No Cover Image

Journal article 61 views

The effect of curved tips on the dynamics of composite rotor blades / M.R. Amoozgar; Alexander Shaw; Michael Friswell

Aerospace Science and Technology, Volume: 106, Start page: 106197

Swansea University Authors: Alexander, Shaw, Michael, Friswell

  • Accepted Manuscript under embargo until: 11th September 2021

Abstract

In this paper, the dynamics of a tailored composite rotating blade with curved tips are investigated, with a view to improving the dynamic behaviour of the blade in flight. The blade tip is curved either in the out-of-plane or in the in-plane directions. The composite blade is modelled by using the...

Full description

Published in: Aerospace Science and Technology
ISSN: 1270-9638
Published: Elsevier BV 2020
Online Access: Check full text

URI: https://cronfa.swan.ac.uk/Record/cronfa55197
Tags: Add Tag
No Tags, Be the first to tag this record!
first_indexed 2020-09-17T15:21:03Z
last_indexed 2020-11-11T04:09:56Z
id cronfa55197
recordtype SURis
fullrecord <?xml version="1.0"?><rfc1807><datestamp>2020-11-10T12:33:14.0445911</datestamp><bib-version>v2</bib-version><id>55197</id><entry>2020-09-17</entry><title>The effect of curved tips on the dynamics of composite rotor blades</title><swanseaauthors><author><sid>10cb5f545bc146fba9a542a1d85f2dea</sid><ORCID>0000-0002-7521-827X</ORCID><firstname>Alexander</firstname><surname>Shaw</surname><name>Alexander Shaw</name><active>true</active><ethesisStudent>false</ethesisStudent></author><author><sid>5894777b8f9c6e64bde3568d68078d40</sid><firstname>Michael</firstname><surname>Friswell</surname><name>Michael Friswell</name><active>true</active><ethesisStudent>false</ethesisStudent></author></swanseaauthors><date>2020-09-17</date><deptcode>EEN</deptcode><abstract>In this paper, the dynamics of a tailored composite rotating blade with curved tips are investigated, with a view to improving the dynamic behaviour of the blade in flight. The blade tip is curved either in the out-of-plane or in the in-plane directions. The composite blade is modelled by using the exact beam formulation, and the cross-sectional properties of the blade are obtained using the variational asymptotic method. The resulting nonlinear partial differential equations are discretised using a time-space scheme, and the stationary and rotating frequencies of the blade are obtained from the eigenvalues of the linearised system. Three case studies are considered here each of them representing one of the main elastic couplings that might happen in a composite blade. These three elastic couplings are the flap-twist, lag-twist, and extension-twist couplings. All these couplings are very important in the blade design as they can affect the twist and hence the dynamics of the blade. The blade tip length and curvature value are two main parameters that this paper is focused on. It is shown that the curved tip of the blade affects the blade frequencies by adding extra couplings, and therefore could be used as a potential morphing concept for tuning the frequencies, enhancing the aeroelastic stability or performance of the blade in flight.</abstract><type>Journal Article</type><journal>Aerospace Science and Technology</journal><volume>106</volume><journalNumber/><paginationStart>106197</paginationStart><paginationEnd/><publisher>Elsevier BV</publisher><placeOfPublication/><isbnPrint/><isbnElectronic/><issnPrint>1270-9638</issnPrint><issnElectronic/><keywords>Rotating frequencies, Veering, Fully intrinsic equations, Composite blade, Elastic couplings</keywords><publishedDay>1</publishedDay><publishedMonth>11</publishedMonth><publishedYear>2020</publishedYear><publishedDate>2020-11-01</publishedDate><doi>10.1016/j.ast.2020.106197</doi><url/><notes/><college>COLLEGE NANME</college><department>Engineering</department><CollegeCode>COLLEGE CODE</CollegeCode><DepartmentCode>EEN</DepartmentCode><institution>Swansea University</institution><lastEdited>2020-11-10T12:33:14.0445911</lastEdited><Created>2020-09-17T16:16:48.1314291</Created><path><level id="1">College of Engineering</level><level id="2">Engineering</level></path><authors><author><firstname>M.R.</firstname><surname>Amoozgar</surname><order>1</order></author><author><firstname>Alexander</firstname><surname>Shaw</surname><orcid>0000-0002-7521-827X</orcid><order>2</order></author><author><firstname>Michael</firstname><surname>Friswell</surname><order>3</order></author></authors><documents><document><filename>Under embargo</filename><originalFilename>Under embargo</originalFilename><uploaded>2020-09-18T08:52:07.4534993</uploaded><type>Output</type><contentLength>1732935</contentLength><contentType>application/pdf</contentType><version>Accepted Manuscript</version><cronfaStatus>true</cronfaStatus><action/><embargoDate>2021-09-11T00:00:00.0000000</embargoDate><documentNotes>&#xA9;2020 All rights reserved. All article content, except where otherwise noted, is licensed under a Creative Commons Attribution Non-Commercial No Derivatives License (CC-BY-NC-ND)</documentNotes><copyrightCorrect>true</copyrightCorrect><language>eng</language></document></documents><OutputDurs/></rfc1807>
