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Single lever control in twin turbopropeller aircraft

a twin-turbopropeller and single-lever technology, applied in the direction of aircraft power plants, rotorcraft, aircraft components, etc., can solve the problem of additional pilot work load

Active Publication Date: 2018-08-23
PRATT & WHITNEY CANADA CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This patent describes a system and method for controlling the operation of propellers on an aircraft. The system includes two engines and two propellers, each associated with its own unified control lever. The system also includes a control system for each engine and propeller, which are responsible for synchronizing the operation of the propellers. The technical effect of this patent is improved control and synchronization of two propellers on an aircraft, allowing for better performance and efficiency.

Problems solved by technology

However, the presence of multiple levers for each principal components of each powerplant can lead to additional work load for the pilot, especially in cases where the aircraft has multiple engines, such as twin turbopropeller aircraft.

Method used

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  • Single lever control in twin turbopropeller aircraft
  • Single lever control in twin turbopropeller aircraft
  • Single lever control in twin turbopropeller aircraft

Examples

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Embodiment Construction

[0016]With reference to FIG. 1, there is illustrated a turbopropeller powerplant 100 for an aircraft of a type preferably provided for use in subsonic flight, generally comprising an engine 110 and a propeller 120. The propeller 120 converts rotary motion from a shaft of the engine 110 to provide propulsive force for the aircraft, also known as thrust. The powerplant 100 of FIG. 1 is a turboprop, but the engine 110 could also be any other type of engine mated to a propeller 120, such as a piston engine, and the like.

[0017]Operation of the engine 110 and of the propeller 120 can be regulated by a pilot or other operator by way of various powerplant controls. Traditionally, a turbopropeller driven aircraft is provided with a throttle lever (also referred to as a power lever), which is used to regulate the output power of the engine 110, and a condition lever, which is used to regulate the propeller rotational speed and blade pitch angle thereby modulating thrust produced by the propel...

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PUM

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Abstract

Herein provided are methods and systems for controlling operation a first propeller of an aircraft, the first propeller associated with a first engine, the aircraft further comprising a second propeller associated with a second engine. A first requested engine power for the first engine is obtained. A second requested engine power for the second engine is obtained. The first propeller is synchronized with the second propeller by setting a first propeller command for the first propeller based on the first and second requested engine power, and the first propeller command is sent for the first propeller.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS[0001]The present application claims the benefit of U.S. Provisional Patent Application No. 62 / 462,090 filed on Feb. 22, 2017, the contents of which are hereby incorporated by reference in their entirety.TECHNICAL FIELD[0002]The present disclosure relates generally to engine control, and, more particularly, to engine and propeller control in aircraft.BACKGROUND OF THE ART[0003]A propeller-driven aircraft powerplant consists of two principal and distinct components: an engine and a propeller. An engine control system is used to modulate the power output of the engine, for example by controlling fuel flow to the engine. Similarly, a propeller control system is used to modulate the thrust produced by the propeller, for example by changing a propeller rotational speed and / or a propeller blade pitch. In traditional propeller driven aircraft, each of the engine control system and the propeller control system is operated by a pilot or other operator u...

Claims

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Application Information

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IPC IPC(8): B64C11/50B64D31/00
CPCB64D31/00B64C11/50B64C27/08B64C27/12B64D31/06B64C11/305B64D31/12
Inventor LISIO, CARMINE
Owner PRATT & WHITNEY CANADA CORP
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