Antriebssystem mit Verstellbarer Kerneinlassleitschaufel

Details

Veröffentlichungs-Nr.

EP4782674

Anmeldetag

26. Januar 2026

Veröffentlichung

29. Juli 2026

Rechtsraum

EP

IPC

F02C9/54, F02C9/20, F04D29/56

Abstract

An aircraft assembly includes an open propulsor rotor (60) and a turbine engine (56) configured to drive rotation of the open propulsor rotor about an axis. The turbine engine includes a flowpath (96), a compressor section (91), a combustor section (92), a turbine section (93), an inlet vane structure (128) and an inlet vane actuation system (138). The flowpath extends longitudinally through the compressor section, the combustor section and the turbine section from a flowpath inlet (98) into the turbine engine to a flowpath exhaust (100) from the turbine engine. The inlet vane structure is located at the flowpath inlet. The inlet vane structure includes a plurality of inlet guide vanes (134) arranged in an annular array. Each of the inlet guide vanes extend across the flowpath. The inlet guide vanes include a first inlet guide vane. The inlet vane actuation system is configured to change at least a parameter of the first inlet guide vane.

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Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete