Abstract: An inlet cooling system unit that is fluidly coupled to a gas turbine can include a filter module configured to filter inlet air, a chiller module configured to cool inlet air, and a framework. The framework is sized and shaped to define a filer module receiving region which supportably receives the filter module, and a chiller module receiving region which supportably receives the chiller module, the chiller module receiving region located below the filter module receiving region such that the chiller module is received below the filter module. Related gas turbine inlet cooling systems are also provided.

Abstract: A gas accumulation detection and ventilation system for a gas turbine enclosure includes a pipe array positioned adjacent a floor of the gas turbine enclosure and a ventilation assembly including a fan, an air flow inlet and an air flow outlet. The pipe array includes at least one pipe having at least one opening therein. The fan of the ventilation assembly directs an air flow sweep through the air flow inlet along the floor of the gas turbine enclosure. A hazardous gas sensor panel in communication with the pipe array and the ventilation assembly detects an accumulation level of turbine fuel gas in the gas turbine enclosure based on input from the pipe array and activates the ventilation assembly according to the detected accumulation level.

Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

Abstract: Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode, the model generates current state derivatives and synthesized parameters as a function of the dynamic states and the model input, wherein a constraint on the current state derivatives is based a series of modules, each member of the series of modules arranged in at least a primary stream group and a secondary stream group corresponding to a component of the system. The model processor may further include an estimate state module for determining an estimated state of the model.

Abstract: An apparatus for manufacturing an article from powder material including a first table, a second table rotatably mounted on the first table about a first axis and a third table rotatably mounted on the second table about a second axis. A hollow canister is supported by the third table. A vibrator is arranged to vibrate the canister. A first device is arranged to rotate the second table about the first axis and a second device is arranged to rotate the third table about the second axis. A hopper is arranged to supply powder material into the canister and a valve controls the flow of powder material from the hopper into the canister. A processor is arranged to control the valve, the vibrator, the first device and the second device to control the filling and packing density of the canister.

Abstract: A system and method for increasing the responsiveness of a duct fired, combined cycle power generation plant (12) via operating one or more gas turbine engines (14) at a part load condition less than 100 percent load, one or more steam turbine engines (16), and one or more supplemental burners (18) providing additional heat to a heat recovery steam generator (20) upstream from the steam turbine engine (16) is disclosed. The combination of the steam turbine engines (16) and supplemental burners (18) operating together with gas turbine engines (14) at a part load condition enables the system to quickly change output to accommodate changes in output demand of the duct fired, combined cycle power generation plant (12). By operating the one or more gas turbine engines (14) at a part load condition, the gas turbine engines (14) are able to be used to increase net output of the combined cycle power generation plant (12) faster than relying on increasing output via duct firing.

Abstract: A heater assembly for use in a hydrogen generator can be retracted to facilitate insertion and removal of a replaceable fuel unit without damaging the heater assembly or the fuel unit and extended to provide good thermal contact with the fuel unit during use of the hydrogen generator. The heater assembly includes a support member, a heater, and an actuator for extending and retracting the heater assembly. When the heater is energized it heats the actuator, thereby extending the heater assembly to contact the adjacent fuel unit, and when the heater is deenergized the actuator cools to retract the heater assembly and provide a gap between the heater assembly and the adjacent fuel unit. The actuator is movably secured to the heater or the support member by a retainer such that an end of the actuator is movable within the retainer as the actuator changes shape during heating and cooling.

Abstract: The present disclosure is directed to a retention assembly for a stationary gas turbine component. The retention assembly includes a first stationary gas turbine wall having a first surface. A retention boss extends outwardly from the first surface. The retention assembly includes a second stationary gas turbine wall having a second surface. A retainer is positioned between the first and the second surfaces. The retainer includes a base wall positioned adjacent to the retention boss. A first sidewall extends outwardly from the base wall, and a second sidewall extends outwardly from the base wall. A first arm extends outwardly from the first sidewall, and a second arm extends outwardly from the second sidewall. Each of the first arm and the second arm includes a plurality of convolutions. At least one of the plurality of convolutions is in contact with the second surface.

Abstract: A manifold pressure damping assembly that includes one or more closed volumes coupled in flow communication with a manifold through one or more flow restrictors is provided.

