Methods and systems for operating an engine are provided. An engine core temperature is monitored. When the engine core temperature is below an engine thermal limit adjusted for a level of deterioration of the engine, an output power of the engine is set in accordance with a reference power based on non-thermal limits of the engine. When the engine core temperature is near or above the engine thermal limit adjusted for the level of deterioration of the engine, the output power of the engine is set to a value lower than the reference power based on non-thermal limits of the engine to reduce the engine core temperature.

An aircraft turbomachine module comprising a ventilation device configured to have a cooling air flow circulate in the turbomachine module, the ventilation device comprising an air outlet, blocking means fixed to the air outlet and mobile between a blocking position of the air outlet and an opening position of the air outlet, and locking means configured to maintain the blocking means in one of the blocking position and the opening position when the temperature within the module is less than a predetermined threshold value, the blocking means being configured to adopt the other of the blocking position and the opening position when the temperature within the module is greater than said predetermined threshold value.

Methods and systems for operating an engine are provided. An engine core temperature is monitored. When the engine core temperature is below an engine thermal limit adjusted for a level of deterioration of the engine, an output power of the engine is set in accordance with a reference power based on non-thermal limits of the engine. When the engine core temperature is near or above the engine thermal limit adjusted for the level of deterioration of the engine, the output power of the engine is set to a value lower than the reference power based on non-thermal limits of the engine to reduce the engine core temperature.

An assembly having an outer tubular portion delimiting an inner space, an inner tubular portion in the outer tubular portion, a fluid jacket in the inner tubular portion, a plurality of groups of at least four thermal flow sensors. For each group, the sensors of the group are disposed in the inner space and overall in one and the same plane perpendicular to a central line. In each group, the sensors of the group are distributed angularly about the central line. A control unit which, for each group, receives the data from each sensor of the group and which, on the basis of these data, determines a warning level. With such an arrangement, the monitoring of the values of the different thermal flow sensors makes it possible to monitor a potential problem at the fluid jacket.

A method for controlling the clearance between the blade tips of a high-pressure turbine of a gas turbine aircraft engine and a turbine shroud, including the controlling of a valve delivering a stream of air to the turbine shroud, this method further including the following steps: the detection of a transient acceleration phase of the engine; the receiving of an item of data representative of the gas temperature at the outlet of the combustion chamber of the engine; a valve opening command, to deliver the air stream to the turbine shroud or to increase the flow rate of the delivered air stream, if the transient acceleration phase is detected and if the gas temperature at the outlet of the combustion chamber is greater than a first temperature threshold corresponding to a degraded clearance characteristic of an aged engine, this threshold being less than an operating limit temperature of the engine.

An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.

A method of operating a turbine engine that includes shutting down the turbine engine such that a rotational speed of the turbine engine decreases, and actuating a starter motor of the turbine engine at one of as the rotational speed of the turbine engine decreases or at a preset time after the turbine engine receives a full stop command such that residual heat is exhausted from the turbine engine.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan and a braking system. The braking system is configured to selectively engage the fan during ground windmilling to apply a first level of braking to slow rotation of the fan. Further, when the rotation of the fan sufficiently slows, the braking system is further configured to apply a second level of braking more restrictive than the first level of braking.

A method of operating a turbine engine that includes shutting down the turbine engine such that a rotational speed of the turbine engine decreases, and actuating a starter motor of the turbine engine at one of as the rotational speed of the turbine engine decreases or at a preset time after the turbine engine receives a full stop command such that residual heat is exhausted from the turbine engine.

Methods, apparatus, systems, and articles of manufacture are disclosed to autonomously detect thermal anomalies. Disclosed examples include an example apparatus to detect engine anomalies comprising: at least one memory; instructions in the apparatus; and processor circuitry to execute the instructions to: control a plurality of infrared cameras to capture a baseline image set, the baseline image set including at least two thermal images; generate emissivity data based on the baseline image set; provide the baseline image set and the emissivity data to an artificial intelligence model, the artificial intelligence model to generate a reconstructed image set; determine a difference between the baseline image set and the reconstructed image set; and in response to the difference exceeding a threshold, generate an alert indicating detection of an engine anomaly.