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Preliminary Design Assessments of Pusher Geared Counter-Rotating Open Rotors: Part I — Low Pressure System Design Choices, Engine Preliminary Design Philosophy and Modelling Methodology

[+] Author Affiliations
Pablo Bellocq

TOTAL S. A., Pau Cedex, France

Iñaki Garmendia

University of the Basque Country UPV/EHU, San Sebastian, Spain

Vishal Sethi

Cranfield University, Cranfield, UK

Paper No. GT2015-43812, pp. V001T01A031; 12 pages
doi:10.1115/GT2015-43812
From:
  • ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
  • Volume 1: Aircraft Engine; Fans and Blowers; Marine
  • Montreal, Quebec, Canada, June 15–19, 2015
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5662-8
  • Copyright © 2015 by ASME

abstract

In this 2-part publication, the impact of the main low pressure system parameters of a pusher counter rotating Geared Open Rotor (GOR) on mission fuel burn, certification noise and emissions is presented for a 160 PAX medium haul class aircraft.

Due to their high propulsive efficiency, GORs have the potential to significantly reduce fuel consumption and emissions relative to conventional high bypass ratio turbofans. However, this novel engine architecture presents many design and operational challenges both at engine and aircraft level.

The assessment of the impact of the main low pressure preliminary design parameters of GORs on mission fuel burn, certification noise and emissions is necessary at preliminary design stages in order to identify optimum design regions. These assessments may also aid the development process when compromises need to be performed as a consequence of design, operational or regulatory constraints.

Part I of this two-part publication describes the main low pressure (LP) system design choices for a GOR as well as the preliminary design philosophy and simulation framework developed for the assessments. Part II presents the assessment studies. The simulation framework described in this paper comprises the following models: engine and aircraft performance, engine mechanical design and weight, engine certification noise and emissions.

A novel aspect of the presented simulation framework is that the design point efficiency and the design feasibility of the low pressure components are calculated for each engine design.

Copyright © 2015 by ASME

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