Triebwerksanordnung für ein Flugzeug

Details

Veröffentlichungs-Nr.

EP4775811

Anmeldetag

12. Januar 2026

Veröffentlichung

15. Juli 2026

Rechtsraum

EP

Abstract

A powerplant assembly (24) for an aircraft (20) includes a first driven rotor, a second driven rotor, a gas turbine engine (28), and an auxiliary engine (30A). The gas turbine engine (28) includes a compressor section (36), a combustor section (38), and a turbine section (40) forming a core gas flow path (88). The gas turbine engine (28) further includes a rotational assembly (46) including a bladed turbine rotor (56) and a shaft (52). The shaft (52) couples the bladed turbine rotor (56) with the first driven rotor. The auxiliary engine (30A) is mechanically independent of the gas turbine engine (28). The auxiliary engine (30A) includes an engine output shaft (66), an air inlet (68), and an exhaust outlet (70). The engine output shaft (66) is coupled with the second driven rotor. The auxiliary engine (30A) further forms the core gas flow path (88) with the air inlet (68) connected in fluid communication with the compressor section (36) and the exhaust outlet (70) connected in fluid communication with the combustor section (38).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada