18211100. SYSTEM AND METHOD FOR TURBINE ENGINE TURBINE COMPONENT COOLING (PRATT & WHITNEY CANADA CORP.)
Contents
SYSTEM AND METHOD FOR TURBINE ENGINE TURBINE COMPONENT COOLING
Organization Name
Inventor(s)
Scott Smith of St-Lambert (CA)
Russell Stratton of Toronto (CA)
SYSTEM AND METHOD FOR TURBINE ENGINE TURBINE COMPONENT COOLING
This abstract first appeared for US patent application 18211100 titled 'SYSTEM AND METHOD FOR TURBINE ENGINE TURBINE COMPONENT COOLING
Original Abstract Submitted
An aircraft propulsion system and method is provided. The system includes compressor, combustor, and turbine sections, a fuel source, a heat exchanger, a compressor bleed air passage, and a cooling air passage. The fuel source is configured to contain a non-hydrocarbon fuel. The heat exchanger has separate air and fuel passages. The air passage permits passage of the compressed air therethrough. The fuel passage is configured to permit a passage of the non-hydrocarbon fuel therethrough. The compressor bleed air passage is configured to receive compressed air bleed off a core flow path upstream of the combustor section. The compressor bleed air passage is in fluid communication with the air passage air inlet. The cooling air passage is configured to receive compressed air exiting the air passage air outlet and configured to direct the compressed bleed air to the vane stage or rotor stage of the turbine section, or both.
