System and method for propeller response enhancement during transition from ground to flight configuration for a turbopropeller engine
US11738855B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 22, 2019 |
| Grant date | Aug 29, 2023 |
| Priority date | — |
| Expiry date | Mar 22, 2039 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D31/06
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An electronic control system for a turbopropeller engine having a gas turbine and a propeller assembly coupled to the gas turbine is provided. The control system implements a propeller control unit to control propeller operation using an actuation assembly designed to adjust a pitch angle of propeller blades. The control unit engages a mechanical lock determining a minimum flight value for the pitch angle during a flight operating mode, and disengages the mechanical lock and controls the pitch angle below the minimum flight value, up to a minimum ground value lower than the minimum flight value, during a ground operating mode. The propeller control unit, during a transition from the ground operating mode to the flight operating mode, engages the mechanical lock. The control unit anticipates the increase of the pitch angle before the mechanical lock engagement when transitioning from the ground operating mode to the flight operating mode.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.