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Matches 851 - 900 out of 8,882

Document Document Title
WO/2009/043487A1
The invention relates to a multi-stage supercharging group (10, 10', 10') for an internal combustion engine for charging the internal combustion engine with a fluid, particularly an exhaust gas, comprising at least one high-pressure turb...  
WO/2009/040112A2
The invention refers to a power supplying device or system for aeronautics, having a hydrocarbon supply (400) for supplying an engine (400) with hydrocarbon fuel and a hydrogen supply (100) having a fuel reformer (120) for producing hydr...  
WO/2009/033944A1
The invention relates to a method for the computer-aided control and/or regulation of a technical system. The method involves the use of a cooperative learning method and artificial neural networks. In this context, feed-forward networks...  
WO/2009/030856A2
The invention relates to a device for motorized aircraft comprising at least one avionic component (300) positioned in the said aircraft, at least one engine interface (310) positioned in the said aircraft and at least one engine control...  
WO/2009/031552A1
In a heating apparatus for heating the air to be sucked into a gas turbine by a heat exchanger, the temperature fluctuation of the heated air is suppressed even in the period, for which a steam source to be fed to the heat exchanger is c...  
WO/2009/018532A1
A plasma generator for delaying the onset of rotation stall by tip gap flow control in, for example, an axial flow compressor is disclosed. The tip gap flow control system includes a housing surrounding a rotor of blades and having an in...  
WO/2009/015868A2
Disclosed is a method for determining emission values of a gas turbine, comprising the following steps: a test run is performed on the gas turbine; operational parameters (T0, T4, T4*, NGG, power) of the gas turbine are determined during...  
WO/2009/016665A1
A gas turbine plant control device has control means for selectively controlling an exhaust gas temperature (TS) of the turbine (11) on the basis of at least two distinct reference values (TSRIFV0, TSRIFVI, TSRIFV2... TSRIFVn) related to...  
WO/2009/013136A1
The invention relates to a method for operating a combustion device (10) which comprises at least one combustion chamber (11) with a plurality of burners (B1,..,Bn) which act in parallel and which generate in each case one flame (F1,..,F...  
WO/2009/004143A2
According to the invention, the hot flow nozzle includes a single skin (14s) conformed for promoting the cold flow (10) circulation when the aircraft including said turboshaft engine is in a cruise flight mode.  
WO/2008/138797A3
A method for pressure dynamics reduction within a gas turbine engine with a number of combustion chambers (1), where a pilot fuel spilt is defined for each combustion chamber, is provided, comprising the steps of measuring the pressure v...  
WO/2008/124327A3
Embodiments of systems and methods for tuning a turbine are provided. In one embodiment, a method may include receiving at least one of a measured operating parameter or a modeled operating parameter of a turbine during operation; and tu...  
WO/2008/105907A3
A control system 10 and method of controlling a propeller aircraft engine 20 during takeoff limits the amount of engine power developed at the very beginning of the takeoff in order to maximize thrust and minimize rollout distances. The ...  
WO/2008/134097A3
A system and method implements machine performance, most preferably for gas ' turbine engines. The system and method implement a control law (118) that ' receives sensed operational parameter feedback signals (124). For each sensed engin...  
WO/2008/097269A3
A method includes controlling an aircraft during descent, and controlling the engine pressure ratio of a jet engine so that the engine has a substantially equal pressure at the exhaust, and at the front of the engine during the descent.  
WO/2008/152964A1
It is possible to reduce the manufacturing cost and the running cost. A plurality of combustion devices are arranged in an annular shape in a combustion device casing. A casing (22) containing a combustion oscillation detection device (2...  
WO/2008/149731A1
A gasifying agent supply passage (A) from an axial flow compressor (21) for increasing the pressure of the gasifying agent to a gasification furnace (2) is branched, and a gasifying agent bypass passage (D) provided with an escape pressu...  
WO/2008/147260A1
The invention relates to a device for moving a plurality of hatches (202), spaced at intervals from one another in a circumferential direction of a gas turbine engine, between a first position and a second position, wherein each of the h...  
WO2008000459A8
Disclosed is a turbo engine comprising a first process control element (5), a second process control element (8), and a test system for testing the first process control element, the first process control element and the second process c...  
WO/2008/142020A1
The invention relates to a gas turbo set (2) comprising a first and a second turbine (4, 6) in addition to a combustion chamber (8) connected therebetween and operating by auto-ignition. The turbines (4, 6) and the combustion chamber (8)...  
WO/2008/139536A1
A natural gas liquefaction plant that while effecting cost reduction, can realize over-load driving of gas turbine power generator and attains stabilization of plant power source and accordingly stabilization of plant operation; and a me...  
WO/2008/139535A1
A natural gas liquefaction plant comprises a liquefier (11) for liquefying a natural gas (111) by exchanging heat with refrigerants (135, 145, 155); refrigerant compressors (13, 14, 15) for compressing the refrigerants (134, 144, 154) su...  
WO/2008/138797A2
A method for pressure dynamics reduction within a gas turbine engine with a number of combustion chambers (1), where a pilot fuel spilt is defined for each combustion chamber, is provided, comprising the steps of measuring the pressure v...  
WO/2008/134853A1
A method of operating a gas turbine engine (10) having a rotatable turbine shaft (14) with an electric machine (24) mounted to the shaft (14). The method includes providing supplemental acceleration and/or deceleration of the turbine sha...  
WO/2008/134856A1
A method of starting a turbine engine (10) at a first engine speed value (S1) which is lower than a second engine speed value (S2) designed for a normal engine starting operation, comprises varying a fuel flow (FF1) into a combustor (28)...  
