ASME PTC 55 PDF

Description

This Code covers the performance testing of gas turbine aircraft engines at steady state conditions installed in a test facility. It applies to turbojet, turbofan, turboshaft, and turboprop engines.
Code covers performance testing gas turbine aircraft engines steady state conditions.  applies turbojet, turbofan, turboshaft, turboprop engines. additionally, will encompass ram and/or altitude test conditions, including sea level, static conditions. primary results include (a) thrust power (b) engine component performance, (operating lines, stall margin, efficiency) (c) auxiliary extraction (d) core fuel flow (e) specific consumption (f) total airflow (g) (h) bypass (i) bleed (j) vibration levels addition, oftentimes military commercial contracts specifications following secondary parameters: (k) pressures temperatures (l) humidity (m) rotor speeds (n) pressure ratio (o) oil (p) variable geometry settings (q) noise emissions (r) control signals brief guidance, procedures, recommendations included address measurement parameters. detailed procedures regulations found elsewhere. only applicable measuring installed facility. not aircraft, engine-specific limits margins.  cover ground-based mechanical electrical power-generating turbines, subject ptc 22. sufficient certification qualification development, intended determination research data. requirements transient testing, recognized may required meet limited contractual requirements.  information provided herein support comprehensive program.