FIELD: engines and pumps.
SUBSTANCE: device for interaction with air or gas to work as a compressor or expander comprises housing, torque transfer shaft and rotor. Said shaft extends through the housing to run about axis and is engaged with rotor. Rotor keeps its revolution at the rim circumferential speed of about 2000-5400 feet/sec. Circular area inside said rotor and said housing makes the flow passage. Said housing includes also the discharge opening for outflow of high-energy gas or air outward from said circular area or its inflow thereto. Shaft contains material of high specific compression or expansion strength and gas flow passage to feed gas or air to rotor or to discharge then therefrom. Some parts of said shaft are wound of fibre bundle of high expansion strength material stretched to half the breaking strength. Rotor surrounds shaft part inside said housing and has gas or air passages to allow air flowing radially and to retain the flow from rotor. Rotor contains material with high expansion strength material and compressive material compressed by fibre bundles stretched to half the breaking strength. Material with high compression strength is engaged with the shaft by compression or by at least one winding of fibre bundle. Machine as a compressor comprises circular area inside the rotor and the housing to make air of gas passage to force the flow in spiral radially from rotor outside via circular area and with decrease in rate. Note here that circular area discharges airflow or gas flow radially outside the rotor. Jet or mechanical engine comprises above described machine as a compressor.
EFFECT: decreased fuel consumption, higher efficiency, lower emission of CO2, lower cost.
16 cl, 11 dwg, 8 tbl
Title | Year | Author | Number |
---|---|---|---|
DIRECT FLOW TURBORETACTIVE DETONATION ENGINE (DFTDE) | 2016 |
|
RU2638239C1 |
VORTEX GAS COMPRESSOR DEVICE FOR COMBINED AIR-JET ENGINE | 2019 |
|
RU2766496C2 |
HYBRID JET ENGINE | 2005 |
|
RU2272926C1 |
ROTARY BIROTATE GAS TURBINE ENGINE | 2019 |
|
RU2702317C1 |
METHOD OF PRODUCING MECHANICAL ENERGY IN TURBINE, TURBINE AND SEGNER'S WHEEL FOR IMPLEMENTING THE METHOD | 2004 |
|
RU2280168C1 |
ENGINE OF HYPERSONIC AIRCRAFT | 2015 |
|
RU2594091C1 |
TURBORAM AIR-JET ENGINE | 2015 |
|
RU2613755C1 |
PROPULSION ENGINE OF SUPERSONIC AIRCRAFT | 2015 |
|
RU2594828C1 |
ENGINE OF HYPERSONIC AIRCRAFT | 2015 |
|
RU2591361C1 |
ENGINE OF HYPERSONIC AIRCRAFT | 2015 |
|
RU2593573C1 |
Authors
Dates
2014-05-20—Published
2009-03-25—Filed