Abstract: An air storage plant comprises a storage volume for a pressurized storage fluid, a storage fluid expansion machine and a generator which is arranged with the expansion machine on a common power train. During the start up of the air storage plant, the generator is operated at least temporarily electromotively in order to assist the acceleration of the rotor of the expansion machine. This allows a more rapid acceleration of the expansion machine to the rated rotational speed and, consequently, earlier synchronization and an earlier power output than acceleration caused solely by the storage fluid flowing through.

Abstract: A method for implementing a system and a device for enhancing the starting process of a turbine engine by use of at least one solid mass of oxidizing-species-releasing material, ORM, selected as a solid oxidizer, or SO, and/or as an oxidizing-species-releasing burning substance, or ORBS. The ORM is introduced into the combustion chamber of the turbine engine and the starting process of the turbine engine is initiated, by help of the igniter and in association with the mass of ORM, to enhance the starting process. In operation, an ORM selected as an SO releases gaseous oxygen when heated to decompose, while an ORM chosen as an ORBS discharges oxidizing species when ignited to burn. An ORM such as an SO or an ORBS may operate alone or in various combinations of both. The ORM is configured to release a predetermined mass flow rate of oxidizing species or of gaseous oxygen.

Abstract: A bi-modal turbine assembly is provided for use in conjunction with a gas turbine engine. In one embodiment, the bi-modal turbine assembly includes a housing assembly having a flow passage therethrough, a turbine wheel rotatably mounted in the housing assembly and positioned so as to be driven by pressurized air flowing through the flow passage, an output shaft rotatably mounted in the housing assembly, and first and second gear trains disposed in the housing assembly. A switching device is also disposed in the housing assembly and configured to mechanically couple: (i) the first gear train between the turbine wheel and the output shaft in a first operational mode, and (ii) the second gear train between the turbine wheel and the output shaft in a second operational mode.

Abstract: A gas turbine includes at least one multi-stage compressor unit 2, with the compressor unit 2 including several, independent compressor modules 3-5, which, independently of each other, are rotatably borne on a drive shaft 1 and are each engageable with the drive shaft 1 by at least one clutch unit 9-11.

Abstract: There is a necessity to provide power for some aircraft service functions whilst the main engines (34) are not operational, for example when the aircraft is on the ground, and to start the main engines (34). This demand is met by provision of auxiliary power units (21). Conventionally a single auxiliary power unit (2) is located in the tail of the aircraft and requires fuel lines and relatively high capacity electrical cabling in order to provide electrical power for main engine starting and service functions. The present invention provides an auxiliary power unit (21) mounted on each main engine (34) and coupled together through an electrical distribution system. This provides greater redundancy in the event of failure of an auxiliary power unit (21) as well as reducing overall weight.

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: Methods and apparatus for fast starting and loading a combined cycle power system are described. In one example embodiment, the method includes loading the gas turbine at up to it's maximum rate, and loading the steam turbine at its maximum rate with excess steam bypassed to the condenser while maintaining the temperature of steam supplied to the steam turbine at a substantially constant temperature from initial steam admission into the steam turbine until all steam generated by the heat recovery steam generator is being admitted to the steam turbine while the gas turbine operates at up to maximum load.

Abstract: A turbine installation includes a main group and an auxiliary group, wherein the main group has at least one first turbine and a generator connected for drive purposes to the first turbine. The auxiliary group includes at least one second turbine and is connectable to the main group via a coupling. The turbine installation furthermore includes a first braking device configured to apply a braking torque to the auxiliary group when the auxiliary group is decoupled from the main group.

Abstract: Starter arrangement for high power rotating equipment strings with multiple compressors driven by a single turbine or motor includes multiple variable fluid drive torque converters (CSTCs) to start the compressors in a pressurized start. The string can use a single CSTC for each compressor or a single CSTC for more than one compressor with at least two CSTCs for a given string. The starting procedure is sequential. After the turbine or motor is started and brought up to speed, successive CSTCs are operated from zero to lock-up speed sequentially to start each compressor or group of compressors in turn. In order to cool the working fluid of the CSTCs, a single heat exchanger is provided and the working fluid of each CSTC in turn is circulated through the heat exchanger as they are sequentially started.

