Abstract: The invention relates to a method for starting a power plant (1), in particular a gas storage power plant, with the following steps: S1: ignition of an auxiliary combustion chamber (19), S2: operation of the auxiliary combustion chamber (19) in such a way that the consequently heated gas introduced into a first flow path (13) has a temperature which is below a self-ignition temperature of a fuel/oxidizer/gas mixture delivered to the main combustion chamber (5) for starting the latter, S3: operation of the auxiliary combustion chamber (19) according to step S2, until a recuperator (12) has a predetermined preheating temperature, S4: Starting of a turbine (3) and ignition of the main combustion chamber (5).

Abstract: A combined cycle power plant (10) utilizing an air injection apparatus (60) for lowering the temperature and raising the mass of the exhaust gas provided to the heat recovery steam generator (22) from the gas turbine portion (12) of the plant. The air injection apparatus is utilized during startup of the plant to permit the gas turbine portion to be operated at a power level sufficiently high to ensure compliance with emissions regulations while at the same time not exceeding an upper exhaust temperature limit for warming the steam generator. The augmented exhaust stream (76) allows the steam generator to more quickly generate enough steam to roll the steam turbine (30), thereby shortening the overall startup sequence.

Abstract: An improved air turbine starter that includes fluid flow control devices. The devices may be check valves, for example normally open check valves. The check valves may be located in fluid flow paths between the starter and the gearbox to which it is mounted. The starter may also include a ring seal about the output shaft to restrict fluid flow over the shaft.

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: Methods and apparatus for control of NOx in catalytic combustion systems, and more particularly to control of thermal or/and prompt NOx produced during combustion of liquid or gaseous fuels in the combustor sections of catalytic combustor-type gas turbines, by controlled injection of water in liquid or vapor form at selected locations, orientations, amounts, rates, temperatures, phases, forms and manners in the compressor and combustor sections of gas turbines. The ratio of thermal NOx ppm reduction to water addition, in weight %, is on the order of 4-20, with % NOx reduction on the order of up to about 50-80% and NOx of below 2 ppm. Liquid water, steam or superheated steam can be used to reduce NOx in combustion systems operating at reaction zone temperatures above 900° C., preferably 1400° C. to 1700° C. The amount of water added is sufficient to provide a concentration of water in the range of from about 0.

Abstract: A gas turbine jet engine having a channel in a turbine casing through which a quantity of compressed air from a pressurized air source is introduced to start the gas turbine jet engine. The compressed air is expanded and accelerated by a series of diffusers and then impinges upon at least one impulse-type turbine bucket member located on the tip of a turbine blade to drive the turbine, which drives a compressor to start engine. Alternatively, the channel in the casing is located close to an axial compressor in a gas turbine engine's forward section and drives at least one turbine bucket member on a shrouded integrated compressor/turbine blade to drive the compressor to start the gas jet turbine engine.

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 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 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: The invention relates to a method for starting a power plant (1), in particular a gas storage power plant, with the following steps:

Abstract: A low cost jet engine for ground based application which is constructed with a conventional automotive turbocharger including a compressor and a turbine. An independent small combustor unit is mounted on the turbocharger between the compressor and the turbine and adapted for taking in air from the compressor and combusting fuel with the compressed air to provide an exhaust for driving the turbine. Controls are provided for starting and controlling the operation of the engine. The jet engine is readily adaptable to many land based applications, such as for educational purposes and snow blowing applications.

Abstract: An engine starting system (100) includes a starter (106) coupled to an engine (102) through a rotational energy storage device (108) such as spiral spring (108). When electrical power is applied to the starter (106), the rotational energy produced by the starter (106) is stored in the rotational energy storage device (108) allowing the starter (106) to rotate which reduces electrical currents in the starter and stress on system components. The rotational energy is gradually transferred to the engine (102) until the engine (102) is rotationally self-sustaining.

Abstract: A turbogenerator system including a recuperator and a catalytic combustor employs a preheater located between the turbine outlet and the recuperator low-pressure inlet to heat the low-pressure turbine exhaust. Heat from the turbine exhaust is transferred to a cool high-pressure flow in the recuperator. A recirculation loop employs valves downstream of the recuperator low-pressure outlet to divert the recuperator low-pressure exhaust into the compressor to be recirculated through the recuperator high-pressure side and the catalytic combustor. Reduced start-up times and emissions are achieved by raising the combustor catalyst to its light-off temperature in a shorter period of time.

Abstract: A system configuration and operating method for a single shaft combined cycle plant includes a gas turbine, an exhaust heat recovery boiler for generating steam using exhaust heat discharged from the gas turbine, and a steam turbine driven by steam generated from the exhaust heat recovery boiler. Rotors of the gas turbine and rotors of the steam turbine are coupled. The steam turbine includes a high pressure turbine being supplied with and driven by high pressure steam generated at a superheater of the exhaust heat recovery boiler and a reheating turbine supplied with and driven by steam that passes through the high pressure turbine and is reheated by a reheater of the exhaust heat recovery boiler. The gas turbine operates independently and a regulated amount of cooling steam is supplied to the steam turbine in order to prevent superheating due to windage loss of the steam turbine rotating in an unventilated state.

Abstract: Transient conditions, such as startup, shutdown, and contingencies, in gas turbine power plants are difficult to manage; oftentimes in designs employing a fuel moisturization system, such conditions require the use of backup fuel or a temporary fuel stream flare. The present invention enables the use of cold, dry fuel during startup and smoothly transitions to the use of moisturized, superheated fuel at high load without using a backup fuel. A bypass line allows fuel to enter a fuel superheater without passing through a fuel saturator. This enables the independent operation of the fuel superheater from the fuel saturator. Additionally, dry fuel is heated in the fuel superheater before moisturized fuel enters the fuel superheater. Gradually, a transition from dry fuel to moisturized fuel occurs before the gas turbine system operates at premixed combustion mode of operation.