Design and component integration of a T63-A-700 gas turbine engine test facility

摘要

A gas turbine engine test cell was developed integrating an Allison T63-A-700 helicopter engine with a superflow water brake dynamometer power absorber. Design specifications were set on all systems and subsystems necessary to operate the engine. Preliminary and detailed designs of the air, water, fuel, and oil systems were developed producing a construction ready overall design. Performance predictions were made which will be compared to experimental data obtained from system operation. Standard Operating Procedures (SOP) and Emergency Operational Procedures (EOP) were developed for engine and auxiliary equipment operation. Preliminary measurements for the structural response of the engine mounting have been made which set engine operating boundaries. The facility has been built and is ready for operation.