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research-article

Installed Performance Assessment of an Array of Distributed Propulsors Ingesting Boundary Layer Flow

[+] Author and Article Information
Chana Goldberg

Research Assistant, Hybrid Electric Propulsion group
c.goldberg@cranfield.ac.uk

Devaiah Nalianda

Lecturer, Propulsion Engineering Centre, Cranfield University, Cranfield, MK43 0AL, United Kingdom
devaiah.nalianda@cranfield.ac.uk

Panagiotis Laskaridis

Senior Lecturer, Propulsion Engineering Centre, Cranfield University, Cranfield, MK43 0AL, United Kingdom
p.laskaridis@cranfield.ac.uk

Pericles Pilidis

Head of Centre, Propulsion Engineering Centre, Cranfield University, Cranfield, MK43 0AL, United Kingdom
p.pilidis@cranfield.ac.uk

1Corresponding author.

ASME doi:10.1115/1.4038837 History: Received October 30, 2017; Revised November 07, 2017

Abstract

Conventional propulsion systems are typically represented as uninstalled system to suit the simple separation between airframe and engine in a podded configuration. However, boundary layer ingesting systems are inherently integrated, and require a different perspective for performance analysis. Simulations of boundary layer ingesting propulsions systems must represent the change in inlet flow characteristics which result from different local flow conditions. In addition, a suitable accounting system is required to split the airframe forces from the propulsion system forces. The research assesses the performance of a conceptual vehicle which applies a boundary layer ingesting propulsion system - NASA's N3-X blended wing body aircraft - as a case study. The performance of the aircraft's distributed propulsor array is assessed using a performance method which accounts for installation terms resulting from the boundary layer ingesting nature of the system. A `thrust split' option is considered which splits the source of thrust between the aircraft's main turbojet engines and the distributed propulsor array. An optimum thrust split for a specific fuel consumption at design point is found to occur for a thrust split value of 94.1%. In comparison, the optimum thrust split with respect to fuel consumption for the design 7500 nmi mission is found to be 93.6%, leading to a 1.5% fuel saving for the configuration considered.

Copyright (c) 2017 by ASME
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