Patent classifications
F05D2270/114
Method for regulating the temperature of the exhaust gases of a turbomachine
A method for regulating the temperature of the exhaust gases of a turbomachine, the method including regulation of the injection of fuel into a combustion chamber of the turbomachine so that the turbomachine generates a target thrust; regulation of the injection of mechanical power by an electric motor onto a shaft driven in rotation by a turbine, the electric motor being activated when a clearance between a casing and the blades of the turbine exceeds a threshold value.
Method and system for mitigating rotor bow in a turbo machine
An aspect of the present disclosure is directed to a method for mitigating rotor bow in a turbo machine. The method includes rotating a rotor over a first period of time; discontinuing rotation of the rotor for a second period of time; and iterating, over an overall period of time, rotation of the rotor over the first period of time and discontinuing rotation of the rotor for the second period of time.
Asymmetric propulsion system with heat recovery
The invention relates to an aircraft propulsion system, comprising a main transmission unit (12) and at least two turbojet engines connected to the main transmission unit (12), respectively a first turbojet engine (14a) and a second turbojet engine (14b), each turbojet engine comprising a free turbine (24a, 24b), characterized in that the first turbojet engine (14a) comprises a heat exchanger (30) configured to recover some of the thermal energy from the exhaust gas at the outlet of the free turbine, and in that the propulsion system comprises at least one computer (28a, 28b) configured to control the two turbojet engines and to limit the acceleration and the deceleration of the first turbojet engine (14a) when neither of the turbojet engines is broken down, in order to limit the reactor power transients at the heat exchanger (30).
Material fatigue improvement for hybrid propulsion systems
Hybrid electric propulsion systems are described. The hybrid electric propulsion systems include a gas turbine engine including a low speed spool and a high speed spool, the low speed spool including a low pressure compressor and a low pressure turbine, and the high speed spool including a high pressure compressor and a high pressure turbine, a mechanical power transmission configured to at least one of extract power from and supply power to at least one of the low speed spool and the high speed spool, an electric motor configured to augment rotational power of at least one of the low speed spool and the high speed spool, and a controller operable to control a power augmentation of at least one of the low speed spool and the high speed spool during an operational stress state of operation of the gas turbine engine.
Aircraft engine
A gas turbine engine for an aircraft includes a fan system having a reverse travelling wave first flap mode, Fan RTW, and including a fan located upstream of the engine core; a fan shaft; and a front engine structure arranged to support the fan shaft and having a front engine structure nodding mode comprising a pair of modes at similar, but not equal, natural frequencies in orthogonal directions; and a gearbox. An LP rotor system including the fan system and a gearbox output shaft arranged to drive the fan shaft has a first reverse whirl rotor dynamic mode, Rotor RW, and a first forward whirl rotor dynamic mode, 1FW. The engine has a maximum take-off speed, MTO. A backward whirl frequency margin of:
Gas turbine engine component
A gas turbine engine component includes an exterior pressure side with a plurality of cooling holes located in the exterior pressure side. A relief cut surrounds at least one of the plurality of cooling holes.
METHOD FOR CONTROLLING THE BENDING DEFORMATION OF A TURBOMACHINE SHAFT AT REST SUBJECTED TO THE RESIDUAL HEAT OF OPERATION OF THE TURBOMACHINE
A method for controlling the bending deformation of a turbomachine shaft at rest subjected to the residual heat of operation of the turbomachine, wherein the shaft is rotated at a rotation speed between 0.1 and 50 revolutions per minute depending on the bending deformation deflection of the shaft when the turbomachine is at rest.
TURBOMACHINE STATOR SECTOR HAVING FLEXIBLE REGIONS SUBJECTED TO HIGH STRESS
A turbine stator sector includes a plurality of vanes extending along a radial direction between a first end and a second end and along an axial direction between a leading edge and a trailing edge. The sector further includes an internal shroud linked to the first end of the vanes and an external shroud linked to the second end of the vanes. The sector includes at least one annular portion forming all or part of the internal shroud or of the external shroud. The annular portion includes a first partition present at the junction with the first or the second end of the vanes and a second partition held spaced from the first partition along the radial direction by a three-dimensional structure including a plurality of cutouts.
Transient control to extend part life in gas turbine engine
A full authority digital engine controller (FADEC) based system is also disclosed. The system includes a processor, and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the processor, cause the FADEC to perform operations. The operations may include measuring a first temperature at a first sensor disposed at a first known location of an engine, measuring a second temperature at a second sensor disposed at a second known location of the engine, and estimating at least one of a stress or a strain of a part or component in the engine based on the first temperature and the second temperature. The system may control fuel flow and/or other engine effectors during a thrust transient to limit the estimated stress or the estimated strain of the component from exceeding a predetermined threshold.