Did You Know...
...that the inventor of the electric motor was a blacksmith named Thomas Davenport? Described as "a brilliantly unsuccessful inventor", Davenport invented the first rotary electric motor. In 1836 he headed out -- on foot -- from his Vermont home to file a patent application at the Patent Office in Washington, D.C. By the time he got there, he had squandered away his money and couldn't afford the $30 filing fee so he turned around and went home. When he later mailed in his application with money he'd raised, the Patent office was destroyed in a fire. He did finally get credit for his invention on Feb. 5, 1837.
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| Number | Title | Issue Date |
| 8146370 | Turbine drive system with lock-up clutch and method A pneumatically driven turbine drive system is coupled to a gas turbine engine that includes low and high pressure compressors, low and high pressure turbines, a lock-up clutch, and at least one engine accessory driven by the high pressure compressor. The pneumatica... | 04/03/2012 |
| 8074455 | Gas turbine engine with a means of driving the accessory gear box, and method of fitting said engine A twin-spool gas turbine engine including a high-pressure rotor and a low-pressure rotor, which rotors are mounted in bearings supported by an intermediate casing, at least one accessory gear box, and a drive device which drives radial and coaxial shafts for transmi... | 12/13/2011 |
| 7870744 | Attachment unit of driving shaft with tensioner nut A system for attaching the end of a shaft of a gas turbine engine engaged inside a coupling supported by a bearing is disclosed. The system includes a nut with a first thread which is screwed into the shaft and a second thread which is screwed to the coupling. Advan... | 01/18/2011 |
| 7762085 | Turbine engine having two off-axis spools with valving-enabled modulation between high and low power modes A turbine engine particularly suited for VTOL aircraft is disclosed. According to various embodiments, the core of the turbine engine includes two spools—a low pressure (LP) spool and a high pressure (HP) spool—where the LP spool is independently mounted remote ... | 07/27/2010 |
| 7762084 | System and method for controlling the working line position in a gas turbine engine compressor A system for actively controlling the working line location within a low pressure compressor. The system includes a plurality of variable inlet guide vanes that are adjusted to maintain the working line at a constant level as the low pressure compressor rotates at a... | 07/27/2010 |
| 7690206 | System for connecting an engine shaft with a retractable nut A system for fastening the end of a gas turbine engine shaft engaged inside a sleeve supported by a bearing is disclosed. The system includes a nut that is screwed at one end inside the sleeve, and is connected by a split annular ring with the shaft at the other end... | 04/06/2010 |
| 7610762 | High efficiency thermal engine The engine comprises a low pressure stage (1) and a high pressure stage (2) with two independent rotors (3,4) and associated fixed fluid preparation members (9,10,13,14), combining “compressor” means (15,16) and “expander” ... | 11/03/2009 |
| 7574867 | Hybrid microturbine for generating electricity A hybrid microturbine to produce electrical output power within a engine housing, having a combustor, and a two spool multi stage compressor wherein the 1st spool has a compressor rotor and a turbine rotor as a turbocharger and the 2nd rotor spool has an ... | 08/18/2009 |
| 7552591 | Twin spool turbine engine with power take-off means on the low-pressure and high-pressure rotors, and power take-off module for the turbine engine The invention relates to a twin spool turbine engine comprising a high-pressure rotor and a low-pressure rotor, at least one accessory gearbox, a drive means, driving coaxial transmission shafts that transmit movement to the accessory gearbox, characterized in that ... | 06/30/2009 |
| 7481062 | More electric aircraft starter-generator multi-speed transmission system A turbofan gas turbine propulsion engine includes a multi-speed transmission between the high pressure and low pressure turbines and associated high pressure and low pressure starter-generators. The multi-speed transmission reduces the operating speed range from the... | 01/27/2009 |
| 7367320 | Fuel control system for internal combustion engine A fuel control system for an internal combustion engine having an intake passage, a compressor provided in the intake passage, a throttle valve disposed downstream of the compressor, a bypass passage connecting an upstream side of the compressor to a downstream side... | 05/06/2008 |
| 7363757 | Turbine engine with semi-fixed turbine driving a receiver controlled so as to preserve a roughly constant rotation speed The invention relates to a turbine engine (1) with a semi-fixed turbine, particularly for aircraft driving a receiver (2) controlled so as to preserve a roughly constant rotation speed. The turbine engine, in particular via a gear system (20), d... | 04/29/2008 |
| 7353647 | 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 ... | 04/08/2008 |
| 7350619 | Auxiliary power unit exhaust duct with muffler incorporating an externally replaceable acoustic liner Methods and apparatus are provided for an exhaust duct having an externally replaceable acoustic liner. The exhaust duct includes a forward section that is configured to be axially coupled with a bulkhead collar on the aircraft, a body section that is coupled to the... | 04/01/2008 |
| 7334755 | Tandem rotor wing and tandem fixed wing aircraft Aircraft comprising an airframe having a fuselage, at least two fixed wing sets. A first fixed wing set of the fixed wing sets is positioned closer to a forward end of the fuselage than a second fixed wing set and the second fixed wing set is positioned closer to th... | 02/26/2008 |
| 7325401 | Power conversion systems Power generation systems and methods are provided with features directed to various innovations including ones relating to the conversion of concentrated solar and biomass energy to electricity, load-shifting of electrical power supply systems, gas turbine devices a... | 02/05/2008 |
| 7328098 | Determining bleed valve failures in gas turbine engines The invention detects gas turbine bleed valve position discordances. The invention derives a modified exhaust gas temperature derivative as the predictive criteria in conjunction with a control logic to determine bleed valve position discordances that may indicate a... | 02/05/2008 |
