The development and testing of an in-flight thrust determination method for a Pratt & Whitney JT15D-1 turbofan engine.

摘要

An in-flight thrust determination technique has been verified for a Pratt & Whitney JT15D-1B turbofan engine. The method is based on momentum theory, and only required the determination of pressure at three points inside the engine. The only pressures required are the inlet pressure, the hot exhaust nozzle pressure, and the cold exhaust nozzle pressure. The method was tested using a computer program supplied by Pratt & Whitney Canada and experimental test data. The technique was proven reliable, and recommendations for implementing the technique were made.