Abstract: A combustor includes a shell that bounds at least a portion of a combustion chamber. The shell includes a wall that has an orifice that opens to the combustion chamber. A grommet includes a body portion and a lip that projects from the body portion. The body portion and the lip carry a surface that extends around a passage through the grommet. At least a portion of the lip extends within the orifice of the wall of the shell.

Abstract: A system includes a controller of a power generation system including a memory storing instructions and a processor that executes the instructions. The instructions cause the controller to control the power generation system to provide inlet bleed heat flow to a gas turbine during deceleration of the gas turbine. The instructions also cause the controller to receive a first temperature, a rotational speed of the gas turbine, and an inlet bleed heat flow rate. Additionally, the instructions cause the controller to calculate an exhaust flow rate based on at least the first temperature, the rotational speed, and the inlet bleed heat flow rate. Further, the instructions cause the controller to control the power generation system to isolate a fuel source from the gas turbine at a portion of normal operating speed of the gas turbine sufficient to achieve a purging volume during coast down of the gas turbine.

Abstract: A system includes a controller including a memory storing instructions and a processor that executes the instructions. The instructions cause the controller to control a steam turbine system coupled to a power generation system to release steam during deceleration of a gas turbine. The instructions cause the controller to receive a first temperature of the gas turbine and a rotational speed of the gas turbine. The instructions cause the controller to calculate an exhaust flow rate of the power generation system based on at least the first input signal and the second input signal. The instructions cause the controller to control the power generation system to isolate a fuel source from the gas turbine at a portion of normal operating speed of the gas turbine sufficient to achieve a predetermined purging volume during coast down of air flow through the power generation system based on the exhaust flow rate.

Abstract: A non-transitory, computer readable medium stores instructions executable by a processor of an electronic device. The instructions include instructions to determine that a transient event is occurring in an electrical grid coupled to an EGR gas turbine system, wherein the transient event is an under-frequency or an under-voltage event. The instructions also include instructions to increase a flow rate of fuel to a combustor of the EGR gas turbine system in response to the transient event when the EGR gas turbine system is operating in a non-stoichiometric combustion mode. The instructions further include instructions to increase a flow rate of oxidant to the combustor before increasing the flow rate of fuel to the combustor, or to decrease a local consumption of the electrical power to increase a portion of the electrical power that is exported to the attached electrical grid, or both, in response to the transient event when the EGR gas turbine system is operating in a stoichiometric combustion mode.

Abstract: In one embodiment, a system includes at least one sensor configured to communicate a signal representative of blower vane position, wherein the blower vane is disposed in a blower of an exhaust gas recirculation system receiving exhaust from a gas turbine system and recycling the exhaust gas back to the gas turbine system. The system further includes a controller communicatively coupled to the at least one sensor, wherein the controller is configured to execute a control logic to derive a reference value for the blower vane position, and wherein the controller is configured to apply a direct limit, an model-based limit, or a combination thereof, to the reference value to derive a limit-based value, and wherein the controller is configured to position the blower vane based on the limit-based value.

Abstract: A method for adjusting startup floor pressure levels of HRSG steam circuits is implemented by a pressure controlling computing device including a processor and a memory. The method includes receiving a plurality of measured plant operating values associated with a HRSG steam circuit, identifying a plurality of candidate pressure levels for use in pressurizing the HRSG steam circuit, determining a calculated steam velocity level for each of the plurality of candidate pressure levels, identifying a steam velocity limit for a steam piping section of the HRSG steam circuit, selecting a lowest pressure level of the plurality of candidate pressure levels, wherein the lowest pressure level is associated with a determined calculated steam velocity level that does not exceed the identified velocity limit, and pressurizing the HRSG steam circuit to the selected lowest pressure level.

Abstract: A transfer coupling has a static component and a rotatable component arranged in axial alignment. The static component includes a first number (n?1) of radially extending ports and the rotatable component has a second number (n) of radially extending ports, the radially extending ports arranged in a common circumferential plane, wherein the ports on each component are equally spaced around the component and the number of ports on a first of the components is one less than on the second of the components.

Abstract: In an embodiment, a method includes performing a turbine combustor diagnostic routine including operating a first turbine combustor of a plurality of turbine combustors at a substantially steady state of combustion; adjusting an operational parameter of the first turbine combustor to cause a change in combustion products produced by the first turbine combustor; identifying a first sensor response of a first subset of a plurality of sensors disposed within or downstream from a turbine fluidly coupled to the turbine combustor, the first sensor response being indicative of the change in the combustion products, and wherein the first subset comprises one or more first sensors; correlating the first subset of sensors with the first turbine combustor; and diagnosing a condition of the first subset of the plurality of sensors, the first turbine combustor, or a combination thereof, based on the first sensor response.

