System und Verfahren zur Kühlung einer Turbinenkomponente eines Turbinenmotors

Details

Veröffentlichungs-Nr.

EP4477860

Aktenzeichen

EP24182417

Anmeldetag

14. Juni 2024

Veröffentlichung

18. Dezember 2024

Rechtsraum

EP

IPC

F02C6/08F02C7/14F02C7/18F02C7/224F02C7/12F02C3/22

Abstract

An aircraft propulsion system (18) and method is provided. The system (18) includes compressor, combustor, and turbine sections (80, 84, 22), a fuel source (64), a heat exchanger (66), a compressor bleed air passage (86), and a cooling air passage (88). The fuel source (64) is configured to contain a non-hydrocarbon fuel. The heat exchanger (66) has separate air and fuel passages (68). The air passage (68) permits passage of the compressed air therethrough. The fuel passage (74) is configured to permit a passage of the non-hydrocarbon fuel therethrough. The compressor bleed air passage (86) is configured to receive compressed air bleed off a core flow path (82) upstream of the combustor section (84). The compressor bleed air passage (86) is in fluid communication with the air passage air inlet (70). The cooling air passage (88) is configured to receive compressed air exiting the air passage (68) air outlet (72) and configured to direct the compressed bleed air to the vane stage or rotor stage of the turbine section (22), or both.

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada

Fachgebiete