A Novel Gas Turbine Engine Health Status Estimation Method Using Quantum-Behaved Particle Swarm Optimization

Table 2

Engine gas path instrumentation set.

Num.	Symbol	Unit	Parameters
1		kN	Engine thrust
2		kg/s	Engine intake gas flow rate
3		MPa	Total pressure at high-pressure compressor exit
4		K	Total temperature at high-pressure compressor exit
5		MPa	Total pressure at low-pressure compressor exit
6		K	Total temperature at low-pressure compressor exit
7		MPa	Total pressure at afterburner exit
8		K	Total temperature at afterburner exit