Abstract: A method of starting a turbomachine, performed by an electronic unit, the turbomachine including a gas turbine engine including at least one rotor and a starter to drive the rotor in rotation, the method including: receiving an order to start the turbomachine, and executing in response to receiving the order to start: a primary acceleration during which the starter is operated to increase speed of rotation of the rotor; a thermal homogenization during which the starter is operated to keep the speed of rotation of the rotor constant or to decrease it until a predetermined condition is satisfied; after the predetermined condition is true, a secondary acceleration in which the starter is operated to increase the speed of rotation of the rotor; and an ignition in which ignition of the engine is ordered.

Abstract: A gas turbine that includes a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section that corresponds to the aftward annulus section and a forward intake section that corresponds to the forward annulus section. The air directing structure may be configured to: direct air entering through the aftward intake section through the aftward annulus section in a forward direction to the staged injector; and direct air entering through the forward intake section through the forward annulus section in an aftward direction to the staged injector.

Abstract: In an exhaust heat recovery device provided with a Rankine cycle device, a clutch for transmitting and interrupting power between an engine and the Rankine cycle device is released appropriately to prevent the Rankine cycle from becoming a load on the engine. An exhaust heat recovery device 1A includes a Rankine cycle device 2A, a power transmission mechanism 3A, and a control unit 4. The power transmission mechanism 3A has a clutch 31 and is capable of transmitting power between an engine 10 and the Rankine cycle device 2A when the clutch 31 is engaged. The control unit 4A controls the engagement and disengagement of the clutch 31 based on a first correlation value correlated with consumed power when the Rankine cycle device 2A is started, and a second correlation value correlated with consumed power of the Rankine cycle device 2A when the output of the Rankine cycle device 2A is negative during the operation of the Rankine cycle device 2A after the start-up.

Abstract: An environmental control system includes a low pressure tap at a location on a first compressor section of a main compressor section. The low pressure tap communicates airflow to a first passage leading to a downstream outlet. A compressor is driven by an electric motor. A combined outlet intermixes airflow from the first passage and from the compressor driven by the electric motor and passes the airflow downstream to be delivered to an aircraft use.

Abstract: Methods and systems for in situ cleaning of internal cooling circuits of a turbine engine with detergent that provide cleaning a turbine engine that includes circumferentially arranged internal impingement cooling circuits that each include a baffle plate configured to air cool a respective surface or component of the turbine engine. Detergent is introduced through the outer wall and proximate to a back side of a baffle plate such that the detergent passes through at least one aperture in the baffle plate and acts at least upon the surface or component that the baffle plate is configured to cool. The detergent may also act on the front side of the baffle plate that is proximate to the surface or component.

Abstract: A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition.

Abstract: A starter air valve comprising: a housing comprising an inlet at a first end, an outlet at a second end opposite the first end, and a center portion between first and second end, the outlet being fluidly connected to the inlet through a fluid passage; a first piston located within the housing between the first end and center portion, the first piston comprising: a first cupped portion configured to form a first chamber with the housing proximate the first end; and a second piston located within the housing between the second end and center portion, the second piston comprises: a third cupped portion configured to form a third chamber with the housing proximate the second end; wherein the first piston is configured to regulate airflow through the fluid passage by adjusting at least one of a first pressure within the first chamber and a third pressure within the third chamber.

Abstract: A gas turbine that includes a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section that corresponds to the aftward annulus section and a forward intake section that corresponds to the forward annulus section. The air directing structure may be configured to: direct air entering through the aftward intake section through the aftward annulus section in a forward direction to the staged injector; and direct air entering through the forward intake section through the forward annulus section in a forward direction to the forward injector.

Abstract: A gas turbine engine comprises a main fan that delivers air into a bypass duct and into a core engine. A heat exchanger is positioned within the bypass duct and receives a fluid to be cooled from a component associated with the gas turbine engine. A heat exchanger fan is positioned to draw air across the heat exchanger and a control for the heat exchanger fan. The control is programmed to stop operation of the fan during certain conditions, and to drive the heat exchanger fan under other conditions. A method of forming a heat exchanger is also disclosed.

