Class / Patent application number | Description | Number of patent applications / Date published |
060730000 | With liquid heat exchanger | 14 |
20090133400 | Turbine engine having fuel-cooled air intercooling - A turbine engine is disclosed. The turbine engine may have a first compressor configured to pressurize inlet air, and a second compressor configured to further pressurize the inlet air. The turbine engine may also have a cooling circuit fluidly located to cool the inlet air after the inlet air is pressurized by the first compressor and before the inlet air is further pressurized by the second compressor. The cooling circuit may have a first heat exchanger configured to transfer heat from the inlet air to a fuel of the engine, and a second heat exchanger configured to transfer heat from exhaust of the engine to the fuel of the engine. | 05-28-2009 |
20090320479 | NESTED CHANNEL DUCTS FOR NOZZLE CONSTRUCTION AND THE LIKE - A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel, adapted for conveying fuel flow, is formed in a surface of a gas turbine engine component. The channel includes at least a first discrete conduit and a second discrete conduit. The first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets. | 12-31-2009 |
20100000217 | TURBINE ENGINE WITH INTERSTAGE HEAT - Efficiency and/or power are increased in a turbine engine by using a self-contained, passive heat transfer device, such as a heat pipe, to transfer heat from working fluid in one section of the engine to working fluid in another section of the engine. | 01-07-2010 |
20100071372 | INTAKE AIR HEATING CONTROL DEVICE FOR GAS TURBINE - Extremely cold (e.g., −20° C.) air A is heated by a heat exchanger | 03-25-2010 |
20100083662 | METHOD AND APPARATUS FOR THE UTILIZATION OF WASTE HEAT FROM GASEOUS HEAT SOURCES CARRYING SUBSTANTIAL QUANTITIES OF DUST - An apparatus, system and method for transferring heat from a hot flue gas stream from a cement plant including large particles and dust to a working fluid of a power plant via a high temperature heat transfer fluid without exposing all or most of the equipment to the erosive force of the particles and dust is disclosed where the apparatus includes a cement plant, a particle separation and heat transfer system and a power plant | 04-08-2010 |
20100146978 | Gas Turbine Base Load Control by Chilling Modulation - A control system for a base load output of a gas turbine engine. The control system may include an inlet chilling coil system for providing air to the gas turbine engine at a desired temperature, a temperature control valve in communication with the inlet chilling coil system, a temperature sensor positioned about the gas turbine engine, and a temperature controller in communication with the temperature control valve and the temperature sensor. The temperature controller modulates the temperature control valve until the air provided to the gas turbine engine by the inlet chilling coil system reaches the desired temperature as sensed by the temperature sensor. | 06-17-2010 |
20100307157 | METHODS RELATING TO TURBINE ENGINE CONTROL AND OPERATION - A method of controlling a combustion turbine engine, wherein the engine includes: a fuel line including a heat exchange portion; a heating value meter; a cold leg bypass comprising an alternate fuel line that bypasses the heat exchange portion, the cold leg bypass being connected to the fuel line at an upstream fork and at a fuel mixing junction, the fuel mixing junction being positioned such that a length of fuel line between it and the inlet to the combustor is short; and valves for controlling the amount of fuel being directed through the heat exchange portion; the method comprising: measuring the heating value of the fuel; determining a target fuel temperature range based on the heating value and a target Modified Wobbe Index range; and controlling the fuel that bypasses the heat exchange portion such that the temperature of the fuel is within the target temperature range. | 12-09-2010 |
20110016866 | APPARATUS FOR FUEL INJECTION IN A TURBINE ENGINE - In one embodiment, a system includes a fuel injector including a liquid fuel passage extending to a first port in a tip portion. The fuel injector also includes a selectable flow passage extending to a second port in the tip portion. The selectable flow passage surrounds the liquid fuel passage to the tip portion, the selectable flow passage is configured to selectively receive a gas fuel flow and an air flow, and the selectable flow passage has a flow temperature configured to cool a liquid fuel flowing through the liquid fuel passage to reduce coking. | 01-27-2011 |
20130086909 | OIL COOLING SYSTEM - A system for cooling one or more circulating flows of oil, the system including: one or more fuel-oil heat exchangers, the fuel-oil heat exchangers using fuel for an engine to cool at least one of one or more circulating flows of oil; and a fuel return line in flow communication with a point downstream of the fuel-oil heat exchangers and a point upstream of the fuel-oil heat exchangers, wherein the fuel return line is arranged so that at least a portion of the fuel exiting the fuel-oil heat exchangers may be diverted to the point upstream of the fuel-oil heat exchangers. Furthermore, a system for cooling a circulating flow of oil may include one or more fuel-oil heat exchangers and one or more air-fuel heat exchangers, the fuel-oil heat exchangers using fuel to cool the circulating flow of oil and the air-fuel heat exchangers using air to cool the fuel. | 04-11-2013 |
20140020391 | AXIAL TURBINE AND POWER PLANT - An axial-flow turbine has turbine nozzles, a heat shield plate, a first communication hole formed in the turbine rotor and connected to the space, to flow a cooling medium, a first opening formed in at least any one of the two adjacent rotor disks, to be connected to the space, a second communication hole connected to the space through the first opening, to communicate with an implant unit of the turbine rotor blade in the rotor disk, a third communication hole connected to the second communication hole, to communicate along an effective length of the turbine rotor blade, a second opening formed in a side face of the turbine rotor blade, to be connected to the third communication hole, and a third opening formed in an outer circumferential end face of the turbine rotor blade, to be connected to the third communication hole. | 01-23-2014 |
20140165570 | OSCILLATING HEAT PIPE FOR THERMAL MANAGEMENT OF GAS TURBINE ENGINES - An oscillating heat pipe of a gas turbine engine includes a plurality of channels that define a continuous loop through which a fluid flows, and an evaporator of a gas turbine engine. The fluid flows through the evaporator to accept heat from a first fluid. The first fluid is located near or in an engine core. The oscillating heat pipe also includes condenser of the gas turbine engine. The fluid flows through the condenser to reject heat to a second fluid, and the second fluid is located outwardly of the engine core. | 06-19-2014 |
20140230441 | HEAT SHIELD MANIFOLD SYSTEM FOR A MIDFRAME CASE OF A GAS TURBINE ENGINE - A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required. In addition, the heat shield manifold system may be configured such that compressor bleed air is passed from the compressor into the heat shield manifold system without passing through a conventional flange to flange joint that is susceptible to leakage. | 08-21-2014 |
20140331673 | COMBUSTION BURNER - A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream so as to swirl air flowing in the air passage from the upstream to the downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane surface of each of the swirler vanes, and a cooling unit that cools a part of the vane surface on which the liquid fuel hits. The cooling unit includes a water cooling circuit formed inside the swirler vane. | 11-13-2014 |
20150107254 | Method and System for Improving the Efficiency of a Simple Cycle Gas Turbine System With a Closed Circuit Fuel Heating System - A closed circuit fuel heating system is provided for heating at least two types of fuel. The heating system includes a heat transfer subsystem disposed in a gas turbine system exhaust. A first heat exchange subsystem is coupled to a first fuel source and the heat transfer subsystem. The first heat exchange subsystem is provided with a control component for controlling a flow of a working fluid through the first heat exchange subsystem. A second heat exchange subsystem may be coupled to a second fuel source and the heat transfer subsystem. The second heat exchange subsystem is provided with a control component for controlling a flow of the working fluid through the second exchange subsystem. A subsystem for controlling the temperature of the working fluid is also provided. | 04-23-2015 |