Bombardier Inc.

Short Brothers Plc

Stephen Colavincenzo

Alexis Caron-L'Ecuyer

Andre Brodeur

Thineshan Kathirchelvan

Mohammad Tabesh

Alexis Caron L'Ecuyer

Stephane Brunet

Mirel Bogdan

Vincent Pointel

Dragan Jovicic

Eric Hansen

Manuel Etchessahar

Mark Huising

Robby Lapointe

Alexis Caron-L'ECUYER

Alexis Caron L Ecuyer

Alexis Caron L' Ecuyer

Alexis Caron-L'ecuyer

Alexis Caron-L Ecuyer

Systems and method for synchrophasing aircraft engines are disclosed. One method comprises receiving data indicative of a sensed vibration level associated with a first aircraft engine and a second aircraft engine operating at a substantially same operating speed and commanding one or more momentary changes in operating speed of the second aircraft engine until the sensed vibration level substantially reaches a target vibration level. The momentary changes in operating speed of the second aircraft engine is commanded irrespective of phase information associated with imbalances of the first and second aircraft engines.

System and method for synchrophasing aircraft engines

An insert for an air intake of a suction duct, the insert including an inner portion configured to extend within the suction duct, a mating portion configured for sealingly engaging the air intake, and an outer portion configured for extending outside of the suction duct. The inner portion includes a conduit having a central axis extending along an inlet direction at the inlet end and along an outlet direction at the outlet end, the inlet and outlet directions being non-parallel. The outlet end has a smaller cross-sectional area than that of the suction duct. The insert includes an inlet in fluid communication with the inlet end of the conduit. The outer portion includes a curved lip surrounding at least part of an inlet opening of the inlet, the lip configured to direct a flow into the inlet opening and toward the inlet end of the conduit.

Insert for suction duct

A noise attenuating device for reducing acoustic resonance in a cavity of an aircraft with an opening in a skin of the aircraft defining a first surface area and an opening peripheral edge includes a connection mechanism for securing the noise attenuating device in proximity to the opening in the skin of the aircraft and an exterior surface. The exterior surface defines a second surface area that is less than the first surface area of the opening and a device peripheral edge, which has a first section having an edge profile complimentary to at least a portion of the opening peripheral edge and a second section having an indented edge profile in relation to the first section such that when the noise attenuating device is secured within the opening, at least one gap is formed between the device peripheral edge and the opening peripheral edge.

Noise attenuating device to reduce noise generated by an opening in a skin of an aircraft

Methods and related apparatus for improving synchronization of two or more engines on an aircraft are disclosed. Such method may be used where each engine comprises a first spool and a second spool, and, where a rotational speed of a first spool of a first engine has been substantially synchronized with a rotational speed of a first spool of a second engine. An exemplary method comprises receiving a value of a sensed parameter useful in controlling the first engine; adding a bias to the value; and using the biased value for controlling the first engine to cause a change in rotational speed of the second spool of the first engine in relation to the rotational speed of the first spool of the first engine.

Synchronization of aircraft engines

A wing assembly includes a swept wing body, a leading edge of the wing body extending outward and rearward from a wing root to a wing edge; a first slat selectively movably connected to the wing body; and a second slat selectively movably connected to the wing body, the second slat being disposed outboard of the first slat, a flexible sealing member disposed and connected between the first slat and the second slat; at least a portion of the first slat, at least a portion of the second slat, and at least a portion of the flexible sealing member defining a slat gap therebetween, at least a majority of the slat gap being substantially parallel to a predetermined local airflow direction. An aircraft is also disclosed which includes a fuselage; and two oppositely disposed wing assemblies connected to the fuselage.

Wing assembly with slats and aircraft

Systems and methods for performing noise reduction in a vehicle comprising a noise reduction system and a plurality of zones are herein provided. A noise reduction criterion for the vehicle is obtained. A first one of the plurality of zones for which noise reduction is to be performed is determined, based on the noise reduction criterion. The noise-reduction system is controlled to perform noise reduction in the first zone, wherein performing noise reduction in the first zone causes the noise reduction system to effect a resultant adjustment in noise level in at least a second one of the plurality of zones.

Noise-reduction in aircraft

Growing community of inventors

Toronto, Canada

Stephen Colavincenzo