Abstract: A starter/generator machine for a turbine with a turbine enclosure, an air duct, and a plurality of fan blades is provided. The starter/generator machine includes a plurality of stator elements spaced at intervals in a ring shape adjacent to the air duct and a plurality of rotor elements mounted on the fan blades. The stator elements and the rotor elements are mounted to interact magnetically to exert a force sufficient to move the rotor elements. The stator elements are shaped to minimize air flow interference and are formed with a core, at least one pole, and multiple windings. The spacing between the stator elements and the rotor elements forms an air gap on the order of 5-10 mm, and the number of stator elements is different from the number of rotor elements.

Abstract: An air conditioning system in an aircraft is provided. The system comprises at least one air cycle air-conditioning pack with a compressor comprising a bleed air outlet and with a compressed-air line connected to the bleed air connection, which compressed-air line is connectable to a starter turbine for a main engine. With the use of air from a compressor of an air conditioning pack it is not necessary to switch off the air conditioning pack; bleed air removal from the auxiliary power units becomes obsolete; and, since there is no unnecessary discharge of compressed air from a bleed air system, noise pollution on the ground is reduced.

Abstract: An accessory box for a gas turbine engine has an input gear to be driven by an input shaft. The input gear is engaged to drive a first driven gear on one radial side of a drive axis of the input gear. The first gear drives at least a second driven gear on one radial side of the drive axis, with at least one accessory driven by one of the first and second driven gears. The second driven gear drives a bevel gear arrangement to drive a third driven gear on an opposed side of the drive axis of the input gear. The third driven gear drives at least a second accessory. The accessories are associated with a gas turbine engine.

Abstract: The present invention has the technical effect of reducing the start-up time associated with starting a powerplant machine. An embodiment of the present invention provides a method of starting a powerplant machine, such as, but not limiting of, a turbomachine. An embodiment of the method of the present invention provides a new philosophy for starting a turbomachine. This new philosophy involves testing the turbomachine systems before the start-up process begins.

Abstract: A method of delivering a purge flow through a gas turbomachine includes generating a purge flow, guiding the purge flow through at least one of a combustor assembly and a turbine portion of the gas turbomachine, determining a cumulative purge volume passing through the one of the combustor assembly and the turbine portion of the gas turbomachine to determine a predetermined purge volume, and discontinuing the purge flow once the predetermined purge volume has passed through the one of the combustor assembly and the turbine portion of the gas turbomachine.

Abstract: A method is described for the start-up of a gas turbine comprising the phases of effecting a preliminary purging cycle of the discharge duct (28) of the turbine (20), establishing a predetermined minimum value (FSR1) for the flow of gaseous fuel entering the combustor (14) for a period of time which is adequate for effecting a first attempt at ignition and effecting a first attempt at ignition, effecting an intermediate purging cycle of the discharge duct (28), interrupting the flow of gaseous fuel to the combustor (14), and progressively increasing the value (FSRn) of the flow of gaseous fuel entering the combustor (14), effecting further attempts at ignition until the mixture of air/gaseous fuel has been ignited and the consequent start-up of the turbine (20), or until a predetermined maximum value (FSRmax) of the flow of gaseous fuel has been reached.

Abstract: A gas turbine engine arrangement comprising a first engine section (2), the first engine section (2) comprising a first compressor (4) and a first turbine (6) mounted on a first shaft (8), the gas turbine engine arrangement further comprising at least one further turbine (20) mounted on a second shaft (22) and arranged such that gases exiting the first engine section (2) are ducted to the further turbine (20), wherein said first and second shafts (8, 22) are not mechanically coupled to one another and have respective axes which are offset from each other.

Abstract: An air starter for turbomachine, including a forward casing, an aft casing, an annular exhaust flow path opening up between an aft end of the forward casing and a forward end of the aft casing, and a cylindrical outlet mesh of the exhaust flow path is disclosed. The forward and aft ends of the outlet mesh include devices for axially retaining the forward casing and the aft casing respectively to the mesh. At least one of the devices for axially retaining one of the casings to the mesh enables a relative rotation of the mesh and this casing.

