Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: A gas bottle assembly may be provided for a gas turbine engine system. The gas bottle system may include a gas bottle, a regulator cavity, a conductor coil, and an insulating jacket. The gas bottle may be configured to store and selectively release pressurized fluid. The regulator cavity and conductor coil may be in fluid connection with the gas bottle. The conductor coil may be disposed around at least a portion of the gas bottle. The insulating jacket may disposed around at least a portion of the gas bottle, pressure regulator, and the conductor coil. The conductor coil may be configured to maintain or decrease a temperature of the gas bottle while the insulting jacket resists heat from other portions of the engine system.

Abstract: A pneumatic starter system for a turbine engine. The pneumatic starter system includes a pneumatic starter and a compressed gas storage unit. The pneumatic starter is configured to cause at least one turbine of the turbine engine to rotate. The compressed gas storage unit is configured to store oxygen rich gas and expel the oxygen rich gas to power the pneumatic starting system to cause the at least one turbine to rotate. The pneumatic starter system also includes a first exhaust path configured to direct at least a first portion of the oxygen rich gas exhausted from the pneumatic starter to a turbine combustion zone of the turbine engine to create an oxygen rich fuel mixture.

Abstract: A gas turbine engine includes a turbine and a rotor tip clearance control system. The rotor tip clearance control system is configured to actively manage a clearance formed between a rotor of the turbine and a case structure of the turbine.

Abstract: Turbine-generator systems having an auxiliary power source and methods of operating turbine-generator systems having auxiliary power sources in a high, intermittent load environment are provided. The turbine may be sized to meet substantially all the power required by the intermittent load. The auxiliary power source may have a power rating approximately equal to the power required to rotate the unloaded generator at an operational speed. The method may include decoupling the turbine from the generator, removing the load from the generator, coupling the auxiliary power source to the unloaded generator, and maintaining the operational rotational speed of the generator with the auxiliary power source.

Abstract: A gas turbine health monitoring fuel system including a fuel splitter, a first and second fuel nozzle, a first and second fuel pump, and a common drive coupled to the first and second fuel pumps. The first and second fuel pumps are downstream from the fuel splitter. The first fuel nozzle is fluidly coupled to the first fuel pump by a first fuel stream. The second fuel nozzle is fluidly coupled to the second fuel pump by a second fuel stream. The common drive is configured to drive the first and second fuel pumps at a same speed. The controller system is configured to determine a first fuel pressure in the first fuel stream, determine a second fuel pressure in the second fuel stream, and identify a difference between the first and second fuel pressures.

Abstract: A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The transmission is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: A self-powered laser system for discharging high energy light beams is disclosed. The laser system includes a laser unit, a power unit, and an exhaust system. The laser unit is capable of discharging beams in multiple directions. The exhaust system directs exhaust gasses discharged from the power unit.

Abstract: Systems and methods for augmenting power output when operating a load having relatively brief periods of high energy demand and high heat generation. A system comprises a gas turbine engine including a coolant injection assembly, an electrical generator coupled to the gas turbine engine, a high-energy operating load coupled to the electrical generator, and a cooling system adapted to provide cooling to the high-energy operating load. The cooling system is coupled and adapted to provide coolant to the coolant injection assembly of the gas turbine engine. A method comprises coupling the cooling system to the coolant injection assembly at the inlet of the gas turbine engine, selectively diverting at least a portion of the coolant of the cooling system to the coolant injection assembly, and spraying the diverted coolant into air entering the gas turbine engine.

Abstract: A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.

Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: A pneumatic starter system for a turbine engine. The pneumatic starter system includes a pneumatic starter and a compressed gas storage unit. The pneumatic starter is configured to cause at least one turbine of the turbine engine to rotate. The compressed gas storage unit is configured to store oxygen rich gas and expel the oxygen rich gas to power the pneumatic starting system to cause the at least one turbine to rotate. The pneumatic starter system also includes a first exhaust path configured to direct at least a first portion of the oxygen rich gas exhausted from the pneumatic starter to a turbine combustion zone of the turbine engine to create an oxygen rich fuel mixture.

Abstract: A gas bottle assembly may be provided for a gas turbine engine system. The gas bottle system may include a gas bottle, a regulator cavity, a conductor coil, and an insulating jacket. The gas bottle may be configured to store and selectively release pressurized fluid. The regulator cavity and conductor coil may be in fluid connection with the gas bottle. The conductor coil may be disposed around at least a portion of the gas bottle. The insulating jacket may disposed around at least a portion of the gas bottle, pressure regulator, and the conductor coil. The conductor coil may be configured to maintain or decrease a temperature of the gas bottle while the insulting jacket resists heat from other portions of the engine system.

Abstract: A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The transmission is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: A gas turbine health monitoring fuel system including a fuel splitter, a first and second fuel nozzle, a first and second fuel pump, and a common drive coupled to the first and second fuel pumps. The first and second fuel pumps are downstream from the fuel splitter. The first fuel nozzle is fluidly coupled to the first fuel pump by a first fuel stream. The second fuel nozzle is fluidly coupled to the second fuel pump by a second fuel stream. The common drive is configured to drive the first and second fuel pumps at a same speed. The controller system is configured to determine a first fuel pressure in the first fuel stream, determine a second fuel pressure in the second fuel stream, and identify a difference between the first and second fuel pressures.

Abstract: A turbine vane cooling system operably coupling a cooling fluid source to a turbine vane assembly is disclosed herein. A plurality of turbine vanes having an airfoil shaped surface forming a substantially hollow body is connected to the turbine vane assembly. An inlet can be operably connected to each turbine vane to form a fluid communication path between a cooling fluid source and an interior of the hollow body of each turbine vane. At least one outlet fluidly communicating with the interior of said hollow body can be formed in the vane. A regulating member can variably block a portion of an inlet of each of the turbine vanes in response to a temperature of each turbine vane.