| 7254951 | High compression gas turbine with superheat enhancement A system and method for adding superheat to the hot process gas at the discharge of a compressor drive turbine of a high compression ratio gas turbine or aviation gas turbine. The superheat brings the temperature ratio (T2/T1) of the power output turbine into equali... | 08/14/2007 |
| 7251989 | Method and device for operating an internal combustion engine A method and a device are provided for diagnosing operation of an internal combustion engine having a compressor for compressing air supplied to the internal combustion engine, which method and device permit diagnosis of as many error patterns in the compressor oper... | 08/07/2007 |
| 7231770 | Onboard supplemental power system at varying high altitudes Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a super... | 06/19/2007 |
| 7229254 | Turbine blade with a reduced mass The invention relates to a turbine comprising at least four stages and to the use of a rotor blade with a reduced mass. In prior art, rotor blades in the fourth stage of a gas turbine, which exceed 50 cm in length, cause problems relating to mechanical strength, as ... | 06/12/2007 |
| 7200987 | Off-axis pulse detonation configuration for gas turbine engine The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation ... | 04/10/2007 |
| 7111462 | Onboard supplemental power system at varying high altitudes Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a super... | 09/26/2006 |
| 7104071 | Method for operating a gas turbine group A gas turbine group is provided with at least one cooling apparatus for cooling the working medium before and/or during the compression. The cooling power of the cooling apparatus can be adjusted by suitable means. A controller controls the cooling power of the cool... | 09/12/2006 |
| 7103515 | Method for analyzing turbine engine disks The present invention provides, in one embodiment, a method for automatically analyzing an article of manufacture comprising the steps of a) providing a master model and a context model specification; b) creating a context model from the master model and the context... | 09/05/2006 |
| 7096674 | High thrust gas turbine engine with improved core system 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 and ... | 08/29/2006 |
| 7093446 | Gas turbine engine having improved core system 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 drive shaft; a booster compressor positioned downstream of the fan se... | 08/22/2006 |
| 7078825 | Microturbine engine system having stand-alone and grid-parallel operating modes A microturbine engine that includes a compressor that is operable to provide a flow of compressed air. The compressed air flows through a recuperator where it is preheated before delivery to a combustor. The preheated compressed air mixes with a fuel and is combuste... | 07/18/2006 |
| 7073335 | Gas storage power station The present invention relates to a gas storage power station (1) having a turbine group (3) and a compressor group (4). The turbine group (3) has at least one turbine (5, 6) and a generator (10). During normal operation of t... | 07/11/2006 |
| 7059830 | Axial-flow serial fan This specification discloses a serial fan comprising a plurality of rotor vanes, one or more supports and a frame. Each of the rotor vanes comprises an inlet, an outlet, and one or more blades. Each support supports at least one of the rotor vanes so that the corres... | 06/13/2006 |
| 7055330 | Apparatus for driving an accessory gearbox in a gas turbine engine A mechanical drive system for an accessory gearbox of a gas turbine engine is provided. The gas turbine engine includes a high-pressure drive shaft and a low-pressure drive shaft. The mechanical drive system includes a tower shaft and a lay shaft. The tower shaft is... | 06/06/2006 |
| 7045913 | Microturbine engine system A microturbine engine that includes a compressor that is operable to provide a flow of compressed air. The compressed air flows through a recuperator where it is preheated before delivery to a combustor. The preheated compressed air mixes with a fuel and is combuste... | 05/16/2006 |
| 7025563 | Stator vane assembly for a gas turbine engine A low-pressure compressor exit stator assembly for a gas turbine includes a multiple of vanes mounted between a full hoop outer shroud and an inner shroud. The outer shroud and inner shroud are mounted to the intermediate case structure. A seal is located between th... | 04/11/2006 |
| 7007484 | Methods and apparatus for operating gas turbine engines A method for operating a gas turbine engine including a compressor, combustor, and turbine is provided that includes channeling compressed airflow from the compressor to a heat exchanger having a working fluid circulating within, channeling the working fluid from th... | 03/07/2006 |
| 6971236 | Domestic combined heat and power unit A DCHP unit with a Stirling engine (1), a burner (3) and a supplementary burner (11). Water is heated by exhaust gas from the Stirling engine and from the supplementary burner. If a sensor (18) detects that the water temperature has risen... | 12/06/2005 |
| 6968701 | Engine integrated auxiliary power unit The present invention relates to an engine integrated auxiliary power unit. The engine comprises a high pressure spool which includes a high pressure compressor connected to a high pressure turbine and a low pressure spool which includes a low pressure compressor co... | 11/29/2005 |
| 6941754 | Heating appliance The heating appliance, and particularly a dchp system, comprising two burners (3, 17). A splitter valve (23) splits a stream of air (24) into two streams, one for each burner. Combustible fuel is mixed with the air. A controller controls the com... | 09/13/2005 |
| 6935831 | Methods and apparatus for operating gas turbine engines A method for operating a gas turbine engine including a first compressor, a second compressor, a combustor and a turbine, coupled together in serial flow arrangement. The method includes channeling compressed airflow discharged from the first compressor to a heat ex... | 08/30/2005 |
| 6901759 | Method for operating a partially closed, turbocharged gas turbine cycle, and gas turbine system for carrying out the method A gas turbine system includes a gas turbine (1, 2, 3) having a compressor (1) and a turbine (2), which via a common shaft (3) drive a generator (4), and a combustion chamber (6), the exit of which is connected to the entry t... | 06/07/2005 |
| 6895741 | Differential geared turbine engine with torque modulation capability A method and apparatus for controllable distribution of power from a turbine of a gas turbine engine between two rotatable loads of the gas turbine engine, comprises transferring a shaft power of the turbine to the respective rotatable loads using differential geari... | 05/24/2005 |