Abstract: A gas turbine engine arrangement comprises a core engine, a power turbine and a propulsor. The core engine comprises at least one compressor and at least one turbine arranged to drive the at least one compressor and the core engine is arranged in a casing. The power turbine is positioned downstream of the at least one turbine and the power turbine is arranged to drive the propulsor. An electrical machine is arranged upstream of the at least one compressor. The electrical machine comprises a stator and a rotor and the electrical machine comprises a motor/generator. A first clutch selectively connects the rotor of the electrical machine to the power turbine and a second clutch selectively connects the rotor of the electrical machine to the at least one compressor of the core engine.

Abstract: Starter control valve failure prediction machines, systems, program products, and computer implemented methods to predict and trend starter control valve failures in gas turbine engines using a starter control valve health prognostic and to make predictions of starter control valve failures, are provided. A computer implemented method according to an embodiment of the present invention can include the steps of generating a continuous starter control valve deterioration trend function responsive to a plurality of health indices derived from gas turbine engine startup data downloaded from gas turbine engine sensors for a plurality of startups and analyzing the continuous starter control valve deterioration trend function to identify potential starter control valve failure points where the points on the starter control valve deterioration trend function correlate to a starter control valve health prognostic responsive to historic gas turbine engine startup data downloaded from gas turbine engine sensors.

Abstract: In a burner for injecting mixed gas fuel containing at least one of hydrogen and carbon monoxide into a combustion chamber of a gas turbine combustor, the burner includes a fuel nozzle for startup from which liquid fuel is injected into the combustion chamber, and a mixed fuel nozzle disposed around the fuel nozzle for injecting the mixed gas fuel. An air swirler is disposed at a downstream end of the mixed fuel nozzle and has a plurality of flow passages from which compressed air is injected into the combustion chamber, and the mixed fuel nozzle has injection ports disposed in the inner peripheral side of the flow passages of the air swirler. Cooling holes formed in the nozzle surface and positioned to face the combustion chamber introduce a part of the mixed gas fuel injected from the mixed fuel nozzle into the combustion chamber.

Abstract: A control disclosed herein for providing fuel to an auxiliary power unit (“APU”) includes a constant speed electrical motor, a first pump driven by the motor; and, a second pump driven by the motor wherein the electric motor, the first pump and the second pump provide fuel at sufficient pressure/flow capacity to run the APU.

Abstract: A gas turbine engine includes a variable inlet guide vane positioned forwardly of a low pressure compressor. The angle of the inlet guide vane is controlled at startup to increase airflow into the compressor. This is particularly useful when the gas turbine engine is being restarted while an associated aircraft is in the air, and is relied upon to increase windmill speed of the compressor and turbine rotors. A method and nozzle are also disclosed.

Abstract: A combined cycle power plant is provided and includes a gas turbine engine to generate power, a heat recovery steam generator (HRSG) to produce steam from high energy fluids produced from the generation of power in the gas turbine engine, a steam turbine engine to generate additional power from the steam produced in the HRSG and a thermal load reduction system to reduce thermal loading of components of the HRSG and/or the steam turbine engine during at least startup and/or part load operations, which includes an eductor by which a mixture of compressor discharge air and entrained ambient air is injectable into the HRSG and/or an attemperator to cool superheated steam to be transmitted to the steam turbine engine.

Abstract: A jet engine (1) includes at least one emergency drive unit (10), with the jet engine (1) having at least one engine shaft (2a) coupled via at least one gear train (4) with at least one auxiliary gearbox (7), which is connected to at least one auxiliary equipment (8), especially an electric generator. The emergency drive unit (10) includes at least one rotatable component. In order to provide a jet engine with an emergency drive unit in a simple configuration, the rotatable component of the emergency drive unit (10) is attached to the gear train (4).

Abstract: One embodiment of the present invention is a unique vehicle. Another embodiment is a unique propulsion system. Yet another embodiment is a unique system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for vehicle propulsions systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: The system and method of the present invention provides stepping speed control of a gas turbine engine to reliably light-off a gas turbine engine. During starting, the speed of the gas turbine engine is incremented by stepped amounts through the light-off window from a minimum speed value to a maximum speed value, with the speed of the gas turbine dwelling at each stepped value for a period of time before incrementing the speed of the engine to the next stepped level. If the gas turbine engine is stepped through the entire light-off window without success, the controller decreases the speed of the gas turbine engine to the minimum value and begins the process again. The process continues until successful light-off is initiated or until the light-off window is traversed a certain number of times, after which the start process is aborted.

