Patent ID: 6134880
Filing Date: 2000-10-24
Classification: F02C,F02K,F05D,F28D,F28F,Y02T

Abstract:
A turbine engine that produces thrust, comprising:a. a low pressure compressor:b. a core air passage through which core air flows;c. a high pressure compressor connected to said core air passage, said high pressure compressor having an outlet;d. a bypass air passage through which bypass air flows, said bypass air having less thermal energy than said core air;e. an intercooler connected to said core air passage and extending into said bypass air passage, wherein said intercooler is constructed to transport more than a mass bleed flow amount of said core air comprising at least twelve percent, by mass, of said core air from said core air passage through said bypass air passage, where thermal energy from said core air is extracted, and back to said core air passage, upstream of said outlet, in a single thermodynamic cycle; andf. wherein said bypass air passage is constructed such that said extracted thermal energy contributes to the thrust of the turbine engine.