Entries |
Document | Title | Date |
20080264067 | Controlling operation of a compressor to avoid surge - A compressor or fan is controlled to avoid stall, surge or flutter. The control system includes a look-up table from which is retrieved a margin-adjusted limiting value of a control parameter of the compressor, using inputs representing inlet guide vane angle (IGV), non-dimensional speed of the compressor (N/R√T), vehicle Mach number (Mn) and inlet geometry (IG). A variable stall, surge or flutter safety margin about a nominal limiting value of a control parameter is pre-established to reflect threats to the working, stall, flutter and surge lines, for example as a result of measurement inaccuracies, and from this the margin-adjusted limiting value is derived. An actual value of the control parameter is determined in real time, and the actual value is compared with the margin-adjusted limiting value. An output signal indicating stall, surge or flutter risk is generated if the actual value falls within the stall, surge or flutter safety margin. | 10-30-2008 |
20080289342 | Method and Apparatus for Spectroscopic Measurements in the Combustion Zone of a Gas Turbine Engine - A method for measuring combustion parameters within a combustion zone of a gas turbine engine, the combustion zone being defined between an inner and outer casing. The method comprises transmitting a beam from a transmit optic optically coupled to a bore in the outer casing off a portion of the inner casing and receiving a portion of the beam reflected off the inner casing with a receiving optic optically coupled to a bore in the outer casing. An apparatus for practicing the method comprises a laser generating a beam and a transmitting/receiving optics pair, the transmitting/receiving optics pair being configured for operative association with a port in an outer casing of a gas turbine engine, whereby the transmitting/receiving optics are in optical communication by reflecting the beam off a portion of an inner casing. | 11-27-2008 |
20100031670 | POWER STATION AND METHOD FOR ITS OPERATION - A power station ( | 02-11-2010 |
20100242492 | DISTRIBUTED ENGINE CONTROL SYSTEMS AND GAS TURBINE ENGINES - Distributed engine control systems and gas turbine engines are provided. In an embodiment, a distributed engine control system includes a central controller, a plurality of nodes in operable communication with the central controller, each node including an electronic circuit and a heat transfer element adapted to absorb heat from the electronic circuit, each node in communication with the central controller, and a coolant distribution system including a plurality of coolant interfaces, a coolant line, and a coolant source, each coolant interface of the plurality of coolant interfaces adapted to contain a coolant that is adapted to absorb heat from the heat transfer element of a node of the plurality of nodes, and the coolant line adapted to provide fluid communication between the nodes of the plurality of nodes and the coolant source | 09-30-2010 |
20110048028 | SYSTEM FOR CONTROLLING A PLURALITY OF FUNCTIONS OF A TURBOJET ENGINE - A control system for controlling a plurality of distinct functions of a turbojet engine, each function being associated with a respective actuation device. The system includes: an electric motor adapted to supply mechanical energy to each of the actuation devices; an electronic control unit for the electric motor; and at least one switching device interposed between the motor and the actuation devices, the switching device(s) serving to distribute the mechanical energy supplied by the electric motor selectively to one of the actuation devices. | 03-03-2011 |
20110113788 | FAULT TOLERANT ANALOG OUTPUTS FOR TURBO COMPRESSORS - A control system for operating a device in a turbo machine system. The system includes a first programmable logic control device producing an analog output signal and a relay circuit electrically connected to the first programmable logic control device to receive the analog output signal. A field device is electrically connected to the relay circuit to receive the analog output signal to operate based on the analog output signal to provide a load. In addition, the relay circuit is electrically connected to a second programmable logic control device to communicate the analog output signal to the second programmable logic control device to monitor the analog output signal. | 05-19-2011 |
20120159965 | MULTI SPOOL GAS TURBINE SYSTEM - A gas turbine engine is provided, including an air inlet in fluid communication with a compressor, a combustor, a compressor turbine, and a power turbine. The compressor and compressor turbine may be mounted on a first drive shaft, and the power turbine may be mounted on a second shaft. The engine further includes an engagement mechanism adapted to selectively engage the first drive shaft to the second drive shaft, wherein the first drive shaft and second drive shaft rotate at substantially the same speed when the engagement mechanism is engaged. The disclosed multi-spool gas turbine engine provides improved part power fuel consumption at reduced output shaft speeds. The proposed invention can relate to turbines with two or more gas generator spools. | 06-28-2012 |
20120247122 | Powerplant and related control system and method - A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust. | 10-04-2012 |
20120291449 | Turbine Section of High Bypass Turbofan - A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170. | 11-22-2012 |
20140144156 | GAS TURBINE TEMPERATURE MEASUREMENT - The disclosure relates to a method for determining a temperature in a pressurized flow path of a gas turbine comprising the steps of sending an acoustic signal from an acoustic signal emitting transducer across a section of the pressurized flow path, detecting the acoustic signal with a receiving transducer, measuring the time needed by the acoustic signal to travel from the acoustic signal emitting transducer to the receiving transducer, calculating the speed of sound, and calculating the temperature as a function of the speed of sound, the heat capacity ratio (□) and a specific gas constant (R | 05-29-2014 |
20140202167 | POWER GENERATION SYSTEM - The power generation system includes a fuel cell that generates electric power using a fuel gas, a gas turbine including an air compressor, a combustor, and a turbine, an exhaust fuel line that introduces an exhaust fuel gas discharged from the fuel cell into the combustor, a branch exhaust fuel line branching off midway from the exhaust fuel line, a switching unit that sends the exhaust fuel gas to one of the branch exhaust fuel line and the combustor, and a heating portion that heats the exhaust fuel line at a downstream side of the switching unit. | 07-24-2014 |
20140283527 | MULTI-ENGINE PERFORMANCE MARGIN SYNCHRONIZATION ADAPTIVE CONTROL SYSTEM AND METHOD - A system and method of adaptively synchronizing the performance margin of a multi-engine system includes continuously, and in real-time, determining the performance margin of a first engine and the performance margin of the second engine. A difference between the performance margins of the first and second engines is calculated, and the first and second engines are controlled to attain a predetermined difference between the performance margins of the first and second engines. | 09-25-2014 |
20140305133 | DUAL CHANNEL ACCELEROMETER AND METHOD OF MANUFACTURING THE SAME - A dual output accelerometer having first and second output channels, comprises a supporting base, a first transducer comprising a plurality of inter-connected first piezoelectric elements, a second transducer comprising a plurality of inter-connected second piezoelectric elements and a seismic mass. | 10-16-2014 |
20140311158 | HEAT AND POWER PLANT WITH A WASTE GASIFICATION SYSTEM - Heat and power plant with a waste gasification system comprising a gas engine ( | 10-23-2014 |
20140311159 | VARIABLE NOZZLE MECHANISM - A variable nozzle mechanism applied to a turbocharger includes a pair of annular plates located between a scroll passage and a turbine chamber such that the plates are apart from each other in a direction along an axis; a coupling portion which couples the plates; a plurality of variable nozzles which are provided between the plates so as to open and close, and which change a flow speed of exhaust gas blown onto a turbine wheel when an opening degree of the variable nozzles is changed; and an urging portion which urges the plates in the direction along the axis to press one of the plates against a contacted object. The one of the plates includes a contact face which is in contact with the contacted object, and the contact face is located on an action line along which an urging force of the urging portion acts. | 10-23-2014 |