The present invention provides a compressor system including a plurality of compressor trains each including a gas turbine and a compression part including a compressor driven by the gas turbine, and a fluid feeding part for distributing a fluid fed from one fluid source to each of the compressors in the plurality of compressor trains. The gas turbine includes a gas turbine compressor for compressing air, a combustor for generating a combustion gas, a high-pressure turbine including a high-pressure turbine rotor mechanically coupled to a compressor rotor, and a low-pressure turbine including a low-pressure turbine rotor disposed away from the high-pressure turbine rotor. The plurality of compressor trains can be operated in parallel.

The present invention provides a compressor system including a plurality of compressor trains each including a gas turbine and a compression part including a compressor driven by the gas turbine, and a fluid feeding part for distributing a fluid fed from one fluid source to each of the compressors in the plurality of compressor trains. The gas turbine includes a gas turbine compressor for compressing air, a combustor for generating a combustion gas, a high-pressure turbine including a high-pressure turbine rotor mechanically coupled to a compressor rotor, and a low-pressure turbine including a low-pressure turbine rotor disposed away from the high-pressure turbine rotor. The plurality of compressor trains can be operated in parallel.

A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.

There is provided a compact turbine-compressor assembly 25. The turbine-compressor assembly 25 includes a turbine wheel 39 with one or more turbine blades 41 and a compressor wheel 47 that includes one or more compressor blades 49. The compressor wheel 47 is concentric with the turbine wheel 39. Furthermore, the compressor wheel 47 and the turbine wheel 39 are not located at opposite ends of a common axle with a medial portion of the axle distancing them apart, as is the case with prior art turbine-compressor assemblies that are known. In contrast, the turbine wheel 39 and the compressor wheel 47 are located adjacent to each other and in one embodiment they axially overlap each other so that one nests within the other to thereby provide a compact arrangement. The turbine-compressor assembly 25 includes a first fluid path 67 which is configured to convey fluid, which will typically be air, through the turbine blades 41. The turbine-compressor assembly 25 also includes a second fluid path 77 which is configured to convey fluid, which will typically be air, through the compressor blades. The turbine-compressor assembly 25 is arranged so that the first fluid path 67 is distinct from the second fluid path 77 and vice-versa.

An electrical power generation system including a micro-turbine alternator including a combustion chamber, at least one turbine driven by combustion gases from the combustion chamber, a first stage compressor, and a second stage compressor located aft of the first stage compressor. The first stage compressor and the second stage compressor being operably connected to the combustion chamber to provide a compressed airflow thereto. The micro-turbine alternator including one or more shafts connecting the at least one turbine to the first stage compressor and the second stage compressor such that rotation of the at least one turbine drives rotation of the first and second stage compressor. An electric generator is disposed along the one or more shafts such that electrical power is generated via rotation of the one or more shafts. The electric generator is disposed along the one or more shafts between the first and second stage compressors.

An electrical power generation system including a micro-turbine alternator including a combustion chamber, at least one turbine driven by combustion gases from the combustion chamber, a first stage compressor, and a second stage compressor located aft of the first stage compressor. The first stage compressor and the second stage compressor being operably connected to the combustion chamber to provide a compressed airflow thereto. The micro-turbine alternator including one or more shafts connecting the at least one turbine to the first stage compressor and the second stage compressor such that rotation of the at least one turbine drives rotation of the first and second stage compressor. An electric generator is disposed along the one or more shafts such that electrical power is generated via rotation of the one or more shafts. The electric generator is disposed along the one or more shafts between the first and second stage compressors.

A rotating shaft of a rotary electric machine is supported by a rotary electric machine housing. For the rotary electric machine housing, compressed air flow passages are formed. In a gas turbine engine, an air bleed port is formed in a shroud case, and compressed air that is compressed by a compressor wheel flows into the air bleed port. The compressed air that has passed through the air bleed port flows through air bleed passages formed in an engine housing and the compressed air flow passages. Then, the compressed air flows into a rotary electric machine housing.

For a rotary electric machine housing, a cooling jacket and compressed air flow passages are formed on an outer circumferential side of the cooling jacket. On an outer side wall of the rotary electric machine housing, a terminal casing is formed and electric terminal portions are accommodated in the terminal casing. Air bleed ports are formed in a shroud case of a gas turbine engine. Compressed air that is compressed by a compressor wheel flows into the air bleed ports. The compressed air that has passed through the air bleed ports flows through air bleed passages formed in an engine housing and the compressed air flow passages. Then, the compressed air reaches the terminal casing.

A gas turbine engine with a rotor comprising a turbine and compressor, mounted in a housing surrounding the rotor. The rotor rotates on one or more hydro bearings, the profiles of the outer surface of the rotor and the inner surface of the housing generating the hydro bearing(s). A combustion chamber is formed within the housing, and the combustion products of the fuel/air mixture are directed from the combustion chamber to the turbine. The housing and rotor are formed by an additive manufacturing process in a single procedure, with the rotor enclosed within the housing, and unsupported by any mechanical connections. A gas turbine respiratory ventilator system is described using a compressed oxygen flow to power the turbine which rotates the centrifugal blower for generating the air flow for respiration of the patient. The oxygen exhausted from the turbine can then be used to supplement the air flow.

The present invention is a turbofan propulsion system, based on a tangential gas turbine that is structurally a part of the propulsion system's centrifugal compressor, wherein the gas turbine's combustion chambers with nozzles are placed to rotate around a larger radius circle at a supersonic circumferential speed, and the fan blades are placed to rotate around a smaller radius circle at a subsonic circumferential speed, therefore increasing the efficiency of the propulsion system.