Integrated bypass turbojet engines for aircraft and other vehicles
OwnerMarius A. Paulinventor
Life of this patent
Estimating the term…
Abstract
Turbojet engines and aircraft configurations for advantageous use of the turbojet engines; the turbojet engines utilizing ram air turbine units that centrifugally compress air isothermally for use in various combustion configurations designed for stoichiometric combustion, wherein a stream of by-pass ram air jets is mixed with combustion gas jets for discharge in a common discharge nozzle.
Claims26
A turbojet engine comprising a turbojet structure with an air intake, a rotor disk unit having a fan unit with centrifugal compressor cells and turbine blades and a peripheral combustion chamber with at least one fuel injector and nozzles that discharge combustion gases to turbine blades of the rotor disk unit wherein bypass air flows through the fan unit cooling air flow compressed in the centrifugal compressor cells that is ejected into the combustion chamber wherein combustion gases from the turbine blades mix with the bypass air through the fan unit in a common ejection nozzle.
A turbojet engine comprising a turbojet structure with an air intake, a common combustion gas and air ejection nozzle, a rotor disk unit having an air fan with internal compressor passages and radial discharge nozzles, a peripheral combustion chamber having a perforated air plenum wherein the air fan has side apertures proximate the radial discharge nozzles that supply compressed air from the compressor passages to the perforated air plenum, fuel injectors that inject fuel into the peripheral combustion chamber wherein air flow into the air intake divides to bypass air through the air fans and compressed air in the compressor passages that is discharged into the combustion chamber through the radial discharge nozzles and through the apertures and perforated air plenum, wherein the combustion chamber has a variable geometry discharge nozzle for discharging combustion gases into the bypass air for ejection with the bypass air from the common ejection nozzle.
A turbojet engine in a turbojet comprising a turbojet structure with an air intake, a common air and combustion gas injection nozzle, counter rotating air fan rotors each rotor having an air fan, an axial compressor with counter rotating compressor blades driven by the counter rotating air fan rotors, a combustion chamber with fuel injection, wherein compressed air from the compressor mixes with fuel to generate combustion gases, and a combustion gas ejection nozzle, wherein the turbojet structure has a bypass air flow from the air intake through the air fans of the air fan rotors and a compressed air flow through the compressor, the combustion gases from the combustion gas ejection nozzle mixing with the bypass air flow for ejection from the common air and combustion gas ejection nozzle.
A turbojet engine comprising a body with an air intake and a common combustion gas and air ejection nozzle, and having therebetween, front struts at the air intake;
- a front rotor unit with cooperating variable geometry air guides located proximate the front rotor unit, the rotor unit including a ram air turbine with hollow blades in the form a centrifugal compressor;
- hollow struts;
- an axial compressor with counter rotating stages, wherein centrifugally compressed air from the centrifugal compressor is supplied to the hollow struts and through the struts to the axial compressor;
- a centrifugal compressor and by-pass fan with hollowed gas turbine blades;
- and a concentric combustion chamber, wherein the gas turbine blades have ends that discharge compressed air from the axial compressor through the hollowed gas turbine blades to the combustion chamber and the combustion chamber diverts combustion gases back to the gas turbine blades before discharge to the common combustion gas and air ejection nozzle, wherein the combustion chamber includes a variable geometry nozzle for direct discharge of combustion gases to the common combustion gas and air ejection nozzle for rocket propulsion.
A turbojet engine comprising a body with an air intake and a common combustion gas and air ejection nozzle, and having therebetween, front struts at the air intake;
- a front rotor unit with cooperating variable geometry air guides located proximate the front rotor unit, the rotor unit including a ram air turbine with hollow blades in the form a centrifugal compressor;
- hollow struts;
- an axial compressor with counter rotating stages, wherein centrifugally compressed air from the centrifugal compressor is supplied to the hollow struts and through the struts to the axial compressor;
- a ram-air turbine with hollowed blades in the form of a second centrifugal compressor;
- second hollow struts;
- and a central combustion chamber, wherein compressed air from the axial compressor is supplied to the second centrifugal compressor and through the hollow-struts to the central combustion chamber, the combustion chamber having a variable discharge nozzle for discharge of a rocket gas jet to the common combustion gas and air ejection nozzle.
Dependencies are inferred from the claim text.