Tail-Integrated Boundary-Layer Ingesting Propulsion Systems for Turbo-Electric Aircraft

Z. Chen, M. Galbraith

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This project is focused on airframe-propulsion system integration and aimed at assessing the optimum number and arrangement of fans to yield the most integration benefit while mitigating the distortion challenge. More specifically tail-BLI aircraft configurations are considered for partial turbo-electric aircraft. The potential performance improvements are explored using an aircraft system optimization tool.

Novel Propulsion Architectures for Unmanned Aerial Vehicles

M. Shorter

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The goal of the project is to identify, assess, and apply current and novel propulsion and aerodynamic technologies to the UAV. The challenge is to put forward novel and relevant contributions to the state of the art in UAV design, particularly with regards to their propulsion. The research will consider and build on as appropriate previous work within the GTL on aviation concepts such as hybridized powertrains, vertical to horizontal flight transition, novel powerplant concepts, and boundary layer ingestion.

Modular Hybrid Propulsion System

A. Kunycky, D. Pham

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This research seeks to expand on the foundational assessments of modular hybrid aircraft propulsion systems conducted at the GTL. Particular areas of focus include optimized mission modeling, mission-based power system architecture design, robust VTOL UAV maneuverability, and incorporation of additional power technologies such as fuel cells. More broadly, this research also aims to further the investigation of novel aircraft power systems in the context of a changing global energy landscape.

Assessment of Installed Turbofan Performance & Stability of Advanced Aircraft

M. Cabral

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How do we define the prosulsion system for high subsonic aircrafts antecipating and eliminating risks related to the propulsion airframe integration? This research aims to anwser this question through a modeling framework capable of assessing fan performance and stability with inlet distortion and inlet-fan coupling. The goal is to provide installed turbofan design guidelines to mitigate the risks associated with the integration of propulsion system on novel aircrafts configurations.