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Propulsion System Integration as Applied to Business Jet Aircraft PUBLIC ACCESS

[+] Author Affiliations
J. P. Suggs, G. W. Burley

Garrett Turbine Engine Company, Phoenix, AZ

Paper No. 83-GT-227, pp. V002T02A021; 10 pages
doi:10.1115/83-GT-227
From:
  • ASME 1983 International Gas Turbine Conference and Exhibit
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Phoenix, Arizona, USA, March 27–31, 1983
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7952-8
  • Copyright © 1983 by ASME

abstract

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 configurations are included as reference data.

Copyright © 1983 by ASME
This article is only available in the PDF format.

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