| Abstract | As part of a continuing program of gas turbine cycle calculations, the Engine Laboratory of the National Research Council of Canada has proposed a simplified method for calculating off-design-point performance of turbojet and turbofan engines, both at sea level static and at altitude flight conditions. This method specifically implies constancy of component efficiencies and linearity of corrected mass flow with corrected engine speed.
During a series of tests on a J-75 two-spool turbojet engine, experimental data were gathered at part-throttle conditions, and subsequently with compressor bleed extraction and with propelling nozzle area change.
In general, the calculation routine yielded very good predictions of the part-throttle performance of the datum engine. It was far less successful, however, in forecasting the effects of compressor bleed extraction, propelling nozzle area change, and combinations of these perturbations to the basic cycle. |
|---|