Abstract: A system, method and apparatus for monitoring the performance of a gas turbine engine. A counter value indicative of the comparison between the engine condition and the threshold condition is adjusted. The aircraft operator is warned of an impending maintenance condition based on the counter value and determines an appropriate course of action.

Abstract: A gas turbine which can detect ignition in a combustor regardless of startup conditions of the gas turbine, such as the hot startup or the cold startup. An ignition detecting method for the gas turbine comprises the steps of calculating a difference between the exhaust temperature detected at a particular time before outputting of an ignition command for a combustor and the exhaust temperature detected after the outputting of the ignition command, and determining that the combustor is ignited, when the calculated difference is not less than a predetermined value. As an alternative, the method includes a step of determining that the combustor is ignited, when a change amount or rate of the exhaust temperature exceeds a predetermined value in a predetermined period from the outputting time of the ignition command.

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 gas turbine engine incorporating a starter mounted on the gear box The present invention refers to a gas turbine engine, comprising an AGB gear housing (12) mechanically connected with an engine shaft for driving auxiliary machines and an air starter (10, 10?) mounted on the housing, the starter and housing enclosures being in communication such that the lubricating oil of the starter should be distributed from the AGB housing. The engine is characterized in that the oil enclosure of the starter (10, 10?) is pressurized by a source of air, being independent from the AGB housing. Advantageously, the pressurization air is taken from a pressurization enclosure of an engine bearing.

Abstract: Methods and systems for starting aircraft turbofan engines are disclosed. A system in accordance with one embodiment includes an electrically-powered starter motor coupled to a turbofan engine to provide power to the turbofan engine during an engine start procedure. The system can further include an on-board, deployable, ram air driven turbine coupled to an electrical generator, which is in turn coupled to the starter motor to provide electrical power to the starter motor. In other embodiments, the ram air driven turbine can be replaced with a fuel cell or a battery. In still further embodiments, a single controller can control operation of both the engine starter and other motors of the aircraft.

Abstract: A dual channel ignition circuit (Channel A and a Channel B). In a start sequence in which a successful ignition event occurs, an exciter controller first energizes only a primary ignition channel (Channel A). Once the exciter controller recognizes a success light-off, the alternate channel (Channel B) will also then be excited as the gas turbine engine is accelerated to a self-sustaining speed. The exciter controller will then switch the primary alternative designation of the channels for the next start attempt. In a start sequence in which an unsuccessful ignition event occurs, the exciter controller sets a fail-to-start on the primary ignition channel on a failure to start A/B counter such that a failed ignition channel is diagnosed without dedicated electronic diagnostic circuits while still attempting to excite both circuits to enhance the dependability of a successful engine light-off.

Abstract: A system and method is provided for startup characterization in a turbine engine that provides the ability to accurately characterize engine startup. The startup characterization system and method uses engine temperature sensor data and engine speed sensor data to accurately characterize the startup of the turbine engine by determining when several key engine startup conditions are reached. By storing and analyzing engine sensor data taken during these key conditions of engine startup, the system and method is able to accurately characterize the performance of the engine during startup. This information can be used as part of a trending system to determine when faults in the start transient regime are occurring or likely to occur. Additionally, this information can be used in real time by control systems to better control the startup and operation of the turbine engine.

Abstract: A method of controlling fuel flow to a combustor (18) of a gas turbine engine (10) during startup of the engine includes determining a relationship between Cv and valve position for a flow control valve (e.g., 24) in a fuel supply (20) to the combustor as a function of at least one real time parameter of fuel (30) in the fuel supply. The method also includes determining a value of the at least one parameter of the fuel before initiating a flow of the fuel to the combustor, and then calculating a first actual Cv value for the flow control valve at a target flow rate using the determined value of the parameter. The method then includes positioning the flow control valve to a first position corresponding to the actual Cv value based upon the determined relationship between Cv and valve position, and initiating the flow of fuel to the combustor through the flow control valve.

Abstract: A combustion chamber device having a field static pressure gradient adapted to expel a flame kernel or hot spot from a fuel-air mixing duct. The swirling flow passing through an annular mixing duct is turned from a radial direction to an axial direction before entering the combustion chamber. An ignition source located within the fuel-air mixing duct can then be used to start the combustion process in the gas turbine.