WO/2008/134097A2
A system and method implements machine performance, most preferably for gas ' turbine engines. The system and method implement a control law (118) that ' receives sensed operational parameter feedback signals (124). For each sensed engin...  
WO/2008/128326A1
A method for detecting a surge condition during operation of a gas turbine engine includes detecting a change of pressure differential between fuel flows in a fuel system (28) of the engine during engine operation.  
WO/2008/128325A1
A method and apparatus for measuring a start fuel flow to a pilot nozzle (34) of a fuel system (28) of a gas turbine engine using pressure differential between fuel passages leading to fuel nozzles (34, 37).  
WO/2008/126399A1
A plant controller of a combined cycle power plant type power-station having a plurality of power generation shafts for coupling a turbine and a generator and outputting electric power generated from the generator by the turbine output a...  
WO/2008/057685A3
A combustor nozzle (72) is provided. The combustor nozzle includes a first fuel system (74) configured to introduce a syngas fuel into a combustion chamber to enable lean premixed combustion within the combustion chamber and a second fue...  
WO/2008/108058A1
A gas turbine power generation system, which can suppress an increase in the number of revolutions of a gas turbine easily upon occurrence of a sudden drop in gas turbine load, comprises a gas turbine (2), a generator (7) connected, in o...  
WO/2008/105907A2
A control system 10 and method of controlling a propeller aircraft engine 20 during takeoff limits the amount of engine power developed at the very beginning of the takeoff in order to maximize thrust and minimize rollout distances. The ...  
WO/2008/098891A1
The invention relates to a power plant system (10), comprising a turbine branch (11) made of a gas turbine (12) and a generator (18), which is directly driven by the gas turbine (12) and generates an alternating current have an operating...  
WO/2008/098894A1
The invention relates to a power plant (40) comprising a turbine train composed of a gas turbine (12) and a generator (28), directly driven by the gas turbine (12) and generating alternating current of a first operating frequency, the ou...  
WO/2008/098911A1
The invention relates to a method for operating a power plant (10) comprising a turbine train (11) composed of a gas turbine (12) and a generator (18), directly driven by the gas turbine (12) and generating alternating current of an oper...  
WO/2008/097269A2
A method includes controlling an aircraft during descent, and controlling the engine pressure ratio of a jet engine so that the engine has a substantially equal pressure at the exhaust, and at the front of the engine during the descent.  
WO/2008/092252A1
A fuel control system (22) having a combustive energy value evaluator (38) determining a combustive energy value of the fuel, and a controller (26) calculating a desired flow rate based at least on the combustive energy value and control...  
WO/2008/091503A2
A combustion turbine power generation system includes a combustion turbine assembly (10) including a main compressor (12) constructed and arranged to receive ambient inlet air, a main expansion turbine (14) operatively associated with th...  
WO/2008/091415A2
An indirect-fired biomass-fueled gas turbine system with a combustor for combustion of biomass particles to produce a combustion gas, a heat exchanger providing a heat exchange relationship between combustion gas from the combustor and c...  
WO/2008/087126A1
Method of Controlling a Fuel Split Method of controlling a fuel split of a pilot fuel flow and a main fuel flow in a gas turbine combustor in case of load reductions characterised in that the rate of change of fuel demand is monitored (1...  
WO/2008/083771A1
The invention relates to a regulating method for a turbocharger (1) with a turbine (4) which has a variable turbine geometry (VTG) provided with adjustable guide blades (5), having the following method steps: a) closing the guide blades ...  
WO/2008/063732A3
A method of increasing the production rate and operational flexibility of an LNG facility by overfiring one or more modular gas turbines employed to drive one or more refrigerant compressors in the LNG facility.  
WO/2008/081488A1
Described herein is a method for controlling the supply of fuel gas (SG, NG) to a burner (3) of a gas turbine; according to said method, a fuel (SM) comprising a gas with low calorific value (SG) is sent to the burner (3) with a flowrate...  
WO/2008/080639A1
The invention relates to a pressure measurement device (20) for pressure measurement in a combustion medium inside a gas turbine, which gas turbine contains a burner (10) for supplying the combustion medium in an uncombusted state to a c...  
WO/2008/081483A1
A control device (8) for a gas-turbine plant (1), having a compressor (12), a combustion chamber (14) and a gas turbine (15), is provided with a regulator (18), for regulating quantities regarding the plant (1) in a first operating condi...  
WO/2008/068330A1
For monitoring (unmeasured) process states of a rotating machine having a combustion chamber (2c), e.g. a gas turbine (2), compositions of educts entering the combustion chamber (2c) are measured. Based on the compositions of the educts,...  
WO/2008/061336A1
The arrangement comprises a fan by-pass duct (32) located within the nacelle (34) and having an inlet (32a) and an outlet (32b). The outlet (32b) is generally oriented substantially radially and at an intermediary location along the nace...  
WO/2008/056790A1
To detect a variation in calorie using available measurements without using a measuring instrument such as a calorimeter. An allowable variation range of gas turbine power generation output with respect to a charged fuel amount or an all...  
WO/2008/057685A2
A combustor nozzle (72) is provided. The combustor nozzle includes a first fuel system (74) configured to introduce a syngas fuel into a combustion chamber to enable lean premixed combustion within the combustion chamber and a second fue...  
WO/2008/056781A1
Provided are a coal gasification composite power generating system which is enabled to stabilize the output of a gas turbine early at a load fluctuating time by adjusting the balance of the pressure/temperature of a plant entirety; and a...  

Matches 851 - 900 out of 8,882