Abstract: A system to mitigate thermal lag of start-up operations of a gas turbine is provided and includes a housing which is disposed upstream from and which is fluidly coupled to a compressor of the gas turbine, a first system coupled to an aft portion of the compressor and to the housing which, when activated, receives a first air supply from the compressor and delivers the first air supply to the housing, and a second system, coupled to the first system, which removes a second air supply from an intermediate portion of the compressor and delivers the second air supply to the first system prior to the activation of the first system.

Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine powered aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: An assembly for a gas turbine engine comprising an accessory gearbox comprising a drive gear and pinion gear and a starter/generator mechanically mounted to the accessory gearbox. The starter/generator comprising a housing and a portion of a rotatable shaft with a safety disconnect where the safety disconnect is located within the housing of the starter/generator.

Abstract: One embodiment of the present invention is a unique aircraft. Another embodiment is a unique aircraft propulsion system. Still another embodiment is a unique system for taxiing an aircraft without starting one or more main aircraft propulsion engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft taxiing and propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: An object of the present invention is to provide a method of starting and stopping a gas turbine and a start-and-stop control device, which are capable of solving a problem of a failure in normally igniting a fuel gas due to a purge gas (nitrogen gas) remaining in a fuel gas pipe and thereby igniting the fuel gas stably.

Abstract: There is described a method for operating an automation system which comprises at least two measuring modules, each connected to a higher order processing unit in order to communicate therewith. The higher order processing unit is informed of an event that is recorded by one of the at least two measuring modules. The processing unit then informs any available measuring module of the event.

Abstract: A pneumatically driven turbine drive system is coupled to a gas turbine engine that includes low and high pressure compressors, low and high pressure turbines, a lock-up clutch, and at least one engine accessory driven by the high pressure compressor. The pneumatically driven turbine drive system selectively bleeds air discharged from the high pressure compressor and supplies it to an air turbine that is coupled to the at least one engine accessory. Thus, the system selectively reduces the power extracted from the high pressure compressor and is capable of supplying power back to the engine core. This, coupled with the bleed air that is diverted from the high pressure turbine and the low pressure turbine, allows the high pressure spool and the low pressure spool to run at lower speeds when high engine thrust is not needed or desired, but when the at least one engine accessory is still needed.

Abstract: A starter/generator machine for a turbine with a turbine enclosure, an air duct, and a plurality of fan blades is provided. The starter/generator machine includes a plurality of stator elements spaced at intervals in a ring shape adjacent to the air duct and a plurality of rotor elements mounted on the fan blades. The stator elements and the rotor elements are mounted to interact magnetically to exert a force sufficient to move the rotor elements. The stator elements are shaped to minimize air flow interference and are formed with a core, at least one pole, and multiple windings. The spacing between the stator elements and the rotor elements forms an air gap on the order of 5-10 mm, and the number of stator elements is different from the number of rotor elements.

Abstract: The present technology generally relates to jet engines, in particular for an aircraft, having at least one turbine shaft on which at least one compressor and a turbine are arranged, and a housing extends over the lateral surfaces of the jet engine, wherein furthermore at least one electrical generator unit for generating electricity is arranged on at least one turbine shaft, wherein the electrical generator unit has a locating plate and a generator, wherein the generator unit is detachably mounted on the engine-side locating plate. Therefore, a jet engine having a generator unit is provided which permits simple installation, removal and servicing of the generator unit in or out of the jet engine.

Abstract: A method and apparatus are disclosed for a multi-spool gas turbine power plant which utilizes motor/generator devices on two or more spools for starting the gas turbine and for power extraction after starting. Methods are disclosed for controlling engine responsiveness under changing load and/or ambient air conditions; providing a momentary power boost when required; providing some engine braking when needed; providing over-speed protection for the free power turbine when load is rapidly lowered or disconnected; charging an energy storage system; and restoring the compressors and/or turbines toward their operating lines when surge or choking limits are approached.

Abstract: A method for gas turbine start-up can include placing a static starter in a torque control mode, sending a torque reference to the static starter to establish a startup torque for the gas turbine, setting current set points for the static starter and modulating a current output to achieve the startup torque.

Abstract: System, methods and apparatus for dynamic control of mixing of diluent and fuel at desired diluent-to-fuel ratios to obtain low level of undesirable emissions in a combustion system are described.

