초록 ▼

The invention provides a micro-gas turbine engine and associated microcomponentry. The engine components, including, e.g., a compressor, a diffuser having diffuser vanes, a combustion chamber, turbine guide vanes, and a turbine are each manufactured by, e.g., microfabrication techniques, of a struct

The invention provides a micro-gas turbine engine and associated microcomponentry. The engine components, including, e.g., a compressor, a diffuser having diffuser vanes, a combustion chamber, turbine guide vanes, and a turbine are each manufactured by, e.g., microfabrication techniques, of a structural material common to all of the elements, e.g., a microelectronic material such as silicon or silicon carbide. Vapor deposition techniques, as well as bulk wafer etching techniques, can be employed to produce the engine. The engine includes a rotor having a shaft with a substantially untapered compressor disk on a first end, defining a centrifugal compressor, and a substantially untapered turbine disk on the opposite end, defining a radial inflow turbine. The rotor is preferably formed of a material characterized by a strength-to-density ratio that enables a rotor speed of at least about 500,000 rotations per minute. An annular, axial-flow combustion chamber is provided that is located axially between the compressor and turbine disks and that has a ratio of annular height to axial length of at least about 0.5. The micro-gas turbine engine can be configured with an integral microgenerator as a source of electrical power, and can be employed for a wide range of power, propulsion, and thermodynamic cycle applications.

대표청구항 ▼

[ We claim:] [1.] A gas turbine engine comprising:a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air;a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure;a combustor comprising a combu

[ We claim:] [1.] A gas turbine engine comprising:a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air;a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure;a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel;a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor;a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; andbearing surfaces of the rotatable elements;wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements and the bearing surfaces each substantially comprise a structural material common to all of the elements.