Modelling and Simulation of helicopters and tilt-rotors in Vortex Ring State

Lead Research Organisation: University of Glasgow
Department Name: School of Engineering

Abstract

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Studentship Projects

Project Reference Relationship Related To Start End Student Name
EP/N509668/1 30/09/2016 29/09/2021
1804616 Studentship EP/N509668/1 02/10/2016 24/08/2020 Ross Higgins
 
Description Following an initial investigation into vortex ring state, it became clear that the study of propeller blades have greater importance due to the change in modern design and hence, the aeroelastic phenomena of flutter was investigated. Under certain conditions, the response of a propeller blade can become unstable and lead to potential unsafe flying conditions. Due to the danger associated with such conditions, accurate simulation methods are required to ensure such a phenomena can be captured. Such a method has been developed and applied through this award. In collaboration with DOWTY Propellers, the UK specialist is propeller design and manufacturing, the response of one of DOWTY's blades was validated and subsequently analysed under different conditions, with the insight and findings to be published within the PhD thesis. Although the method was validated via a known experiment, one of the key findings from this research was that a distinct lack of fully comprehensive experimental results were available. This has since lead on to further projects focusing on experimental study of propeller blades.
Exploitation Route Following this investigation, it became clear that a modern experimental test was required. Such findings from this award can be validated through the experimental campaign with a greater amount of detail to validate from. This award has shown that high-fidelity modelling techniques are required for such a study. This is due to the complex flow physics associated with stalled propeller flow which only resolved computational fluid dynamics can capture accurately.
Sectors Aerospace

Defence and Marine
 
Description Aid in the development of higher-fidelity methods in propeller modelling and design.
First Year Of Impact 2019
Sector Aerospace, Defence and Marine
 
Description Support provided by DOWTY Propellers for the investigation of propeller blades 
Organisation Messier-Dowty Ltd
Country United Kingdom 
Sector Private 
PI Contribution The support allowed for the validation of the method. Based upon this validated model, the blade was subsequently investigated under different conditions to provide a greater understanding for Dowty.
Collaborator Contribution Support was provided by Dowty Propellers to study propeller blades during flutter. Both geometry and experimental results were provided by Dowty.
Impact Several journal papers and conference proceedings were published as a result of this collaboration. 1) http://dx.doi.org/10.2514/1.J058463 2) https://doi.org/10.1017/aer.2019.135 3) http://dx.doi.org/10.2514/6.2019-1102
Start Year 2017
 
Title HMB3 - Helicopter Multi-Block 3 
Description The HMB3 CFD solver has been extended and validated for stall flutter flows. This is a new application area for out in-house CFD solver. Apart from the validation and extension of the tool to cover this particular type of fluid-structure interaction, additional documentation has been produced for HMB3 and additional test cases were added to its validation database. 
Type Of Technology Software 
Year Produced 2019 
Impact The advent of small, personal flying machines, requires the use of safe propeller blades, free from flutter. The HMB3 method as extended in this project can cover this gap and deliver computations of high fidelity that can be used to de-risk propeller designs for stall flutter. 
URL http://www.gla.ac.uk/cfd