Abstract: In a cooling system used in cooling of a heater housing box, the present invention presents an apparatus for stabilizing power supply of heater housing box cooling apparatus capable of changing over a plurality of taps provided in the winding of a power transformer before the output voltage exceeds an allowable voltage range when turning on alternating-current power supply. For this purpose, first resistor 1 for elevating slowly the output voltage of the power transformer when turning on the alternating-current power supply is provided at the secondary side of the power transformer, direct-current voltage V1 rectified and smoothed from the output voltage is delayed by the charging time of a first capacitor, and an electronic controller for operating a tap changeover relay for automatically changing over the plurality of taps provided in the power transformer is started before the output voltage exceeds the allowable voltage range.

Abstract: A power take-off system for a gas turbine engine includes a starter coupled to a second spool, and a clutch assembly coupled between the starter and a first spool, the clutch assembly configured to couple the first spool to the starter when starting the gas turbine engine assembly. A method of assembling a gas turbine engine assembly that includes the power take-off system, and a gas turbine engine assembly including the power take-off system are also described.

Abstract: A method for assembling a gas turbine engine including a core gas turbine engine, a low-pressure turbine, a starter, and a generator is provided. The method includes coupling a starter to the core gas turbine engine, and coupling a generator to the low-pressure turbine.

Abstract: An embodiment of the present invention provides a method of starting a powerplant machine, such as, but not limiting of, a turbomachine set to operate in a Fast Start mode. The turbomachine may include, but is not limited to, a steam turbine, a heavy-duty gas turbine, an aero-derivative gas turbine, and the like. An embodiment of the method of the present invention provides a new philosophy for controlling a starting system associated with the turbomachine. An embodiment of the present invention may be applied to a powerplant having multiple turbomachines and a starting system having multiple starting means, which may include at least one LCI system. Here, an embodiment of the present invention may eliminate the manual process of preparing and integrating a desired turbomachine with a desired starting means.

Abstract: Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine.

Abstract: An engine starting apparatus and method may allow for two methods of engine start where only one engine gearbox accessory pad exists off the aircraft engine. A gearbox lubricating apparatus may also be provided to lubricate the gearbox at altitude without added complexity. Two engine starting inputs (for example, one input for ground start and one input for in-flight engine start) are provided while avoiding complex gearbox designs. Clutches may also be used to prevent the starter gearbox from continuous operation (rotation) after the engine has started. Apparatus and methods are also provided for improving the air-fuel combustion of the hot-gas turbine start input (for in-flight engine start) to minimize the build-up of solid carbon (soot) in and around the combustor and turbine nozzle flow passages.

Abstract: In a gas turbine power plant, pressurized fuel gas undergoes pressure reduction and gas expansion before being provided to a gas turbine. Condensations, which can damage the turbine, can form as the fuel gas cools when the fuel gas undergoes the pressure reduction and expansion. An electric startup heater is used to superheat the fuel gas to substantially prevent the condensations from forming. The electric startup heater includes band heaters wrapped externally to a fuel gas pipe to heat the fuel gas from outside in. Compared to conventional heaters which provide superheating through internal heating elements, the electric startup heater reduces costs and provides increased safety, flexibility, operational efficiency and ability to adapt to varying fuel gas characteristics.

Abstract: The present invention discloses a turbine assembly (20b) driven by predetermined deflagration of anaerobic fuel. The use of anaerobic fuel enables operation without any necessity for an additional oxidant, and leads to more efficient and environmentally friendly turbine operation. In addition, the gaseous products of the deflagration can be used for any number of purposes after they have passed through the turbine, e.g. combustion of the inflammable portion can drive a second turbine stage (214, 216) or be used to heat air or water.

Abstract: A turboprop propulsion unit for an aircraft comprises a propeller 22 which is driven by a core engine by means of a propeller turbine 26 which drives the propeller 22 through a shaft 28 and a propeller gearbox 24. Restarting of the engine in flight is achieved by windmilling of the propeller 22, which drives a propeller gearbox lubricant pump 30. A diverter valve 40 causes lubricant delivered by the propeller gearbox lubricant pump 30 to be supplied to a turbomachinery lubricant pump 18 along a restart conduit 44, so as to drive the turbomachinery lubricant pump 18 as a motor. Torque generated by the turbomachinery lubricant pump 18 is transferred through an accessory gearbox 12 to a spool 4, 6, 8 of the core engine 2 and to a fuel pump 16. Control of the pitch of blades 36 of the propeller 22 enables the windmilling propeller 22 to achieve a desired speed of the spool 4, 6, 8 and output of the fuel pump 16 sufficient to restart the engine 2, even at low air speeds.

