There is provided a system and a method for operating a multi-engine rotorcraft. When the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of a power level of the at least one second engine is increased and at least one variable geometry mechanism of the at least one second engine is moved to shed any ice accumulation on the at least one second engine.

A system for automated management of in-flight restarting of engines of an aircraft includes controllers, each engine of the aircraft being managed by one of the controllers. A controller that detects an engine that has stopped: cuts off the energy supply of the engine and performs a windmill engine start. If at least one other engine has stopped, prioritization of engine restarting includes: collecting information concerning a state of health of each engine; determining from the information collected information representing a probability of restarting each stopped engine; determining a sequential order of restarting the stopped engines as a function of information representing the probability of restarting each stopped engine. Each stopped engine continues to be windmill started until selection of the engine in question in the sequential order of restarting the stopped engines. Thus, the operational status of the aircraft is improved as quickly as possible.

Examples described herein provide a computer-implemented method that includes monitoring a hybrid electric turbine engine of an aircraft, the hybrid electric turbine engine including a first electric machine associated with a high speed spool and a second electric machine associated with a low speed spool. The method further includes receiving an indication of a failed electric machine, the failed electric machine being an electric machine on another hybrid electric turbine engine of the aircraft. The method further includes, responsive to detecting the failed electric machine, distributing power from one or more of the first electric machine or the second electric machine to a spool associated with the failed electric machine.

An evaluation of the oil level of an aircraft engine tank from doses of oil delivered from another tank by a pump can be checked by comparing the evaluation of the volume provided by a sensor associated with the engine tank with an estimation of the volume extracted from the aircraft rank, either by another level sensor associated with this tank, or directly from the control of the pump. This comparison is made by a module capable of notifying staff of the need to check or maintain the device, and in particular to check if the sensor is operating correctly. Application to aeronautics, in particular to devices wherein a single aircraft tank supplies all the engine tanks.

A motor support comprises two coaxial rings (20; 22) and an element for limiting the tilting of the inner ring relative to the outer ring. The limiting element comprises a finger (26) projecting from a first of the rings (20; 22) and housed in a receptacle (28) in the second of the rings (20; 22). An axial end-stop in the receptacle (28) limits the movement of the finger (26) in the receptacle (28) in the direction of the common axis (A) of the two rings (20; 22). The axial end-stop comprises a spigot (32) extending from a base (38) of a peg (36) through a wall (45) of the receptacle. The base (38) of the peg (36) is fixed to the second ring. The spigot (32) has a projection (44) capable of abutting against the wall (45) of the receptacle (28).

A pump assembly for use within a high pressure pumping system includes housing, a head and a base. The housing contains at least one centrifugal pump stage. The head and base are attached to the housing with corresponding internal threaded connections. The head and base are further retained to the housing with corresponding external flanged connections. The external flanged connections provide redundant connections that reduce the risk of separation between the housing and the head and base.

A combustor includes a liner having an outlet end to pass combustion gas and a liner flange protruding outward from the outlet end; a transition piece to discharge combustion gas from the liner to a turbine, the transition piece having an inlet end for coupling to the outlet end of the liner and a transition piece flange protruding outward from the inlet end to face the liner flange; and a first elastic support installed on the liner flange to protrude toward the transition piece flange. A force applied from the transition piece elastically deforms an elastic arch of the first elastic support, which includes a movable support that is spaced apart from the liner flange if the force applied from the transition piece does not primarily deform the elastic arch. An auxiliary elastic support installed inside the first elastic support elastically deforms if the force secondarily deforms the elastic arch.

A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.

A redundant oil and fuel pumping system for use with a gas turbine engine. The pumping system includes a plurality of power sources, a fuel system and an oil system. The fuel system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power sources. The oil system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power sources.

A redundant oil and fuel pumping system for use with a gas turbine engine. The pumping system includes a plurality of power supplies, a fuel system and an oil system. The fuel system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power supplies. The oil system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power supplies.