Abstract: A gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted. The gas turbine has an icing sensor unit having at least one sensor arranged between a first compressor blade row and a first compressor guide vane row. The first compressor blade row is thereby arranged in the compressor flow channel directly downstream of the inlet guide vane row, and the first compressor guide vane row is arranged directly downstream of the first compressor blade row. A method detects an imminent icing of the compressor, and the compressor is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row are adjusted such that the acceleration of an intake air mass flow is reduced.

Abstract: A method to condense and recover CO2 from CO2 containing streams. A first step involve providing at more than one heat exchanger, with each heat exchanger having a first flow path for passage of a first fluid and a second flow path for passage of a second fluid. A second step involves passing a stream of very cold natural gas sequentially along the second flow path of each heat exchanger until it is heated for distribution and concurrently passing a CO2 containing stream sequentially along the first flow path of each heat exchanger, allowing the water vapor portion of the CO2 containing stream to condense and precipitate on the condensing heat exchangers. A third step involves passing a water vapor free CO2 containing stream to a cryogenic heat exchanger to condense, precipitate and recover CO2.

Abstract: A turbine engine assembly includes a turbine engine case, a gearbox and a plurality of mounts connecting the gearbox to the case. Each of the mounts includes a linkage and a fuse joint. The linkage extends towards the case substantially in a first direction. The fuse joint is configured to substantially prevent movement between the gearbox and the case when the fuse joint is subject to loading less than a threshold, and to permit a constrained movement between the gearbox and the case when the loading is greater than the threshold. The fuse joint of a first of the mounts has a different configuration than the fuse joint of a second of the mounts.

Abstract: A transition duct system (100) for routing a gas flow from a combustor (102) to the first stage (104) of a turbine section (106) in a combustion turbine engine (108), wherein the transition duct system (100) includes one or more converging flow joint inserts (120) forming a trailing edge (122) at an intersection (124) between adjacent transition ducts (126, 128) is disclosed. The transition duct system (100) may include a transition duct (126, 128) having an internal passage (130) extending between an inlet (132, 184) to an outlet (134, 186) and may expel gases into the first stage turbine (104) with a tangential component. The converging flow joint insert (120) may be contained within a converging flow joint insert receiver (136) and disconnected from the transition duct bodies (126, 128) by which the converging flow joint insert (120) is positioned. Being disconnected eliminates stress formation within the converging flow joint insert (120), thereby enhancing the life of the insert.

Abstract: A cable assembly for a flame sensor apparatus includes an inner conductor electrically connected to a photodiode that generates a current. The inner conductor transmits the current from the photodiode. A first insulating layer circumferentially surrounds the inner conductor. The first insulating layer includes a mineral insulation material. An inner sheath circumferentially surrounds the first insulating layer. The inner sheath includes an electrically conductive material. A second insulating layer circumferentially surrounds the inner sheath. The second insulating layer includes a mineral insulation material. An outer sheath circumferentially surrounds the second insulating layer. The outer sheath includes an electrically conductive material. The cable assembly is for use in temperatures up to about 300 degrees Celsius or greater. A method of attaching a cable assembly for a flame sensor apparatus.

Abstract: An automated industrial system is provided that includes a sensor system configured to monitor multiple parameters. The automated industrial system also includes a controller. The controller is configured to determine if any of the multiple parameters has surpassed a respective constraint threshold of multiple constraint thresholds. If any of the parameters has surpassed a respective constraint threshold, the controller is configured to classify a parameter of the multiple parameters which has surpassed the respective constraint threshold by the highest degree as the most constrained parameter. The controller is also configured to calculate a minimum temperature load path based on the most constrained parameter, with the minimum temperature load path configured to transition the automated industrial system from a base load to a part load via a minimum temperature load path.

Abstract: An airflow control system for a gas turbine according to an embodiment includes: an airflow generation system for attachment to a rotatable shaft of a gas turbine system, the airflow generation system drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream of the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the airflow generation system to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

Abstract: An engine cooling system, capable of reducing vehicle weight caused by employing a Rankine cycle and capable of improving Rankine cycle performance, including some inlet-side cooling water of a radiator is used as a heating source for a first evaporator and some outlet-side cooling water of a sub-radiator is used as a cooling source for a condenser, a coolant that has passed through an expander, a second evaporator, and a compressor in a cooling cycle for an air conditioner, vaporized, cooled and liquefied by passing through a side to be cooled of the condenser in the Rankine cycle.

