TURBOJET ENGINE AND METHOD OF ITS TESTING Russian patent published in 2012 - IPC G01M15/14 

FIELD: engines and pumps.

SUBSTANCE: bypass turbojet engine comprises housing, turbines with rotors, compressors, jet nozzles and control system with rotor rpm range indication range limit indicators and control device, for example, control lever and thrusts separating said frequency ranges and defining positions of said lever corresponding to maximum and augmented thrust conditions. Tests are performed at test bench in two rotor rpm ranges with identification or refinement of their limits. One of said ranges incorporates rotor rpm with compressor safety margin in tolerable limits while another one with said margin beyond said limits. In testing, engine is accelerated to one of said conditions to master compensation adjustment procedures for engine operating conditions by varying rotor rpm to define tolerable rpm magnitudes that ensure required safety margin of compressor operation. With control lever position below thrust corresponding to maximum mode, jet nozzle critical section is increased. With engine control lever on thrusts corresponding to maximum and thrust augmenting conditions, pressure difference is set at turbines to ensure required safety margins of compressor operation.

EFFECT: improved operating performances, higher safety.

2 cl