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"That the automobile has practically reached the limit of its development is suggested by the fact that during the past year no improvements of a radical nature have been introduced."
Scientific American ; Jan. 2 edition, 1909
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| Number | Title | Issue Date |
| 8028512 | Active combustion control for a turbine engine A combustion control system for a turbine engine is disclosed. The combustion control system includes a fuel injector having a main fuel supply and pilot fuel supply coupled to a combustor of the turbine engine. The combustion control system also includes a sensor c... | 10/04/2011 |
| 8015825 | Fast acting aircraft engine bleed air check valve An engine air supply system includes an air source, which is a gas turbine engine in one example. A component, such as an environmental control system component, is interconnected to the air source by a conduit that includes a supply flow direction. A check valve is... | 09/13/2011 |
| 8006479 | Thrust reversing variable area nozzle A gas turbine engine system includes a first nozzle section associated with a gas turbine engine bypass passage and a second nozzle section that includes a plurality of positions relative to the first nozzle section. In at least one of the positions, there is a gap ... | 08/30/2011 |
| 8001787 | Transition support system for combustion transition ducts for turbine engines A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition ... | 08/23/2011 |
| 8001786 | Combustor of a gas turbine engine A combustor of gas turbine engine, including: a fuel spray portion that sprays fuel to create a diffusion combustion region in a combustion chamber, the fuel spray portion including a fuel atomizing portion that atomizes the fuel, and a diffusion passage portion dis... | 08/23/2011 |
| 8001762 | Method and device to increase thrust and efficiency of jet engine A method and device for adding special substances to the gaseous outflow of the jet engine in order to create a “virtual wall” of increased pressure zone behind the jet engine nozzle which can serve as a support for the jet engine gas outflow to push against, th... | 08/23/2011 |
| 7451601 | Method of tuning individual combustion chambers in a turbine based on a combustion chamber stratification index A method, system and software for reducing combustion chamber to chamber variation in a multiple-combustion chamber turbine system comprising sensing dynamic combustion pressure tones emitted from combustion chambers in a multiple combustion chamber turbine and dete... | 11/18/2008 |
| 7451599 | Fuel manifold inlet tube An inlet tube supplies fuel to a manifold of a combustor in a gas turbine engine, the manifold defining a manifold plane. The inlet tube comprises a tube body having a channel providing fluid flow communication between first and second ends of the tube body. At leas... | 11/18/2008 |
| 7451602 | Methods and apparatus for injecting fluids into turbine engines A method facilitates operating a gas turbine engine. The method comprises supplying steam and primary fuel to a chamber within a nozzle, mixing the primary fuel and steam within the chamber, and discharging the mixture into a combustor from a plurality of circumfere... | 11/18/2008 |
| 7448215 | Combustion chamber for a gas turbine engine A combustion chamber suitable for a gas turbine engine is provided with at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the chamber interior. The resonator neck is provided with at least cooling holes extend... | 11/11/2008 |
| 7448220 | Torque control for starting system A start system for a gas turbine engine delivers starter current according to a schedule selected according to measured rotational speed and oil temperature of the gas turbine engine. ... | 11/11/2008 |
| 7448217 | Power plant A combined cycle power plant comprises a gas turbo group and a water/steam circuit A liquid atomization device is arranged, upstream of the compressor, in the intake duct of the gas turbo group. The liquid under pressure, which is intended to be injected into the co... | 11/11/2008 |
| 7441398 | NOx adjustment system for gas turbine combustors An embodiment may comprise a system for controlling NOx emissions from a turbine having combustion chambers. The system may comprise a center fuel flow and a plurality of outer fuel flows for each of a plurality of combustion chambers. An outer fuel flow is set to a... | 10/28/2008 |
| 7437871 | Automatic engine protection system for use when electronic parts of a control system are exposed to overtemperature conditions An automatic engine protection system for use when electronic parts of the control system are exposed to overtemperature conditions. A thermally sensitive component, such as an engine electronic control or an electronic overspeed control, is mounted on the engine. A... | 10/21/2008 |
| 7434406 | Drive for using a direct driven generator to start a counter-rotating multi-spool gas turbine engine A drivetrain for a multi-spool counter rotating gas turbine engine may include a lay shaft for connecting a power turbine shaft of the engine with a gas generator shaft of the engine when the drivetrain is in engine start mode. In normal operation mode, an actuator ... | 10/14/2008 |
| 7430850 | Bifurcated oil scavenging bearing compartment within a gas turbine engine An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially ... | 10/07/2008 |
| 7428817 | Premix burner with a swirl generator delimiting a conical swirl space and having sensor monitoring A premix burner is disclosed, with a swirl generator which delimits a conical swirl space and provides at least two conical part shells which are arranged, offset to one another, along a burner axis, mutually enclose in each case air inlet slits running longitudinal... | 09/30/2008 |
| 7428818 | System and method for augmenting power output from a gas turbine engine The present invention discloses a method and system for augmenting shaft output of stationary gas turbines that can be used in multiple modes of operation. The system comprises a washing unit (25, 27, 28) adapted to inject a spray (26) of atomized liqu... | 09/30/2008 |
| 7421835 | Air-staged reheat power generation system A two-stage power generation system having a compressed air source with two compressed air outlets, one of which provides compressed air to the first stage of power generation and the other of which provides compressed air to the second stage of power generation. Al... | 09/09/2008 |
| 7418814 | Dual expander cycle rocket engine with an intermediate, closed-cycle heat exchanger A dual expander cycle (DEC) rocket engine with an intermediate closed-cycle heat exchanger is provided. A conventional DEC rocket engine has a closed-cycle heat exchanger terhamlly coupled thereto. The heat exchanger utilizes heat extracted from the engine's fuel ci... | 09/02/2008 |