spelling 2020-11-10T12:33:14.0445911 v2 55197 2020-09-17 The effect of curved tips on the dynamics of composite rotor blades 10cb5f545bc146fba9a542a1d85f2dea 0000-0002-7521-827X Alexander Shaw Alexander Shaw true false 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false 2020-09-17 EEN In this paper, the dynamics of a tailored composite rotating blade with curved tips are investigated, with a view to improving the dynamic behaviour of the blade in flight. The blade tip is curved either in the out-of-plane or in the in-plane directions. The composite blade is modelled by using the exact beam formulation, and the cross-sectional properties of the blade are obtained using the variational asymptotic method. The resulting nonlinear partial differential equations are discretised using a time-space scheme, and the stationary and rotating frequencies of the blade are obtained from the eigenvalues of the linearised system. Three case studies are considered here each of them representing one of the main elastic couplings that might happen in a composite blade. These three elastic couplings are the flap-twist, lag-twist, and extension-twist couplings. All these couplings are very important in the blade design as they can affect the twist and hence the dynamics of the blade. The blade tip length and curvature value are two main parameters that this paper is focused on. It is shown that the curved tip of the blade affects the blade frequencies by adding extra couplings, and therefore could be used as a potential morphing concept for tuning the frequencies, enhancing the aeroelastic stability or performance of the blade in flight. Journal Article Aerospace Science and Technology 106 106197 Elsevier BV 1270-9638 Rotating frequencies, Veering, Fully intrinsic equations, Composite blade, Elastic couplings 1 11 2020 2020-11-01 10.1016/j.ast.2020.106197 COLLEGE NANME Engineering COLLEGE CODE EEN Swansea University 2020-11-10T12:33:14.0445911 2020-09-17T16:16:48.1314291 College of Engineering Engineering M.R. Amoozgar 1 Alexander Shaw 0000-0002-7521-827X 2 Michael Friswell 3 Under embargo Under embargo 2020-09-18T08:52:07.4534993 Output 1732935 application/pdf Accepted Manuscript true 2021-09-11T00:00:00.0000000 ©2020 All rights reserved. All article content, except where otherwise noted, is licensed under a Creative Commons Attribution Non-Commercial No Derivatives License (CC-BY-NC-ND) true eng
title The effect of curved tips on the dynamics of composite rotor blades
spellingShingle The effect of curved tips on the dynamics of composite rotor blades
Alexander, Shaw
Michael, Friswell
title_short The effect of curved tips on the dynamics of composite rotor blades
title_full The effect of curved tips on the dynamics of composite rotor blades
title_fullStr The effect of curved tips on the dynamics of composite rotor blades
title_full_unstemmed The effect of curved tips on the dynamics of composite rotor blades
title_sort The effect of curved tips on the dynamics of composite rotor blades
author_id_str_mv 10cb5f545bc146fba9a542a1d85f2dea
5894777b8f9c6e64bde3568d68078d40
author_id_fullname_str_mv 10cb5f545bc146fba9a542a1d85f2dea_***_Alexander, Shaw
5894777b8f9c6e64bde3568d68078d40_***_Michael, Friswell
author Alexander, Shaw
Michael, Friswell
author2 M.R. Amoozgar
Alexander Shaw
Michael Friswell
format Journal article
container_title Aerospace Science and Technology
container_volume 106
container_start_page 106197
publishDate 2020
institution Swansea University
issn 1270-9638
doi_str_mv 10.1016/j.ast.2020.106197
publisher Elsevier BV
college_str College of Engineering
hierarchytype
hierarchy_top_id collegeofengineering
hierarchy_top_title College of Engineering
hierarchy_parent_id collegeofengineering
hierarchy_parent_title College of Engineering
department_str Engineering{{{_:::_}}}College of Engineering{{{_:::_}}}Engineering
document_store_str 0
active_str 0
description In this paper, the dynamics of a tailored composite rotating blade with curved tips are investigated, with a view to improving the dynamic behaviour of the blade in flight. The blade tip is curved either in the out-of-plane or in the in-plane directions. The composite blade is modelled by using the exact beam formulation, and the cross-sectional properties of the blade are obtained using the variational asymptotic method. The resulting nonlinear partial differential equations are discretised using a time-space scheme, and the stationary and rotating frequencies of the blade are obtained from the eigenvalues of the linearised system. Three case studies are considered here each of them representing one of the main elastic couplings that might happen in a composite blade. These three elastic couplings are the flap-twist, lag-twist, and extension-twist couplings. All these couplings are very important in the blade design as they can affect the twist and hence the dynamics of the blade. The blade tip length and curvature value are two main parameters that this paper is focused on. It is shown that the curved tip of the blade affects the blade frequencies by adding extra couplings, and therefore could be used as a potential morphing concept for tuning the frequencies, enhancing the aeroelastic stability or performance of the blade in flight.
published_date 2020-11-01T04:20:54Z
_version_ 1697075014631686144
score 10.787852