The process of integrating an engine into a new or existing airframe is characterized by three major phases. The first phase comprises the preliminary design, and includes all aspects of model testing, engine inlet compatibility, matching studies, and the aircraft performance determinations that are necessary to ensure an economically viable product. This phase is followed by a detailed design of the nacelle and interface systems, and a mockup evaluation period, at which time the installation interface requirements are incorporated. The final phase consists of ground and flight tests resulting in FAA certification. This phase includes the demonstration of the aircraft and propulsion system performance and system compatibility. The role of Garrett Turbine Engine Company (GTEC) in this phase is to support the Original Equipment Manufacturers by sharing its detailed installation experience to ensure an optimum engine installation. The many aspects involved in the above are examined relative to the two-, three- and four-engine configurations used by all general aviation aircraft.Factors unique to some of the existing configuration are included as reference data.
Propulsion system integration as applied to business jet aircraft
Antriebssystemintegration bei Geschaeftsreisejets
ASME-Papers ; 1-10
1982
10 Seiten, 16 Bilder, 1 Tabelle, 2 Quellen
Conference paper
English
The 3X Propulsion Concept Applied to a Business Aircraft
AIAA | 2007
|Fighter aircraft/propulsion integration
AIAA | 1986
|Cycloidal propulsion applied to aircraft
Engineering Index Backfile | 1928
|The 3X Propulsion Concept Applied to a Business Aircraft AIAA Paper
British Library Conference Proceedings | 2007
|Propulsion integration for military aircraft
Tema Archive | 1989
|