Abstract: 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.

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Abstract: A method may comprise providing an M-flange of a gas turbine engine, wherein the M-flange may comprise a bolt hole therethrough defined by a bolt hole circumference between an inner diameter and an outer diameter of the M-flange; heating a mandrel; inserting the heated mandrel into the bolt hole such that an outer edge of the heated mandrel contacts the bolt hole circumference; and plastically deforming the bolt hole circumference to strengthen the bolt hole circumference in response to the applying the heated mandrel, producing a plastically deformed bolt hole.

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Abstract: 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.

Abstract: A rotor stack assembly for a gas turbine engine includes a first rotor assembly and a second rotor assembly axially downstream from the first rotor assembly. The first rotor assembly and the second rotor assembly include a rim, a bore and a web that extends between the rim and the bore. A tie shaft is positioned radially inward of the bores. The tie shaft maintains a compressive load on the first rotor assembly and the second rotor assembly. The compressive load is communicated through a first load path of the first rotor assembly and a second load path of the second rotor assembly. At least one of the first load path and the second load path is radially inboard of the rims.

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Abstract: A rotor stack assembly for a gas turbine engine includes a first rotor assembly and a second rotor assembly axially downstream from the first rotor assembly. The first rotor assembly and the second rotor assembly include a rim, a bore and a web that extends between the rim and the bore. A tie shaft is positioned radially inward of the bores. The tie shaft maintains a compressive load on the first rotor assembly and the second rotor assembly. The compressive load is communicated through a first load path of the first rotor assembly and a second load path of the second rotor assembly. At least one of the first load path and the second load path is radially inboard of the rims.