Lycoming Engines, a Division of Avco Corporation

Forrest Ross Lysinger

James Paul Morris

Scott Matas

Ron Behar

Ken Kremer

William Gundrum

Joseph Eric Parlow

Jason Rogers

A crankshaft detection system includes a pickup element mounted to an end of a crankshaft and disposed within a rear portion of the aircraft engine's crankcase. The crankshaft detection system also includes pickup element sensor secured to a mounting location formed in the rear portion of the aircraft engine's crankcase and disposed in proximity to the pickup element. As the crankshaft rotates the pickup element relative to the pickup element sensor, the pickup element causes the pickup element sensor to generate a signal indicative of the angular velocity and rotational position of the crankshaft. In order to optimize engine performance, in response to the signal, the controller controls a spark event associated with each the cylinder assembly of the engine such that ignition of the fuel and air mixture occurs within each cylinder assembly at a time prior to each piston of each cylinder assembly reaching a top dead center position.

Aircraft engine crankshaft position and angular velocity detection apparatus

An aircraft engine power distribution system for an aircraft engine controller, such as a FADEC, is provided where the power source is independent from the conventional airframe power system, without the need for a back-up battery. The aircraft engine power distribution system includes a magnetic generator operated by an aircraft engine. The aircraft engine power distribution system also includes a power distributor that rectifies the generator output and provides the rectified power to the engine controller as its primary source of power. In this configuration, as long as the aircraft engine is able to operate the magnetic generator, the engine controller receives power. Accordingly, the engine controller operates regardless of the operational status of the airframe power system.

Power source for aircraft engine controller systems

A fuel pump includes a bearing element disposed in proximity to an impeller. The bearing element is configured to form a fuel seal with the impeller and to drain fuel leaked from the pump chamber back into the pump chamber. The bearing element minimizes leakage of fuel from the pump chamber into an engine coupled to the impeller. The fuel pump also includes redundant lip seals configured to provide redundant sealing relative to a shaft of the impeller within the fuel pump in order to minimize engine oil from entering the pump chamber and to minimize fuel from entering the engine. Integration of both the bearing element and the redundant lip seals as part of the fuel pump results in the fuel pump having a relatively compact size.

Fuel pump for engine

A fuel injector mounting assembly is configured to limit or constrain movement of a fuel injector relative to a corresponding cylinder assembly. For example, the fuel injector mounting assembly includes a base that is secured to a cylinder assembly's housing and a fuel conduit. The fuel conduit includes a first fuel conduit portion which operates in conjunction with a cylinder assembly's fuel manifold to capture a fuel injector between the fuel injector mounting assembly and the cylinder assembly's fuel manifold. The fuel conduit also includes a second fuel conduit portion which is secured to a compliant fuel line. With such a configuration of the fuel injector mounting assembly, both ends of the fuel injector are secured to the cylinder assembly to minimize any relative motion in the fuel injector's seals relative to either the cylinder assembly's fuel manifold or to the compliant fuel line.

Fuel injector mounting assembly for an aircraft engine fuel delivery system

In one embodiment, a sensing apparatus senses rotation of an engine component (e.g., a crank shaft) relative to an engine body. The sensing apparatus includes a sensor, and a bracket configured to position the sensor in a fixed location relative to the engine body. The starter ring has (i) a support portion configured to rotate in tandem with the engine component, (ii) a starter interface mounted to the support portion, the starter interface being configured to receive drive from a starter motor during operation of the starter motor, and (iii) a trigger portion mounted to the support portion. The trigger portion is configured to provide a series of indicators during rotation of the engine component. The series of indicators (e.g., a series of magnetic field perturbations during rotation of the engine component) is readable by the sensor thus enabling identification of component positioning and speed.

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Harrisburg, PA, United States of America

Forrest Ross Lysinger