Patent ID: 6282897
Filing Date: 2001-09-04
Classification: B60K,B60W,F01D,F02B,F02C,Y02T,Y10S

Abstract:
In a hybrid propulsion system having an electrical storage and drive system, an improved thermal engine comprising:a. thermal energy source;b. a Brayton cycle compressor and turbine combination wherein during operation the combination has a substantially constant pressure compressor and a substantially constant pressure turbine, wherein the compressor has a drive shaft with an electric motor connected to the drive shaft and the turbine has a driven output shaft for mechanical output disconnected from the drive shaft of the compressor, wherein the compressor compresses motive gas, the thermal energy source heats the compressed motive gas from the compressor, and the turbine receives heated motive gas from the thermal energy source, the turbine having an output dependent on the amount of thermal energy transferred to the motive gas by the thermal energy source; andc. an integrator module under control of a controller, the integrator module, having a predefined program means for operating the compressor at a specific, substantially constant pressure optimized for the projected operating conditions of the propulsion system.