A bottoming cycle power system includes an expander disposed on a crankshaft. The expander being operable to receive a flow of exhaust gas from a combustion process and to rotate the crankshaft as the exhaust gas passes through. An absorption chiller system has a generator section having a first heat exchanger to receive the flow of exhaust gas from the expander and to remove heat from the exhaust gas after the exhaust gas has passed through the expander. An evaporator section has a second heat exchanger to receive the flow of exhaust gas from the generator section and to remove heat from the exhaust gas after the exhaust gas has passed through the generator section. A compressor is disposed on the crankshaft and connected to the flow of exhaust gas. The compressor is operable to compress the exhaust gas after the exhaust gas has passed through the second heat exchanger.

A gas turbine engine that includes a compressor, a turbine, a heat exchanger, and a combustor. The compressor is mounted on a rotating shaft with at least one rotor with an inlet and an outlet, and at least one diffuser downstream from each rotor. The turbine includes at least one stator, and at least one rotor with an inlet and outlet located downstream of each stator, and mounted on the rotating shaft as the at least one of the compressor rotors. The inlet of the compressor rotor faces toward the outlet of the turbine rotor. The heat exchanger is configured to preheat the compressed air leaving the compressor by transferring heat from the turbine exhaust. The combustor can be configured for mixing fuel with the compressed air, either upstream or downstream from the heat exchanger, and further configured for igniting the preheated fuel/air mixture located downstream from the heat exchanger.

A high temperature superconductor (HTS) rotating machine having a longitudinal axis and having a first rotational inertia. There is a cylindrical stator assembly disposed about the longitudinal axis and a cylindrical rotor assembly disposed within the stator assembly. The rotor assembly is configured to rotate within the stator assembly about the longitudinal axis. The rotor assembly includes at least one HTS winding assembly which, in operation, generates a magnetic flux linking the stator assembly. There is a cylindrical electromagnetic shield disposed about the at least one HTS winding assembly having a second rotational inertia. There is a cryogenic cooling system for cooling the at least one superconducting winding assembly of the rotor assembly. The second rotational inertia is at least eighty percent (80%) of the first rotational inertia.

A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500 F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.

A power generating unit, control unit and modular power generating system. A power generating unit includes an engine-generator set including an engine that produces mechanical power and a generator mechanically coupled to the engine. The generator converts the mechanical power to electrical power provided to a DC link. The control unit includes at least one controller configured to control fuel flow to the engine based on a voltage of the DC link.

A turbine system structured to generate electricity from waste gas includes a combustor structured to burn gas to heat air, a heat exchanger structured to receive the heated air, and a turbine energy conversion system including a compressor turbine structured to compress ambient air and provide the compressed air to the heat exchanger, wherein the heat exchanger is structured to heat the compressed air with the heated air, a generator turbine structured to be turned by the heated compressed air from the decompressor turbine, and a generator structured to be turned by the generator turbine and to generate electricity in response to being turned. The turbine system further includes a mixer structured to receive excess air from the heat exchanger and the generator turbine and to mix the excess air with ambient air to a desired temperature.

An aircraft starting and generating system includes a starter/generator that includes a main machine, an exciter, and a permanent magnet generator. The system also includes an inverter/converter/controller that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to DC power in a generate mode of the starter/generator. A main bridge gate driver is configured to drive a MOSFET-based bridge during start mode using Space Vector Pulse Width Modulation (SVPWM) and during generate mode using reverse conduction based inactive rectification.

A gas turbine control device for a gas turbine system includes a sensing unit for measuring the rotor speed and the output of the power generator; a speed regulation rate setting unit for calculating an actual speed regulation rate based on the measured rotor speed and the measured output of the power generator, and for setting a reference speed regulation rate based on the actual speed regulation rate and the target speed regulation rate; and a fuel amount control unit for controlling an amount of fuel supplied to the combustor based on the set reference speed regulation rate. Stable system operation is secured by a method of controlling the gas turbine system to satisfy a target speed regulation rate if additional power should be supplied due to sudden load fluctuations or a failure at another power plant.

The invention concerns a method for operating a gas turbine arrangement, wherein the gas turbine arrangement can be actively connected to a grid system and includes a separation of compressor and turbine shaft to operate both components individually as unit. A first unit can include at least one turbine and at least one generator and a second unit can include at least one compressor and least one motor. Various switches are situated along power lines and are actively connected to a frequency converter and/or the grid system, wherein the compressed air duct operating downstream of the compressor includes a flap.

A gas turbine engine comprises a low speed spool and a high speed spool, with each of the spools including a turbine to drive a respective one of the spools. The high speed spool rotates at a higher speed than the low speed spool. A high speed power takeoff is driven to rotate by the high speed spool, and a low speed power takeoff is driven to rotate by the low speed spool. The high speed power takeoff drives a starter generator and a permanent magnet alternator. The low speed power takeoff drives a variable frequency generator.