Abstract: Disclosed are a hydrogen generator and a method of producing hydrogen gas therefrom. A fuel unit containing a fuel that releases hydrogen gas when heated is removably disposed in a cavity within a housing having a door. A heater assembly for heating the fuel unit is disposed in the hydrogen generator. A mechanism retracts the heater assembly from the fuel unit when the door is opened and extends the heater assembly to contact the fuel unit when the door is closed. When the heater assembly is retracted, more space is available into which the fuel unit can be inserted to prevent damage to the heater assembly and the fuel unit, and when the heater assembly is extended, good contact is provided between the heater assembly and the fuel unit for efficient heating. A cam bar can move the heater assembly normal to the lateral motion of the cam bar.

Abstract: The specification is related to a motor controller, a vehicle including the motor controller and a heat stress estimating method for a switching element. The motor controller includes a switching element, a temperature sensor, and a computer. The switching element is configured to convert output electric power of an electric power supply into motor-driving electric power. The temperature sensor is configured to measure a temperature of the switching element. The computer is configured to extract a maximum point and a minimum point in a time-dependent change in the temperature of the switching element, the computer is configured to calculate a temperature difference between the maximum point and the minimum point adjacent to each other and configured to calculate an estimated value of a heat stress to which the switching element is subjected based on each calculated temperature difference.

Abstract: A system and method for reducing modal coupling of combustion dynamics among multiple combustors are provided. Each combustor may include one or more fuel nozzles axially aligned with a combustion chamber; one or more fuel injectors downstream from the fuel nozzles; and a set of flow openings integrated with the combustor. The fuel injectors provide fluid communication through a liner that circumferentially surrounds each combustion chamber. The flow rate of compressed working fluid diverted through the fuel injectors may be different and/or variable between the combustors to produce different combustion instability frequencies.

Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the opening of the row of variable compressor inlet guide vanes is controlled depending on the temperatures of the operative burners of the second combustor and simultaneously the number of operative burners is kept at a minimum. This leads to low CO emissions at partial load of the gas turbine.

Abstract: A method for controlling an air-fuel ratio (AFR) in an engine powered by a gaseous fuel having an unknown composition may comprise receiving an assumed gas species composition for the gaseous fuel, and determining an assumed lower heating value (LHV) for the assumed gas species composition. The method may further comprise determining a perceived lower heating value (LHV) for the gaseous fuel based on a perceived gas mass flow and a gas energy flow for the gaseous fuel, and updating the assumed gas species composition until the assumed LHV and the perceived LHV are aligned. The method may further comprise determining a desired AFR and an airflow necessary to provide the desired AFR using the aligned gas species composition and a desired lambda (?), and adjusting an air system controller of the engine to provide the airflow.

Abstract: A system for managing thermal transfer in an aircraft includes a fuel stabilization unit, a fuel-air heat exchanger, and a turbine. The fuel-air heat exchanger is located downstream from the fuel stabilization unit. The fuel-air heat exchanger places deoxygenized fuel in a heat exchange relationship with compressor bleed air to produce heated deoxygenized fuel and cooled bleed air. The turbine is operationally connected to the engine compressor and receives cooled bleed air from the fuel-air heat exchanger.

Abstract: Energy-efficient gasification-based multi-generation apparatus, facilities, or systems, and methods of modifying existing gasification-based multi-generation apparatus and the various conventional thermal coupling arrangements, are provided. An exemplary gasification-based multi-generation apparatus comprises an acid gas removal system configured to remove acidic contaminants from a raw syngas feed to thereby provide a treated syngas feed and an acid gas removal plant or facility; a gasification system configured to generate the raw syngas feed from a carbon-based feedstock and comprising a gasification plant or facility; and a condensate polishing plant or facility. The acid gas removal system comprises an acid gas contaminant absorber, a solvent regenerator, a contaminant hydrolysis reactor, and an acid gas removal system energy management system.

