The fundamental performance task for a single shaft turbojet is to match the operation of the compressor, turbine and propelling nozzle.
12.
Matching may be defined as designing, sizing, and manipulating the operating characteristics of the compressor, turbine and propelling nozzle.
13.
Turbojets consist of an inlet, a compressor, a combustor, a turbine ( that drives the compressor ) and a propelling nozzle.
14.
According to the type of engine, it is discharged into the atmosphere through an exhaust pipe, flue gas stack, or propelling nozzle.
15.
The most efficient atmospheric pressure at which a conventional propelling nozzle works is set by the geometry of the SSTO engine must use a single set of nozzles.
16.
Turbofan engines may have an additional and separate propelling nozzle which produces a high speed propelling jet from the energy in the air that has passed through the fan.
17.
For example, the way the compressor operates is determined by the flow resistances behind it, which occur in the combustor, turbine, tailpipe and propelling nozzle.
18.
In addition, the flow resistance seen by the compressor is determined by the two restrictors downstream, namely the turbine nozzle area and the propelling nozzle exit area.
19.
The propelling nozzle at speeds above about Mach 2 usually has extra internal thrust losses because the exit area is not big enough as a trade-off with external afterbody drag.
20.
Most of the compressor bleed was required for cooling the afterburner duct and propelling nozzle and the remainder was used, together with the turbine exhaust, to burn the afterburner fuel flow.
