scope:

This Code covers the performance testing of gas turbine aircraft engines at steady-state conditions. This Code applies to turbojet, turbofan, turboshaft, and turboprop engines. Additionally, the Code will encompass ram and/or altitude test conditions, including sea level static test conditions.

The primary test results include

(a) Thrust or Power

(b) Engine Component Performance (operating lines, stall margin, efficiency)

(c) Auxiliary Power Extraction

(d) Core Fuel Flow

(e) Specific Fuel Consumption

(f) Total Engine Airflow

(g) Core Airflow

(h) Bypass Airflow

(i) Bleed Airflow

(j) Vibration Levels In addition, oftentimes military and commercial contracts include specifications for the following secondary parameters:

(k) Pressures and Temperatures

(l) Humidity

(m) Rotor Speeds

(n) Engine Pressure Ratio

(o) Oil Flow

(p) Variable Geometry Settings

(q) Noise and Emissions

(r) Engine Control Signals

Brief guidance, procedures, and recommendations are included to address the measurement of these parameters. More detailed procedures and regulations for these are found elsewhere.

This Code is only applicable to measuring performance when the engine is installed in a test facility. This Code is not applicable to measuring performance when the engine is installed in an aircraft, and it does not address engine-specific limits and margins. The Code does not cover ground-based mechanical or electrical power-generating gas turbines, which is the subject of PTC 22. This Code is not sufficient for certification or qualification of engines under development, nor is it intended for determination of research data. While this Code does not cover the requirements for transient testing, it is recognized that transient testing may be required to meet some limited contractual requirements. Information on transient testing is provided herein to support a comprehensive test program.