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Aircraft Turbine Engine Development 133 constructing the duty cycle, the engine designer studies the system’s full spectrum of projected mission profiles. The designer then develops a “composite” cycle that reflects, in a compressed period of testing, a series of representative throttle settings, transients, dwell times, pressures, and temperatures. So, for example, one hour of endurance testing is designed to duplicate the structural demands of multiple hours of mission operation in the aircraft. Cycles are now run on an automated schedule in the test cell to allow for rapid accumulation of endurance hours in a minimal number of test hours. This reduces test costs and allows endurance testing to stay ahead of the fleet when introducing new components. Successful completion of this durability testing and certification means that no additional development effort is required for full specification compliance and leads to approval of the OCR milestone. The OCR milestone demonstrates system durability, which was not addressed by the MQT, and was added to provide a more reliable fielded system to the operator. Hot and cold section life verification is one of the elements of en- durance testing. A tailored duty cycle may be developed to target damage accumulation specifically at hot or cold section parts be- cause the life of these components is typically affected by different types of operation. A series of these types of tests is run throughout the development program. Often, the program will designate a test engine for the sole purpose of milestone qualification. This dedicated qualification vehicle is used to verify that the engine’s final configuration, with all design modifications incorporated, meets all specification requirements. Qualification testing usually includes a repeat of much of the engine testing done in the development program on this single, final con- figuration engine. In some cases, where time or funding is con- strained, data from earlier development testing may be accepted for official qualification if significant modifications have not been made to the engine configuration. Controls and integration testing verifies the functionality and com- patibility of engine systems and aircraft systems that must interface. Integration begins at the component level, continues during engine testing in the sea-level and altitude test cells, and follows into flight test. This testing includes evaluation of the engine control system asPDF Image | Military Jet Engine Acquisition Technology Basics and Cost-Estimating Methodology
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