Abstract: During operation of a power generating plant, which essentially comprises a gas turbogroup, a compressed air accumulator, an air turbine which is equipped with at least one generator, the compressed air which is extracted from the compressed air accumulator is directed through a heat exchanger, which acts on the outflow side of the gas turbogroup, and is thermally conditioned there. This compressed air then charges the air turbine, wherein during a “black out” or other shutdown of the power generating plant, the electric current energy which can be obtained by means of the thermally conditioned compressed air in the air turbine, via a power line is used directly for start-up of the gas turbogroup.

Abstract: A method of operating a gas turbine engine having a turbine and a compressor connected via a shaft, a main fuel supply line for supplying fuel to a combustor that is positioned to release expanding hot gases to the turbine, the engine further including a starter/generator connected to the shaft via a gearbox assembly, the method is characterised the step of during engine start up fuel is circulated in a re-circulating fuel circuit positioned on the main fuel supply line and which a first fuel/oil heat exchanger, for cooling the oil, and a fuel accumulator.

Abstract: A method of operating a power generation system is provided. The system includes a first gas turbine engine that uses at least one of a primary fuel and a secondary fuel, and at least one second gas turbine engine that operates using at least one of a primary and secondary fuel. The method includes supplying primary fuel to at least one of the first and second engines from a common fuel source coupled to the first and second engines, and selectively operating the first engine between a first operational position and a second operational position. The first engine using only secondary fuel in the first operational position and operates using only primary fuel in the second operational position. The method includes supplying the second engine with primary fuel from the common fuel source without flaring the primary fuel.

Abstract: At least one of the main injectors of the engine, forming a starter main injector, is fed directly by the pressurized feed pipe, while a head loss is imposed between the pressurized feed pipe and the other main injectors. Ignition is caused to take place at the starter main injector, and after ignition, said head loss imposed between the feed pipe and the other main injectors is eliminated so that all of the main injectors are fed with fuel at substantially the same pressure, without any imposed head loss.

Abstract: An aircraft gas turbine engine including a first hydraulic pump connected to a starter motor and a second hydraulic pump connected to the high-pressure compressor. The engine being arranged such that during starting the starter motor drives the first pump, to pump hydraulic fluid to operate the second pump as a motor to drive the high pressure compressor. During running the first and second pumps are connected to the aircraft hydraulic system.

Abstract: A modular method of modeling a power plant includes selecting a major component module model from a library of component module models for each major component of the power plant, with each major component module representing a power plant major component of a unique configuration. The method also includes inputting initial model information into a database for the selected modules, with the initial model information including at least convergence criteria and a maximum number of passes. The method further includes running the modular model by running each selected module and enabling data exchange between the selected modules.

Abstract: An aspect of the invention is directed towards a method and device for optimizing a light-up procedure of a gas turbine engine. An aspect of the method comprises repeating an engine start attempt with amended light-up parameter values or range of light-up parameter values, where the values are amended by a predefined scheme including recording the light-up parameter value or the range of light-up parameter values of each start attempt together with the light-up success rate achieved in the respective start attempts, and optimizing the light-up parameter value or range of parameter values by analyzing the recorded data after the start attempts have been finished. An aspect of the device is to provide a control unit that implements the inventive method.

Abstract: A system and method is provided for lightoff detection in a turbine engine that provides improved accuracy and consistency. The system and method use engine temperature and engine rotation speed sensor data to determine a first time interval during which the lightoff is estimated to have occurred. A peak gradient in the temperature sensor data within the first time interval and a peak gradient in the engine rotation sensor data within the first time interval are then determined. The temperature peak gradient time and the engine rotation peak gradient time are then used as boundaries to determine a narrowed time interval within the first time interval. The minimum gradient in the engine rotation sensor data in the narrowed time interval is determined, with the minimum gradient time in the engine rotation sensor data comprising an accurate estimate of lightoff time for the turbine engine.

Abstract: A method and an apparatus for starting a gas turbine engine under various conditions are used to distribute a varying total amount of electric power to at least one of a starter, a fuel heater and an oil heater while providing fuel.

