Herein provided are systems and methods for operating an aircraft engine during inclement weather. At least one image of a location substantially in line with a heading of the aircraft is acquired. Based on the at least one image, an inclement weather condition in the location is detected. An alert mode of the engine is triggered upon detecting the inclement weather condition. Responsive to the alert mode being triggered, at least one predetermined performance parameter of the engine is monitored. Upon detecting a change in the at least one predetermined performance parameter beyond a predetermined threshold, at least one operating condition of the engine is altered.

Various embodiments may include a method for monitoring a hot gas region of a gas turbine comprising: monitoring the region using an imaging radar assembly remote from the region, connected to the region with a hollow conductor. The hollow conductor is closed off at a first end proximate the radar assembly. The radar assembly operates outside the closed-off cavity and the second end opens into the region or is shielded against heat but permeable to radar waves passing into the region. The radar is actuated in time intervals wherein at least parts of the hot gas space are detected by the radar assembly repeatedly at the time intervals. The method includes: feeding acquired image data to an evaluation device; evaluating the acquired image data against a predefined maintenance requirement; and triggering a maintenance alarm as a function of the result of the evaluation.

A process for mitigating or proactively avoiding an aircraft engine icing event may include detecting ice crystals in the atmosphere using one or more sensors on board an aircraft in real time. The process may also include modulating one or more engine operating conditions to proactively change an ice accretion location, to avoid the occurrence of an icing event. The process may further include implementing one or more modulated engine operating conditions in engine controls software, hardware, or both.

Systems and methods for enhancing engine performance based on atmospheric ice particles are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a reflectivity measurement for each of the one or more points obtained using a device located on the aircraft. The method can further include determining an estimate of ice water content for each of the one or more points based at least in part on the reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable bleed valve) based at least in part on the estimate of ice water content for at least one of the plurality of points.

Systems and methods for enhancing engine performance based on atmospheric rain conditions are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a radar reflectivity measurement for each of the one or more points obtained using a radar device located on the aircraft. The method can further include determining an estimate of liquid water content for each of the one or more points based at least in part on the radar reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable stator vane) based at least in part on the estimate of liquid water content for at least one of the plurality of points.

Systems and methods for enhancing engine performance based on atmospheric rain conditions are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a radar reflectivity measurement for each of the one or more points obtained using a radar device located on the aircraft. The method can further include determining an estimate of liquid water content for each of the one or more points based at least in part on the radar reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable stator vane) based at least in part on the estimate of liquid water content for at least one of the plurality of points.

Systems and methods for enhancing engine performance based on atmospheric ice particles are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a reflectivity measurement for each of the one or more points obtained using a device located on the aircraft. The method can further include determining an estimate of ice water content for each of the one or more points based at least in part on the reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable bleed valve) based at least in part on the estimate of ice water content for at least one of the plurality of points.

A gas turbine engine for an aircraft that includes a nacelle, a fan, an engine core, a bypass duct extending between the engine core and the nacelle and guiding a bypass airflow through the bypass duct, and at least one non-structural strut extending in the radial direction within the bypass duct, wherein the non-structural strut includes an outside wall acting as a heat exchanger, and wherein the outside wall includes first transport means configured to transport in the outside wall at least one fluid to be cooled. It is provided that the non-structural strut further includes second transport means configured to transport a fluid to be heated, wherein the first transport means and the second transport means are configured such that the fluid to be heated is heated by the at least one fluid to be cooled and the at least one fluid to be cooled is cooled both by the bypass airflow and the fluid to be heated.

An automatic emergency radar and proximity sensor activated protection system that could assist to prevent commercial, private, or military aircraft jet engines from being damaged or destroyed by the installment of a Shielding Blade Assembly which will immediately close when detection of objects such as; birds, debris, or other destructive elements try to enter through the engine intake while the aircraft is in FLIGHT causing the Internal Air Injection Unit (A.I.U.) to supply high volumes of air in order for the engine to stay operational and prevent it from stalling while in FLIGHT.