REGELVERFAHREN UND ELEKTRONISCHER BRENNSTOFFREGLER FUER EINEN MIT TURBINENTRIEBWERK(EN) VERSEHENEN HUBSCHRAUBER

摘要

An electronic fuel control system 10 controls fuel supplied to a gas turbine engine 14 (via line 12) to maintain torque Q, temperature T5 and speed N1 within one of three sets of limits 44, 46, 48. The engine(s) 14 (14') drives a helicopter rotor 30 via a gear box 28 and clutch 26. "Blow-away" limits (46) for temperature (T5), speed (N1), and torque (Q) are automatically implemented: -if the rotor speed (NR) droops to a specific value; or -if the rotor speed (NR) droops to a specific amount below a selected reference speed (NRREF); or -if the rotor speed is decaying (NRDOT) at an excessive rate for a specified time and the rotor speed (NR) equals the free turbine speed (NF) of the engine. Apparatus and method are disclosed.