Abstract: A synchronizing stationary clutch system for compression braking in a two spool gas turbine engine is provided by the present invention. The synchronizing stationary clutch system allows the two shafts of a two spool gas turbine engine to be reliably coupled at any given speed of either shaft. This coupling ability is useful to a gas turbine engine functioning in a land vehicle for the purpose of slowing the forward momentum of a rolling vehicle. The clutch system may also allow the use of auxiliary power from an electrical motor to start the engine.

Abstract: A method for combustion in a combustor in a gas turbine including: fueling the center fuel nozzle with a fuel-rich mixture of gaseous fuel and air and fueling the outer fuel nozzles with a fuel-lean mixture of fuel and air; igniting the fuel-rich mixture injected by the center fuel nozzle while the fuel-lean mixture injected by the outer combustors is insufficient to sustain ignition; stabilizing a flame on the center fuel nozzle using the bluff body and while the outer fuel nozzles inject the fuel-lean mixture; staging fuel to the outer nozzles by increasing a fuel ratio of the fuel-lean mixture, and after the outer nozzles sustain ignition, reducing fuel applied to the center nozzle.

Abstract: A gas turbine apparatus is provided which comprises a turbine, a combustor for burning a mixture of air and fuel and providing the turbine with a combustion gas to drive it, a generator connected to the turbine to receive rotational force therefrom to generate electric power, a temperature sensor for measuring a temperature of an exhaust gas from the turbine, a temperature setting unit and a power setting unit.

Abstract: Methods and apparatus are disclosed for starting up a combined cycle plant using a startup duct to connect an auxiliary engine to the inlet of a plurality of HRSGs or other heat recovery systems. Each HRSG is fed by a combustion turbine. Dampers are supplied to isolate each HRSG from the startup duct and its CTG. The auxiliary engine is also ported to a stack allowing simple cycle operation. Dampers are also supplied to isolate the auxiliary engine from the startup duct and from its stack. During startups, the large CTGs will be isolated and the auxiliary engine will be connected to the HRSGs and started, allowing the HRSG to pressurize. As each HRSG pressurizes, it is isolated from the startup duct and connected to its respective CTG. The CTG is then started and loaded. The auxiliary engine is turned off and isolated when the last HRSG pressurizes.

Abstract: A starting system for starting the propulsion engines of gas turbine powered aircraft that combines power sources delivered by the APU so that essentially then entire power delivered by the APU for pneumatic, hydraulic and electric power is applied to corresponding starters on each propulsion engine during MES simultaneously.

Abstract: A helicopter having a helicopter turbine engine disposed therein includes an over-stress protection system. The over-stress protection system includes a computer for storing data and an input such as a keyboard for inputting a safe temperature profile for starting the turbine engine. A temperature sensor is provided for measuring the actual turbine outlet temperature during the start up of the helicopter turbine engine. The actual engine temperature is then compared with the safe engine temperature profile and water and/or alcohol is injected into the engine when an actual temperature exceeds the safe temperature. The use of a ground based tank for use during start up and an airborne tank for in flight use are also disclosed.

Abstract: A method and an appliance are described for supplying fuel to a premixing burner for operating a gas turbine, which premixing burner has at least one burner shell (1, 2) at least partially bounding an axially extending premixing burner space, having a premixing gas supply directed into the premixing burner space via the burner shell (1, 2), the premixing gas (6) being mixed with combustion inlet air and being ignited downstream external to the premixing burner, The invention is characterized by the fact that the premixing gas supply is carried out separately by means of at least two spatially axially separated regions (S1, S2) along the burner shell (1, 2), having a region (S1), which is arranged upstream, and at least a second region (S2), which is arranged downstream, by the fact that more than 60% of the total premixing gas supply takes place via the first region (S1) in order to start the gas turbine, and by the fact that a stepwise or continuous redistribution of the premixing gas supply to the second re

Abstract: A gas turbine starting method, comprising the steps of rotatively driving a turbine by a motor coupled to the turbine, while at the same time supplying a compressed air to a combustor by an air compressor operating in interlocking motion with the turbine, starting a fuel supply to the combustor when a revolution speed of the turbine has reached up to a predetermined value, and simultaneously starting an igniting operation on an air-fuel mixture in the combustor, wherein at least during the igniting operation to the air-fuel mixture in the combustor, a quantity of fuel supply per unit time to the combustor is increased while increasing the revolution speed of the turbine, to thereby ensuring the ignition of the air-fuel mixture under various conditions, and depressing the temperature rise of the gas turbine, which may otherwise occur immediately after the ignition.

