | 08-12-2010 |
| 20100257837 | SYSTEMS INVOLVING HYBRID POWER PLANTS - A system comprises, a first heat recovery steam generator (HRSG) having an upstream intake duct portion, a first gas turbine engine connected to a first exhaust duct operative to output exhaust from the first gas turbine engine to the upstream intake duct portion of the first HRSG, and a second gas turbine engine connected to a second exhaust duct operative to output exhaust from the second gas turbine engine to the upstream intake duct portion of the first HRSG. | 10-14-2010 |
| 20110219741 | DETERMINING FAN PARAMETERS THROUGH PRESSURE MONITORING - A method for determining the speed of at least one rotating fan, such as a propeller, through sensing pressure waves generated by the blades of the fan. An apparatus operable to execute the method is also disclosed. The apparatus includes a fan having a hub portion and a plurality of blades extending radially outward from the hub portion. The apparatus also includes an engine operable to rotate the fan about an axis of rotation. The apparatus also includes a sensor spaced from the fan along the axis of rotation. The sensor is positioned to sense at least one physical condition that is external of the engine and is changed by rotation of the plurality of blades. The sensor is operable to emit a signal corresponding to at least one physical condition. The apparatus also includes a processor operably engaged with the engine and the sensor. The processor is operable to receive the signal from the sensor and change the operation of the engine in response to the signal to change a speed of the fan. | 09-15-2011 |
| 20120023891 | GAS TURBINE ENGINE WITH NOISE ATTENUATING VARIABLE AREA FAN NOZZLE - A rotary-wing aircraft includes a retractable port movable between a closed position and an open position to selectively control flow of combustion gases into a bypass passage to change a power distribution between a rotor system and a secondary propulsion system. | 02-02-2012 |
| 20120159922 | TOP CYCLE POWER GENERATION WITH HIGH RADIANT AND EMISSIVITY EXHAUST - The present invention generally relates to power generation methods and secondary processes requiring high radiant and emissivity homogeneous combustion to maximize production output. In one embodiment, the present invention relates to a top cycle power generator with combustion exhaust modified to have radiant flux in excess of 500 kW per square meter and emissivity greater than 0.90, and supercritical CO2 power generating cycle to maximize exergy efficiency. | 06-28-2012 |
| 20130192191 | GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES - A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section. | 08-01-2013 |
| 20130205747 | GAS TURBINE ENGINE WITH MODULAR CORES AND PROPULSION UNIT - A separate propulsion unit incorporating a free turbine and a fan receives gases from a plurality of core engines. The core engines each include a compressor, a turbine and a combustion section. The core engines in combination pass gases across the free turbine. A method is also disclosed. | 08-15-2013 |
| 20130247539 | MULTI-SHAFT POWER EXTRACTION FROM GAS TURBINE ENGINE - A gas turbine engine power generation system includes first and second spools respectively connected to first and second turbine sections. First and second shafts respectively are coupled to the first and second spools. First and second generators respectively are configured to provide first and second electrical powers. A generator gearbox operatively connects the first and second shafts respectively to the first and second generators. An electrical summing device is electrically connected to the first and second generators and is configured to receive the first and second electrical powers and combine the first and second electrical powers to produce a common output power. | 09-26-2013 |
| 20130255219 | GEARED TURBOFAN WITH THREE CO-ROTATING TURBINES - A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan rotor through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine rotate in the same direction. | 10-03-2013 |
| 20140196432 | THE TESLA TWIN TURBINES COMBUSTION ENGINE MODULE - A new type of engine module is described based on the Tesla turbine. Our Tesla Twin Turbines Combustion Engine Module comprises of two Tesla turbines welded together, forming a combustion chamber in between. The combustion chamber includes an air-fuel mixture inlet and an ignition inlet. Fuel-air mixture is injected through the air-fuel inlet into the combustion chamber which is ignited by an ignition device. The high temperature combustion gas flow in opposite directions across 2 stacks of evenly spaced smooth parallel discs, transferring energy into rotating the discs via the mechanism of boundary layer laminar flow interaction. The pair of rotating stacks of discs rotates a pair of rods. The gas exits through exhaust holes or openings adjacent to the pair of rods. The rotating rods can be used to drive generators or do useful works. | 07-17-2014 |
| 20140250860 | MULTI-SHAFT GAS TURBINE ENGINE - A gas turbine engine is disclosed with a first spool having a first turbine connected to a first compressor through a first rotatable shaft; a second spool having a second turbine connected to a second compressor through a second rotatable shaft; and a gearbox having a power input port coupled to each of the first and second shafts and a power output port connected to a third shaft, wherein the rotational speed of the third shaft is lower than the rotational speed of each of the first and second shafts. | 09-11-2014 |
| 20140373505 | MULTI-ENGINE POWER PLANT HAVING AN EMERGENCY FLUID INJECTION SYSTEM, AND AN AIRCRAFT - A power plant ( | 12-25-2014 |
| 20150013300 | METHOD AND APPARATUS FOR CAPTURING CARBON DIOXIDE DURING COMBUSTION OF CARBON CONTAINING FUEL - A boiler system having a series of boilers. Each boiler includes a shell having an upstream end, a downstream end, and a hollow interior. The boilers also have an oxidizer inlet entering the hollow interior adjacent the upstream end of the shell and a fuel nozzle positioned adjacent the upstream end of the shell for introducing fuel into the hollow interior of the shell. Each boiler includes a flue duct connected to the shell adjacent the downstream end for transporting flue gas from the hollow interior. Oxygen is delivered to the oxidizer inlet of the first boiler in the series. Flue gas from the immediately preceding boiler in the series is delivered through the oxidizer inlet of each boiler subsequent to the first boiler in the series. | 01-15-2015 |
| 20150121838 | CONJOINED REVERSE CORE FLOW ENGINE ARRANGEMENT - A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another. | 05-07-2015 |
| 20150292410 | Gas Turbine Engine with Plural Accessory Air Paths - A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications. | 10-15-2015 |
| 20150316001 | Pulse Detonation Engine with Variable Control Piezoelectric Fuel Injector - A pulse detonation engine including one or more fuel injectors comprising one or more piezoelectric driving stacks wherein a flow control member of each injector is driven directly by the one or more piezoelectric stacks without additional amplification means or interposing elements while a flow area of the nozzle is variably adjustable to deliver controlled flow rates in a desired flow profile to improve engine performance and reduce emissions. The pulse detonation engine configured to support variable mission and operational requirements including delivery of required thrust using specific fuel types and with power and performance of the pulse detonation engine variably adaptable. The fuel injectors associated with the pulse detonation engine configure to deliver specified flow rates with minimal linear movement of the flow control member. The injector and drive electronics configured to deliver higher frequency operation and response with increased operational stability. | 11-05-2015 |
| 20160061045 | DECOUPLED GAS TURBINE ENGINE - A decoupled gas turbine engine includes a high spool assembly and a low spool assembly each having a rotational axis that are spaced from one-another. The engine further includes a combustor that may have a centerline spaced from the rotational axes of each spool assembly. Turning ducts of the engine are configured to re-direct airflow from one spool assembly to the next and/or between one spool assembly and the combustor. | 03-03-2016 |
| 20160076445 | GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE - A gas turbine engine comprises a fan includes a plurality of fan blades rotatable about an axis. A compressor section includes at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° F. and about 1500° F. A combustor is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis. | 03-17-2016 |
| 20160153356 | GEARED TURBOFAN ENGINE GEARBOX ARRANGEMENT | 06-02-2016 |
| 20160195019 | TURBINE SECTION SUPPORT FOR A GAS TURBINE ENGINE | 07-07-2016 |