| 7406828 | Power augmentation of combustion turbines with compressed air energy storage and additional expander with airflow extraction and injection thereof upstream of combustors A combustion turbine power generation system (10) includes a combustion turbine assembly (11) including a main compressor (12) constructed and arranged to receive ambient inlet air, a main expansion turbine (14) operatively associated wit... | 08/05/2008 |
| RE39796 | Method of eliminating mach waves from supersonic jets A method and device for reducing the amount of noise generated by a supersonic jet engine is provided. The method creates an envelope of air around the supersonic jet exhaust. The temperature and velocity of this envelope is controlled to eliminate or reduce the for... | 08/28/2007 |
| 7188475 | Starting and controlling speed of a two spool gas turbine engine Two spool gas turbine engines are often used to drive variable speed loads, such as an electric generator, or the fan/propeller of aircraft engines. The gas turbine engine must be designed to withstand transient speed and temperature conditions which are encountered... | 03/13/2007 |
| 7174719 | Gas turbine engine with seal assembly A gas turbine engine includes an interstage seal assembly positioned in a plenum between the compressor section and turbine section. The seal assembly includes an annular seal member positioned in the plenum adjacent to the compressor section for restraining a fluid... | 02/13/2007 |
| 7168235 | Highly supercharged regenerative gas turbine The present invention comprises a highly supercharged, regenerative gas-turbine system. The gas turbine comprises a compressor, a regenerator, a combustor, and an expander. A pre-compressor pressurizes air going into the compressor section of the gas turbine. A cool... | 01/30/2007 |
| 7168254 | Control logic for fuel controls on APUs Conventional auxiliary power units (APUs) may experience over-temperature shutdowns when attempting to start them at high altitudes. Further, such conventional APUs may also experience overspeed conditions when a generator load is removed during on-speed operations.... | 01/30/2007 |
| 7168253 | Monobloc flameholder arm for an afterburner device of a bypass turbojet A support arm (13) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together ... | 01/30/2007 |
| 7165405 | Fully premixed secondary fuel nozzle with dual fuel capability A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a mo... | 01/23/2007 |
| 7162874 | Apparatus and method for gas turbine engine fuel/air premixer exit velocity control A gas turbine engine with a single stage combustor includes an external premixer to provide premixed fuel/compressed air to the combustor as well as compressed air for dilution; and an automatic controller to provide feedback control of the compressed air flow and f... | 01/16/2007 |
| 7162875 | Method and system for controlling fuel supply in a combustion turbine engine In order to regulate fuel flow to the combustor (36) of the combustion turbine engine (10) having a primary combustion zone (64) and at least one further combustion zone, the temperature of the inlet and outlet of the combustor (36) are d... | 01/16/2007 |
| 7162876 | Ejector for cooling air supply pressure optimization A system for optimizing cooling air supply pressure includes a high pressure fluid source which receives bleed air from the exit of a high pressure compressor and a nozzle and ejector assembly for supplying fluid to a point of use at a pressure sufficient to maintai... | 01/16/2007 |
| 7155898 | Thrust vector control system for a plug nozzle rocket engine A thrust vector control system for a plug nozzle rocket engine for propelling and maneuvering a vehicle is disclosed. The plug nozzle rocket engine includes a housing having a nozzle throat, a plug disposed within the housing and positioned within the nozzle throat ... | 01/02/2007 |
| 7152409 | Dynamic control system and method for multi-combustor catalytic gas turbine engine According to one aspect, a method of controlling a multi-combustor catalytic combustion system is provided for determining a characteristic of a fuel-air mixture downstream of a preburner associated with a catalytic combustor and adjusting the fuel flow to the prebu... | 12/26/2006 |
| 7146795 | System and method for producing injection-quality steam for combustion turbine power augmentation The present invention is a combustion turbine assembly connected to a steam generator which utilizes deaerated potable water. The steam formed by the steam generator may be combined with air and injected into the combustor of the combustion turbine assembly to incre... | 12/12/2006 |
| 7146794 | Gas turbine installation Disclosed is a gas turbine power generating system capable of achieving a high output power and a high power generating efficiency under conditions with a small amount of supplied water and less change in design of a gas turbine. A fine water droplet spraying... | 12/12/2006 |
| 7143581 | Gas turbine plant A gas turbine plant comprises an air compressor, gas turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel syste... | 12/05/2006 |
| 7143584 | Gas turbine apparatus A gas turbine apparatus is provided which comprises a turbine, a combustor for burning a mixture of air and fuel and providing the turbine with a combustion gas to drive it, a generator connected to the turbine to receive rotational force therefrom to generate elect... | 12/05/2006 |
| 7143582 | Method for operation of a burner and burner in particular for a gas turbine The invention relates to a method for operation of a burner, whereby a mixture used for burning is supplied to the burner in a two-stage process. In a first step atomised water is mixed with combustion air and said mixture is mixed with a fuel in a second step and t... | 12/05/2006 |
| 7143585 | Turbine power plant, installation process and removal process of the turbine power plant A turbine power plant includes power generation apparatuses divided into a plurality of modules, a common base mounting thereon the power generation apparatuses and a supporting apparatus for supporting the common base. The common base is constructed so as to be com... | 12/05/2006 |
| 7140175 | Throttle control device in particular for turbine aero engine test bench The invention concerns a throttle control device for an aircraft turbine engine. It comprises a control assembly acting on the native command of the turbine engine (MT1–MT3) as a function of a manual input defined by a pilot control element (1... | 11/28/2006 |
