The invention relates to a method for starting a turbine engine in cold weather, including a starting system intended for rotating a drive shaft of the turbine engine, the method comprising the following steps: —a pre-starting step in which a first starting signal is generated to control the drive shaft in a first direction of rotation about a longitudinal axis (X) and in a second opposite direction of rotation in an alternating manner; and —a starting step in which a second starting signal is transmitted to the starting system in order for the latter to drive the drive shaft of the turbine engine in a normal direction of rotation and in which the drive shaft is rotated until a rotation speed that causes the turbine engine to start.

A method of starting a turbine engine utilizing multiple components. The turbine engine may comprise a gearbox coupled to a spool of the turbine engine via an output shaft. A first starter may be coupled to the gearbox via an input shaft. A first accessory may be coupled to the gearbox via another input shaft. The rotation of the output shaft of the gearbox may be coupled to the rotation of the spool. The rotation of each of the first starter and first accessory may be coupled to the rotation of the respective input shaft of the gearbox. The method may comprise applying a first application of power to one of the first starter and the first accessory and applying a second application of power to the other of the first accessory and the first starter.

A method of starting a turbine engine utilizing multiple components. The turbine engine may comprise a gearbox coupled to a spool of the turbine engine via an output shaft. A first starter may be coupled to the gearbox via an input shaft. A first accessory may be coupled to the gearbox via another input shaft. The rotation of the output shaft of the gearbox may be coupled to the rotation of the spool. The rotation of each of the first starter and first accessory may be coupled to the rotation of the respective input shaft of the gearbox. The method may comprise applying a first application of power to one of the first starter and the first accessory and applying a second application of power to the other of the first accessory and the first starter.

A geared turbofan engine with at least one compression stage and at least one turbine stage on a high speed shaft, the high speed shaft coupled through a speed reduction gear box to a low speed shaft with a fan and a starter/generator. The low speed shaft is collinear with the high speed shaft but does not rotate within the high speed shaft. The speed reduction gear box is positioned between and mechanically couples the high speed shaft and the low speed shaft, which allows the fan and the integrated starter/generator on the low speed shaft to operate at a lower speed than the high speed shaft.

A geared turbofan engine with at least one compression stage and at least one turbine stage on a high speed shaft, the high speed shaft coupled through a speed reduction gear box to a low speed shaft with a fan and a starter/generator. The low speed shaft is collinear with the high speed shaft but does not rotate within the high speed shaft. The speed reduction gear box is positioned between and mechanically couples the high speed shaft and the low speed shaft, which allows the fan and the integrated starter/generator on the low speed shaft to operate at a lower speed than the high speed shaft.

A turboprop or turboshaft gas turbine engine includes a low pressure turbine drivingly engaged to an output shaft for driving a rotatable load. A low pressure compressor is de-coupled from the low pressure turbine, the low pressure compressor and turbine rotating independently from one another. A high pressure compressor is disposed downstream from the low pressure compressor and is in fluid communication therewith to receive pressurized air therefrom. A high pressure turbine is disposed downstream from the high pressure compressor and is drivingly engaged thereto via a high pressure shaft. The high pressure turbine is disposed upstream from the low pressure turbine and is in fluid communication therewith. An electric motor receives power from a power source, is drivingly engaged to the low pressure compressor, and is operable to drive the low pressure compressor independently from the low pressure turbine, the high pressure compressor and the high pressure turbine.

An apparatus and method relating to a generator comprising a housing defining an interior and fluidly separating the interior from surrounding ambient air, at least one of a rotor or stator located within the housing, a cooling circuit passing through at least a portion of the housing to cool the interior and recirculating a coolant having a density greater than the ambient air, and a jet pump having a motive fluid conduit fluidly coupled to the cooling circuit, a transport fluid circuit fluidly coupled to the ambient air.

A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: increasing an angular velocity of a low pressure compressor; determining if an exit pressure of the low pressure compressor is equal to or greater than a first threshold pressure; in response to determining that the exit pressure of the low pressure compressor is equal to or greater than the first threshold pressure, controlling rotation of the low pressure compressor using a first electrical machine and controlling rotation of a high pressure compressor using a second electrical machine, to increase angular velocity of the high pressure compressor; determining if an exit pressure of the high pressure compressor is equal to or greater than a second threshold pressure.

A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: controlling ignition within a combustion chamber of the gas turbine engine; controlling rotation of a low pressure compressor using a first electrical machine, and controlling rotation of a high pressure compressor using a second electrical machine, the combustion chamber downstream of the low pressure compressor and high pressure compressor; determining if an exit pressure of the high pressure compressor is equal to or greater than a self-sustaining threshold pressure; and in response to determining that the exit pressure of the high pressure compressor is equal to or greater than the self-sustaining threshold pressure, ceasing controlling rotation of the low pressure compressor using the first electrical machine, and/or the high pressure compressor using a second electrical machine.

In one aspect, the present disclosure is directed to a gas turbine starting system that includes a shaft coupling a compressor and a turbine. An annular housing extends circumferentially around the shaft such that the annular housing defines a compartment. A flange extends radially outward from the annular housing for mounting the annular housing to a stationary wall. A starter is positioned in the compartment. A collar rotatably couples to the annular housing and selectively couples to the starter. The collar includes a radially inner surface having a plurality of splines for engaging the shaft. The starter, when activated, rotates the collar, which rotates the shaft to start the gas turbine.