A gas turbine system and method is provided. The proposed gas turbine system includes a combustor with at least one burner. The burner has an entry for introducing a fuel into an operating medium composed of a gas containing an oxidant to facilitate combustion of the fuel. In operation, the combustion of the fuel generates a flame and a resulting combustion gas. The provided gas turbine system includes at least one oxygen sensor located downstream of the flame, and measures an oxygen concentration of the combustion gas at that location. Further, the proposed gas turbine system includes a device to determine the temperature of the flame based upon the measured oxygen concentration of the combustion gas at the location of at least one oxygen sensor.

Gas turbine system and method

A system includes a radiation sensor configured to direct a field of view toward at least one conduit along a fluid flow path into a heat exchanger. The radiation sensor is configured to output a signal indicative of a temperature of the at least one conduit. The system also includes a controller communicatively coupled to the radiation sensor. The controller is configured to determine the temperature based on the signal, to compare the temperature to a threshold range, and to adjust a fluid flow through the fluid flow path or the at least one conduit if the temperature deviates from the threshold range.

Thermal control system for fault detection and mitigation within a power generation system

A system includes a radiation sensor configured to direct a field of view toward a conduit within a heat recovery steam generator, and to output a signal indicative of a temperature of the conduit The system also includes a controller communicatively coupled to the radiation sensor The controller is configured to determine the temperature based on the signal, and to compare the temperature to a threshold value

Thermal measurement system for fault detection within a power generation system

A rotating electric machine comprises a stator and a rotor. In the rotor, numerous slots are formed along a circumferential direction. In the each of slots, a first stator coil and a second stator coil are inserted and insulated by an insulator inserted before inserting the coils in the slots. The insulator encircles the first and second stator coils so as to be formed into an S shape. The center portion thereof extends over the area between the first and second stator coils. One end of the insulator is held between one surface of the center portion of the insulator and the first stator coil. Other end of the insulator is held between another surface of the center portion of the insulator and the second stator coil.

Rotating electric machine

A turbomachine comprises a turbine shaft, first and second rotors, first and second propulsion stages, and a magnetic stator. The first rotor is rotationally coupled to the turbine shaft, and coaxially arranged along an axis. The first propulsion stage is rotationally coupled to the first rotor, opposite the turbine shaft. The second rotor is coaxially arranged about the first rotor, and the second propulsion stage is rotationally coupled to second rotor, opposite the turbine shaft and adjacent the first propulsion stage. The magnetic stator is coaxially arranged between the first rotor and the second rotor, forming a magnetic coupling between the and second rotors to drive the second propulsion stage in contra-rotation with respect to the first propulsion stage.

Magnetically coupled contra-rotating propulsion stages

A system and a method for detecting gas turbine engine hot section condition using temperature measurements during engine operation. The system comprises a sensing unit for sensing a temperature distribution across a hot combustion gas stream generated by a gas turbine engine combustor. A signal processor receives temperature signals from the sensing unit and generates a combustor malfunction signal when the difference between a maximal temperature and a minimal temperature of the sensed temperature distribution is greater than a predetermined acceptable delta value.

Detection of gas turbine engine hot section condition

A gas turbine engine including a first shaft being one of a main shaft concentrically mounted to at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom, the first shaft having a reduced diameter portion located within the gas turbine engine, an electrical assembly having a rotor comprising permanent magnets retained on an outer surface of the reduced diameter portion and a stator comprising a magnetic field circuit disposed adjacent an outer periphery of the rotor, and an electrical connection between the magnetic field circuit and at least one of a power source and an electrically drivable accessory.

Gas turbine with magnetic shaft forming part of a generator/motor assembly

An engine casing for a gas turbine engine, such as, but not limited to, a gas turbine engine fan case, is disclosed which includes an annular case shell formed of a substrate material that is at least partially coated by a nanocrystalline metal coating. A method of manufacturing such an engine casing is also provided. The present engine casing provides improved containment capability in the event of a blade release or other failure during operation of the engine.

Gas turbine engine casing

A hybrid vane airfoil for a gas turbine engine, such as a vane of a compressor stator, is disclosed which includes a non-metallic core, and an outer metallic shell at least partially covering the non-metallic core and which defines an outer surface of the airfoil. The non-metallic core is composed for example of a polymer, and the metallic outer shell is composed of a nanocrystalline metallic coating.

Metal encapsulated stator vane

A method of manufacturing a vane component of a gas turbine engine is described, and includes forming a core of the vane component using a rapid manufacturing process, and applying a coating of nanocrystalline metal onto the core, the nanocrystalline metal fully encapsulating the core and defining an outer structural surface of the vane component.

Nano-metal coated vane component for gas turbine engines and method of manufacturing same

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