BLEEDING CORE AIR FROM A TURBINE ENGINE CORE FLOWPATH

Abstract: an assembly is provided for a turbine engine. this assembly includes an engine core configured to drive rotation of a propulsor rotor. the engine core includes a first compressor section, a second compressor section, a flowpath, a bleed port, an inner passage and an outer passage. the first compressor section and the second compressor section are arranged axially along an axis. the flowpath extends longitudinally through the first compressor section and the second compressor section. the bleed port fluidly couples the flowpath to the inner passage and the outer passage in parallel. the bleed port is located longitudinally along the flowpath between the first compressor section and the second compressor section. the inner passage is arranged radially between the flowpath and the outer passage.

Inventor(s): Michael G. McCaffrey, Mark F. Zelesky

CPC Classification: F02C7/18 (GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines ; jet-propulsion plants ; construction of compressors or fans ; generating combustion products of high pressure or high velocity ; using gas turbines in compression refrigeration plants ))

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