Abstract: This invention relates to an assembly (100) for an aircraft turbofan comprising a flowpath splitter (40) downstream from which there is firstly a fan flowpath (31) inner delimitation ring (44) and secondly a compressor case (42), the assembly comprising a plurality of outlet guide vanes (34) provided with an inner platform (50) located in the downstream continuity of the delimitation ring. According to the invention, the assembly comprises at least one part (52) to support the delimitation ring (44), comprising a radially outer end (52b) fixed to a downstream part of this ring (44) and a radially inner end (52a) fixed to the compressor case (42).

Abstract: A system for detecting an at-fault combustor includes a sensor that is configured to sense combustion dynamics pressure data from the combustor and a computing device that is in electronic communication with the sensor and configured to receive the combustion dynamics pressure data from the sensor. The computing device is programmed to convert the combustion dynamics pressure data into a frequency spectrum, segment the frequency spectrum into a plurality of frequency intervals, extract a feature from the frequency spectrum, generate feature values for the feature within a corresponding frequency interval over a period of time, and to store the feature values to generate a historical database. The computing device is further programmed to execute a machine learning algorithm using the historical database of the feature values to train the computing device to recognize feature behavior that is indicative of an at-fault combustor.

Abstract: A heating and cooling system for inlet air of a turbine compressor. The heating and cooling system may include a thermal energy storage tank charging loop, a cooling loop in communication with the thermal energy storage charging loop, and a heating loop in communication with the cooling loop and the inlet air of the turbine compressor.

Abstract: A method including providing a wet algae material having been subjected to a refinement process without a water separation phase; supplying the wet algae material including a water fraction and an algae-grown biofuel to a turbine engine; and operating the turbine engine with the wet algae material where a retained portion of the water fraction is retained in the wet biofuel during a manufacturing process not including a dehydration step and includes an amount sufficient to reduce generation of a quantity of nitrogen oxides, and where the turbine engine can further include a combustor capable of combusting the wet biofuel.

Abstract: Apparatus for controlling a turbine aircraft engine may include apparatus to determine an amount of secondary power extraction from the engine, a secondary load processor configured to receive and condition secondary power extraction data. An electronic engine controller (EEC) may be configured to receive secondary load data from the secondary load processor and produce commands to open bleed-air valves of the engine, said commands being based on the secondary load data.

Abstract: An aircraft (1) having at least one rotor (2) driven by a main gearbox (3), at least one fuel-burning engine (4), an on-board electricity network (7), and at least one electrical machine (10) corresponding to the engine (4) and capable of operating both in electric motor mode and also in electricity generator mode, each electrical machine (10) being mechanically connected to said main gearbox (3) by first connection means (20) and being electrically connected to said on-board electricity network (7). Second mechanical connection means (40) connect each electrical machine (10) mechanically to a gas generator (5) of an engine.

Abstract: A gas turbine engine fuel system has an ecology valve for withdrawing residual fuel from primary and secondary fuel manifolds upon engine shut-down. The ecology valve has primary and secondary reservoirs respectively connected in fluid flow communication with the primary and secondary fuel manifolds. The valve further has a reciprocating piston movable from a retracted position when engine start-up is initiated to an extended position which the piston assumes under normal engine running conditions. The movement of the reciprocating piston between the retracted and extended positions controls the flow of fuel from and to the primary and secondary reservoirs. A cross-bleed passage is defined in the reciprocating piston. The cross-bleed passage connects the primary and secondary reservoirs in fluid flow communication only when the piston is in its extended position. In this way, the cross-bleed flow between the primary and secondary fuel manifolds may be initiated only at the end of the engine start-up phase.

Abstract: The present invention is an industrial gas turbine engine with a circulating fluidized bed cooling system to provide cooling to certain parts of the engine such as a transition duct or a stator vane. The circulating fluidized bed cooling system can be used to cool a stator vane, a casing, or any stationary part of the engine. A circulating fluidized bed cooling system uses very fine particles that pass along with a cooling fluid such as cooling air and provide for a much higher heat transfer coefficient than does turbulent flow cooling air because of the particles. The fine particles produce conduction cooling from the hot surface to the particles that are then carried along in the circulating fluid flow to another location where the heat picked up by the particles is then transferred out from the particles.

Abstract: A pilot liquid tube having a pilot liquid fuel inlet, a pilot liquid fuel conduit, a pilot liquid fuel nozzle, and a shroud configured to shield the pilot liquid fuel nozzle. The pilot liquid tube may be installed and/or removed from an injector of a gas turbine engine while the shroud remains fixed to pilot liquid fuel conduit.