Disclosed is an active tip clearance control system (ATCCS) for a gas turbine engine, having an electronically controlled regulating valve directing cooling airflow to a turbine case, and an engine electronic control (EEC), controlling the electronically controlled regulating valve, wherein the EEC controls the electronically controlled regulating valve to regulate cooling airflow according to a selected target blade tip clearance schedule, and wherein the selected target blade tip clearance schedule is selected before or after an engine cycle, from of a plurality of target blade tip clearance schedules, each correlating to one of a plurality of thrust rating applications for the engine.

A transient cooling system includes a first phase change material (PCM) element and a second PCM element. The first PCM element includes a first PCM, a first surface, and a second surface, the first surface complementary to a surface to be cooled. The second PCM element includes a second PCM and a third surface in thermal contact with the second surface. The first PCM and the second PCM may have different thermal characteristics.

A system is provided. The system includes a combustor assembly that receives a fuel flow. The system includes a pressure sensor disposed within the combustor assembly that measures a pressure of the fuel flow from a fuel supply to a fuel nozzle of the combustor assembly. The system includes a controller communicatively coupled to the pressure sensor. The controller is configured to receive a pressure measurement from the pressure sensor. The pressure measurement is a current operating parameter of the combustor assembly. The controller is configured to determine a predicted fuel flow based at least in part on the pressure measurement, determine a fuel composition factor based on a comparison of the predicted fuel flow with a commanded fuel flow, and adjust control of the combustor assembly based on the fuel composition factor. The fuel composition factor is indicative of a change in a fuel composition of the fuel flow.

When the output power of a gas turbine is going to be reduced and when the relationship between the target output power and the rotational frequency of the gas turbine satisfies predetermined conditions, a control device of a power unit system reduces the output power of the gas turbine to the target output power and thereafter reduces the rotational frequency of the gas turbine to the target rotational frequency, whereas when the relationship between the target output power and the rotational frequency of the gas turbine does not satisfy the predetermined conditions, the control device reduces the rotational frequency of the gas turbine to the target rotational frequency and thereafter reduces the output power of the gas turbine to the target output power.

A sensor system for identifying a transient sensor failure in an industrial system and for recovering from an erroneous estimation of an expected mass flow rate resulting from the transient sensor failure. The sensor system includes one or more sensors for measuring at least one fluid property of the industrial system. The sensor system includes an enhanced flow soft sensing (EFSS) computing device configured to determine an estimated mass flow rate. The EFSS computing device is also configured to generate expected measurements to be received from one or more sensors. If an error value is not within predetermined parameters, the transient sensor failure is detected. The EFSS computing device is further configured to identify a resurgence of the sensor from the transient sensor failure. An erroneous expected mass flow rate then converges toward a correct expected mass flow rate.