A gas turbine engine comprises at least a power output turbine unit (POT), which is rotatably arranged inside an outer housing unit, and a compressor-turbine unit (CTU), which is rotatably arranged inside the POT, and the CTU, POT and outer housing unit are arranged about a common axis of rotation (CL). The POT and the CTU are arranged in such close proximity (d) that a dynamic friction coupling is generated between the POT and the CTU.

A gas turbine engine comprises at least a power output turbine unit (POT), which is rotatably arranged inside an outer housing unit, and a compressor-turbine unit (CTU), which is rotatably arranged inside the POT, and the CTU, POT and outer housing unit are arranged about a common axis of rotation (CL). The POT and the CTU are arranged in such close proximity (d) that a dynamic friction coupling is generated between the POT and the CTU.

A gas turbine engine (1) has a centrifugal compressor (4) and a radial turbine (14) mounted to a turbine shaft (2) for rotation with the shaft about the shaft axis Z. A number of combustion chambers (10) in the air/gas flow path between the compressor and the turbine are spaced circumferentially about the shaft axis. The combustion chambers (10) are elongate in the direction of air/gas flow and the longitudinal axis of each combustion chamber is skewed transversely relative to the axis Z of the turbine shaft. The combustion chambers (10) may be curved longitudinally about the shaft axis and may be aligned concentric about the axis. The engine may have a recuperator (8) radially outboard the compressor, the recuperator having radially directed flow passages through which air from the compressor is directed.

A gas turbine engine (1) has a centrifugal compressor (4) and a radial turbine (14) mounted to a turbine shaft (2) for rotation with the shaft about the shaft axis Z. A number of combustion chambers (10) in the air/gas flow path between the compressor and the turbine are spaced circumferentially about the shaft axis. The combustion chambers (10) are elongate in the direction of air/gas flow and the longitudinal axis of each combustion chamber is skewed transversely relative to the axis Z of the turbine shaft. The combustion chambers (10) may be curved longitudinally about the shaft axis and may be aligned concentric about the axis. The engine may have a recuperator (8) radially outboard the compressor, the recuperator having radially directed flow passages through which air from the compressor is directed.

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.

The present disclosure is directed to a system for bleeding air from a compressed gas path of a gas turbine engine. The system includes an impeller positioned at a downstream end of a compressor in the gas turbine engine. The impeller includes an impeller hub, an impeller arm coupled to the impeller hub, and a plurality of circumferentially spaced apart impeller vanes extending radially outwardly from the impeller arm. The impeller arm defines an impeller arm aperture extending therethrough. A vortex spoiler is positioned radially inwardly from the impeller arm and defines a vortex spoiler passage extending radially therethrough. Bleed air flows from the compressed gas path radially inwardly through both the impeller arm aperture and the vortex spoiler passage.

A gas turbine engine includes a rotatable first shaft, a first disk connected to the first shaft, a second disk connected to the first shaft, a combustor radially outward from the first disk and the second disk, and a heat exchanger connected to the combustor aft of the second disk. The first disk includes a row of low pressure compressor blades and a row of high pressure turbine blades connected to a radially outer end of the row of low pressure compressor blades. The second disk includes a row of high pressure compressor blades and a row of low pressure turbine blades connected to a radially outer end of the row of high pressure compressor blades.

A vehicle propulsion system comprises at least two motors. Combustion occurs upstream of a first motor, and a second motor is downstream of said first motor. The first motor is a turbine that drives a primary propulsion element to effect propulsion and a compressor to effect compression. The second motor is an expansion device whose incoming gases arrive from said first motor. The first motor and the second motor intercommunicate energy via electrical, electromagnetic, and/or mechanical means. Pressurized gases that result from said compression, combustion, or both are rendered or wastegated for auxiliary usage such as aerial thrust, vertical takeoff and/or vertical landing, near-vertical takeoff and/or near-vertical landing, pneumatic storage for hybrid drive, pneumatic lift and/or drive for towing and/or raising another vehicle, aerial vehicle steering, aerial vehicle pitch stabilization or manipulation, aerial vehicle roll stabilization or manipulation, and/or aerial vehicle yaw stabilization or manipulation.

A vehicle propulsion system comprises at least two motors. Combustion occurs upstream of a first motor, and a second motor is downstream of said first motor. The first motor is a turbine that drives a primary propulsion element to effect propulsion and a compressor to effect compression. The second motor is an expansion device whose incoming gases arrive from said first motor. The first motor and the second motor intercommunicate energy via electrical, electromagnetic, and/or mechanical means. Pressurized gases that result from said compression, combustion, or both are rendered or wastegated for auxiliary usage such as aerial thrust, vertical takeoff and/or vertical landing, near-vertical takeoff and/or near-vertical landing, pneumatic storage for hybrid drive, pneumatic lift and/or drive for towing and/or raising another vehicle, aerial vehicle steering, aerial vehicle pitch stabilization or manipulation, aerial vehicle roll stabilization or manipulation, and/or aerial vehicle yaw stabilization or manipulation.