Abstract: A method of engine starting in a gas turbine engine comprises rotating the engine to provide an air flow into a combustor of the engine and injecting fuel into the combustor at a varying rate until the engine is lighted-off. The varying rate of the fuel flow is a function of time and is represented by a curve having at least one high frequency with respect to a light-off time, representing instant changes of the rate for intersecting a light-off zone while reducing a quantity of fuel injected into the combustor. After the light-off occurrence fuel is continuously injected into the combustor to accelerate the engine to a self-sustaining operation condition. This method of the present invention is adapted to find light-off points under various temperature and altitude conditions, thereby advantageously providing a rapid light-off, particularly under cold weather conditions.

Abstract: A gas turbine has a cooling air system supplying air for cooling a high temperature part of the gas turbine and a spray air system supplying air for spraying fuel into a combustor and is formed so that a part of high-pressure air compressed by a gas turbine compressor is used as air of the cooling air system and spray air system, wherein a heat exchanger and a boost compressor are arranged downstream of the outlet of compressed air of the gas turbine compressor, and the boost compressor is composed of a parallel connection of a compressor driven by the turbine shaft and ae compressor driven by a driven source other than the turbine shaft, and pressurized air from the boost compressor is used as air for the cooling air system and the spray air system.

Abstract: A variable loading rate method of starting a plurality of gas turbines (GT1, GT2) used in a combined cycle power plant for generating electricity. A first gas turbine is started and allowed to operate at a minimum load condition. The turbine is maintained at this load level while a second gas turbine is started brought up to its minimum load condition. Start-up of a steam turbine (ST) to which the gas turbines are operationally coupled is initiated while both gas turbines are maintained at their minimum load conditions. The load on both gas turbines is then increased to a predetermined level, which is greater than their minimum load levels, once operating temperatures within the steam turbine reach predetermined levels. Subsequently, both gas turbines are loaded as function of the load on the a steam turbine at to which the gas turbines are coupled.

Abstract: A combustor includes outer and inner liners joined together by a dome to define a combustion chamber. A row of air swirlers is mounted in the dome and includes corresponding main fuel injectors for producing corresponding fuel and air mixtures. Pilot fuel injectors fewer in number than the main injectors are mounted in the dome between corresponding ones of the swirlers. Staged fuel injection from the pilot and main injectors is used for starting the combustor during operation.

Abstract: When loading a power station in a grid without any energy, this power station must be able to cover all the short-term power requirements, and at the same time to keep the grid frequency within a permissible tolerance band. The invention specifies a method of providing this capability by means of an efficient combination system. According to the invention, the gas turbine (1) is loaded in a lower power range such that it is controlled in accordance with a predetermined load program, without having to react to load transients in the grid (50). Before the power station is connected to the grid, the heat recovery steam generator (5) is heated up as an energy store, and a steam turbine (2) is raised at least to its rated rotation speed, with the steam control valves (9, 15) being highly restricted. The steam turbine reacts in the event of short-term load requirements from the grid, which cannot be covered by the gas turbine.

Abstract: A start system for an expendable gas turbine engine includes a pressurized oxygen source and a pyroflare igniter. The pressure source communicates oxygen to a compressor through a first passage to spin-up a rotor and communicates oxygen to a combustor through a second passage to provide light-off oxygen for the atomized fuel within the combustor. A pressure regulator shuts off the impingement flow at a predetermined pressure and blow down of combustor flow continues for an enhancement period to assure continued operation of the gas turbine even at high altitudes.

Abstract: A purge air and fuel flow divider module (15) independently directs fuel flow to a plurality of manifolds (25, 27 and 29) and independently purges fuel from these manifolds with air when they are not flowing fuel. A secondary manifold (29) is filled with fuel before flowing metered burn flow to it and fuel flow is apportioned between a primary manifold (27) and the secondary manifold (29) during secondary manifold metered burn flow. Three manifolds are disclosed, a primary manifold (27), a secondary manifold (29) and a start or pilot manifold (25), each containing fuel nozzles (31, 33). A manifold main housing (61) contains a purge valve (41) and two three-way solenoids (37, 39) controlling respectively a secondary transfer valve (43) and a pilot nozzle transfer valve (45). Depending on the requirements, the solenoids position the valves to either provide manifold fill fuel, burn flow fuel or purge air to their respective manifolds.

