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A gas turbine engine is a rotary internal combustion engine in which energy is extracted from a continuous flow of gas that is compressed, combusted, and expanded through a turbine to produce shaft power or jet thrust ^[1]. Its core consists of an air compressor that raises the pressure of incoming air, a combustor that burns fuel in the compressed air to raise gas temperature, and a turbine that extracts work from the expanding hot gas to drive the compressor; the remaining energy is delivered either as rotational shaft output to a driven load or as exhaust jet momentum for propulsion ^[1]. The engine operates on a continuous open Brayton (Joule) cycle, with air continuously entering the compressor and combustion products continuously leaving the turbine, rather than on the intermittent reciprocating cycles of piston engines ^[2]. Gas turbines are configured as turbojet, turbofan, turboprop, turboshaft, or industrial gas turbine variants depending on how the extracted work is used, and are distinguished by their continuous-flow rotary operation and by the high ratio of turbine inlet temperature to compressor delivery pressure that governs their cycle efficiency ^[3].