Abstract: In order to start a turbine engine (10), high-pressure fluid is directed onto a turbine (34a) to cause rotation of the turbine and thereby start the turbine engine. In a disclosed embodiment, the high-pressure fluid is provided through a fluid outlet (120) in a vane (36a) positioned adjacent the turbine (34a). The high-pressure fluid is provided by an air source, which may be another turbine engine, especially where the turbine engine to be started is a tip turbine engine that is not the primary propulsion source.

Abstract: A starter-generator system for a tip turbine engine includes a starter motor with a fixed starter generator stator and a starter generator rotor. The fixed starter generator stator is mounted to a static inner support housing. The starter generator rotor surrounds the fixed starter generator stator and is engagement with the axial compressor rotor.

Abstract: The method and apparatus for in-flight relighting of a turbofan engine involve in one aspect selectively controlling an accessory drag load on one or more windmilling rotors to permit control of the windmill speed to an optimum value for relight conditions.

Abstract: A method and apparatus for measuring a start fuel flow to a pilot nozzle of a fuel system of a gas turbine engine using pressure differential between fuel passages leading to fuel nozzles.

Abstract: A method of starting a gas turbine engine by use of a start sequence is provided. Turbine speed and fuel delivery are coordinated so as to provide a fuel/air mixture at an ignition device allowing a successful ignition. If a successful ignition has not occurred by end of the start sequence the gas turbine engine is purged and the start sequence is repeated after the purging of the gas turbine engine.

Abstract: The present application provides for a gas turbine engine system for turbine deceleration during shutdown procedures. The gas turbine engine system may include a rotor extending through a turbine, a generator engaged with the rotor, and a starting system in communication with the rotor. The starting system may reverse the operation of the generator so as to apply torque to the rotor during the shutdown procedures.

Abstract: A powerplant (8) is provided with a drive shaft (4) and at least one engine (1) having an outlet shaft (2) that is necessarily set into rotation during starting of the engine (1), the drive shaft (4) being suitable for setting a mechanical system (7) into motion. The powerplant (8) includes a link member (3) having a clutch (15) and a declutchable freewheel (25) for mechanically linking the outlet shaft (2) to the drive shaft (4).

Abstract: One aspect relates to a hybrid propulsive technique, comprising providing a flow of a working fluid through at least a portion of an at least one jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to a torque. The hybrid propulsive technique also comprises rotating an at least one independently rotatable compressor stator at least partially responsive to the converting the at least a portion of the electrical power to the torque.

Abstract: One aspect relates to a hybrid propulsive technique, comprising providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique includes extracting energy at least partially in the form of electrical power from the working fluid, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique further includes rotating an at least one substantially axial-flow independently rotatable compressor rotor at least partially responsive to the converting the at least a portion of the electrical power to torque.

Abstract: A system and method is provided that facilitates improved fault detection. The fault detection system provides the ability to detect symptoms of fault in the fuel system of a turbine engine. The fault detection system captures selected data from the turbine engines that is used to characterize the performance of the fuel system. The fault detection system includes a feature extractor that extracts salient features from the selected sensor data. The extracted salient features are passed to a classifier that analyzes the extracted salient features to determine if a fault is occurring or has occurred in the turbine engine fuel system. Detected faults can then be passed to a diagnostic system where they can be passed as appropriate to maintenance personnel.

Abstract: An apparatus and method is provided to start gas turbine engines at cold start. A gearbox is not mechanically coupled to any accessory or to the starter-generator. Rather, a controller is used to route power to a starter-generator to rotate the turbine mainshaft to start the gas turbine engine. The controller prevents power to an accessory drive motor, until the starter-generator creates a positive torque. When a positive torque is reached, excess power is routed to the accessory drive motor, typically a brushless direct current motor.

Abstract: An integrated electric gas turbine comprises a compressor that includes a plurality of airfoils. An electric motor is arranged to drive the compressor, and a combustor is arranged to receive compressed air from the compressor and further arranged to receive a fuel input. A turbine is arranged to receive the combustion gases from the combustor. A generator is integrated with the turbine and arranged to provide a power output. A controller is connected between the generator and the electric motor and arranged to direct a portion of the power output from the generator to the electric motor.