Abstract: A system for starting an APU, including an air control valve assembly located in the air flow passageway extending between a source of pressurized air and a turbine power modulator. The system further includes a fuel control valve assembly located in the fuel flow passageway extending between a source of jet fuel and the turbine power modulator. Upon energizing the air control and fuel control valves, a mixture of compressed air and jet fuel entering the turbine power module is ignited, creating a flow steam of hot gases for driving a gas turbine to power the APU.

Abstract: A gas turbine starting method, comprising the steps of rotatively driving a turbine by a motor coupled to the turbine, while at the same time supplying a compressed air to a combustor by an air compressor operating in interlocking motion with the turbine, starting a fuel supply to the combustor when a revolution speed of the turbine has reached up to a predetermined value, and simultaneously starting an igniting operation on an air-fuel mixture in the combustor, wherein at least during the igniting operation to the air-fuel mixture in the combustor, a quantity of fuel supply per unit time to the combustor is increased while increasing the revolution speed of the turbine, to thereby ensuring the ignition of the air-fuel mixture under various conditions, and depressing the temperature rise of the gas turbine, which may otherwise occur immediately after the ignition.

Abstract: A combustor includes outer and inner liners joined together by a dome to define a combustor chamber. A row of air swirlers is mounted in the dome and includes corresponding main fuel injectors for producing corresponding fuel and air mixtures. Pilot fuel injectors fewer in number than the main injectors are mounted in the dome between corresponding ones of the swirlers. Staged fuel injection from the pilot and main injectors is used for starting the combustor during operation.

Abstract: A method of engine starting in a gas turbine engine comprises rotating the engine to provide an air flow into a combustor of the engine and injecting fuel into the combustor at a varying rate until the engine is lighted-off. The varying rate of the fuel flow is a function of time and is represented by a curve having at least one high frequency with respect to a light-off time, representing instant changes of the rate for intersecting a light-off zone while reducing a quantity of fuel injected into the combustor. After the light-off occurrence fuel is continuously injected into the combustor to accelerate the engine to a self-sustaining operation condition. This method of the present invention is adapted to find light-off points under various temperature and altitude conditions, thereby advantageously providing a rapid light-off, particularly under cold weather conditions.

Abstract: An internal combustion engine includes an insulated combustion chamber having a fuel mixture inlet and a spark plug nearby the inlet. A series of baffles is configured within the combustion chamber to absorb a shockwave caused by ignition of fuel mixture by the spark plug. A turbine receives reduced-pressure combustion gases from an exhaust-side of the baffles and there is a power takeoff at the turbine.

Abstract: A method for gas turbine light-off that utilizes a fixed or secondary fuel line that provides a substantially constant flow of fuel to the combustor primarily upon light-off.

Abstract: A method of operating a turbine arranged in a compressed air energy storage power generation plant comprises an open-loop control of an air mass flow applied within a lower turbine speed range and a closed-loop control of the turbine speed within a higher turbine speed range. The open-loop control comprises the control of the air mass flow by means of air inlet valves and a free development of the turbine speed. The closed-loop control comprises the control of the turbine speed by means of a speed controller, which is acted upon by a speed limiting value determined according to the current air mass flow and a windage calculation. The speed controller activates a static frequency converter in the case that the turbine speed reaches values that are critical with respect to turbine windage or rotor dynamics.

Abstract: A gas turbine has a cooling air system supplying air for cooling a high temperature part of the gas turbine and a spray air system supplying air for spraying fuel into a combustor and is formed so that a part of high-pressure air compressed by a gas turbine compressor is used as air of the cooling air system and spray air system, wherein a heat exchanger and a boost compressor are arranged downstream of the outlet of compressed air of the gas turbine compressor, and the boost compressor is composed of a parallel connection of a compressor driven by the turbine shaft and ae compressor driven by a driven source other than the turbine shaft, and pressurized air from the boost compressor is used as air for the cooling air system and the spray air system.