Towards simulation of NASA35 axial compressor
Purpose – This paper aims to validate and analyse the NASA35 axial compressor performance based on a numerical approach. Design/methodology/approach – Knowledge about flow property change during compressor operation at high and relatively low speed is still limited. This work provides a numerical ap...
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| Veröffentlicht in: | Aircraft Engineering and Aerospace Technology 2015-10, Vol.87 (6), p.571-583 |
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| container_title | Aircraft Engineering and Aerospace Technology |
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| creator | Xiang, Junting Schlüter, Jorg Uwe Duan, Fei |
| description | Purpose
– This paper aims to validate and analyse the NASA35 axial compressor performance based on a numerical approach.
Design/methodology/approach
– Knowledge about flow property change during compressor operation at high and relatively low speed is still limited. This work provides a numerical approach to address these problems. Validation of numerical methods is proposed to generate confidence the numerical approach adopted, and after that, analysis of compressor performance at different operation conditions is carried out.
Findings
– The numerical methods proposed are proved capable in predicting compressor performance. Changes of flow property during compressor operation are discussed and explained.
Research limitations/implications
– The current numerical work is carried out based on the first stage of the NASA35 axial compressor, where the interactive effects from adjacent stage are not counted in. Furthermore, the steady-state simulation enforces an averaging of flow at rotor-stator interface, where the transient rotor-stator interaction is removed.
Practical implications
– This work validates the numerical methods used in the prediction of NASA35 axial compressor performance, and a similar numerical approach can be used for other turbomachinery simulation cases.
Originality/value
– This work reinforces the understanding of axial compressor operation and provides reliable results for further investigation of a similar type of compressor. In addition, details of flow field within the NASA35 compressor during operation are given and explained which experiments still have difficult to achieve. |
| doi_str_mv | 10.1108/AEAT-03-2015-0073 |
| format | Article |
| fullrecord | <record><control><sourceid>proquest_cross</sourceid><recordid>TN_cdi_proquest_journals_2080775711</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>2080775711</sourcerecordid><originalsourceid>FETCH-LOGICAL-c347t-80320abb717ba294a82ecfa8ddc905df7056770cb70c37a10a0cb58b64b184383</originalsourceid><addsrcrecordid>eNptkE1LxDAQhoMouK7-AG8FL16iM0mzSY9lWT9A9OB6DtM0hS7tZk22qP_elvWieBjmPTzvMDyMXSLcIIK5LVflmoPkAlBxAC2P2Ay1MjwXKI-nnBtuTC5O2VlKGwBcKJAzxtfhg2KdstT2Q0f7Nmyz0GTP5WspVUafLXWZC_0u-pRCPGcnDXXJX_zsOXu7W62XD_zp5f5xWT5xJ3O95wakAKoqjboiUeRkhHcNmbp2Bai60aAWWoOrxpGaEGjMylSLvEKTSyPn7PpwdxfD--DT3vZtcr7raOvDkCwapWQhChAjevUH3YQhbsfvrAADWiuNOFJ4oFwMKUXf2F1se4pfFsFOAu0k0IK0k0A7CRw7cOj43kfq6n8rv5zLbzMtbto</addsrcrecordid><sourcetype>Aggregation Database</sourcetype><iscdi>true</iscdi><recordtype>article</recordtype><pqid>2080775711</pqid></control><display><type>article</type><title>Towards simulation of NASA35 axial compressor</title><source>Emerald A-Z Current Journals</source><creator>Xiang, Junting ; Schlüter, Jorg Uwe ; Duan, Fei</creator><contributor>Renuganth Varatharajoo, Prof</contributor><creatorcontrib>Xiang, Junting ; Schlüter, Jorg Uwe ; Duan, Fei ; Renuganth Varatharajoo, Prof</creatorcontrib><description>Purpose
– This paper aims to validate and analyse the NASA35 axial compressor performance based on a numerical approach.
Design/methodology/approach
– Knowledge about flow property change during compressor operation at high and relatively low speed is still limited. This work provides a numerical approach to address these problems. Validation of numerical methods is proposed to generate confidence the numerical approach adopted, and after that, analysis of compressor performance at different operation conditions is carried out.
Findings
– The numerical methods proposed are proved capable in predicting compressor performance. Changes of flow property during compressor operation are discussed and explained.
Research limitations/implications
– The current numerical work is carried out based on the first stage of the NASA35 axial compressor, where the interactive effects from adjacent stage are not counted in. Furthermore, the steady-state simulation enforces an averaging of flow at rotor-stator interface, where the transient rotor-stator interaction is removed.
Practical implications
– This work validates the numerical methods used in the prediction of NASA35 axial compressor performance, and a similar numerical approach can be used for other turbomachinery simulation cases.
Originality/value
– This work reinforces the understanding of axial compressor operation and provides reliable results for further investigation of a similar type of compressor. In addition, details of flow field within the NASA35 compressor during operation are given and explained which experiments still have difficult to achieve.</description><identifier>ISSN: 1748-8842</identifier><identifier>ISSN: 0002-2667</identifier><identifier>EISSN: 1758-4213</identifier><identifier>DOI: 10.1108/AEAT-03-2015-0073</identifier><language>eng</language><publisher>Bradford: Emerald Group Publishing Limited</publisher><subject>Aerospace engineering ; Boundary conditions ; Compressors ; Computer simulation ; Design engineering ; Design specifications ; Efficiency ; Engineering ; Entropy ; Gas turbine engines ; Low speed ; Mathematical models ; Methods ; Numerical analysis ; Numerical methods ; Numerical prediction ; Performance prediction ; Pressure distribution ; Rotor stator interactions ; Rotors ; Simulation ; Stators ; Studies ; Turbocompressors ; Turbomachinery ; Turbulence models ; Validation studies</subject><ispartof>Aircraft Engineering and Aerospace Technology, 2015-10, Vol.87 (6), p.571-583</ispartof><rights>Emerald Group Publishing Limited</rights><rights>Emerald Group Publishing Limited 2015</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c347t-80320abb717ba294a82ecfa8ddc905df7056770cb70c37a10a0cb58b64b184383</citedby><cites>FETCH-LOGICAL-c347t-80320abb717ba294a82ecfa8ddc905df7056770cb70c37a10a0cb58b64b184383</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,777,781,962,27905,27906</link.rule.ids></links><search><contributor>Renuganth Varatharajoo, Prof</contributor><creatorcontrib>Xiang, Junting</creatorcontrib><creatorcontrib>Schlüter, Jorg Uwe</creatorcontrib><creatorcontrib>Duan, Fei</creatorcontrib><title>Towards simulation of NASA35 axial compressor</title><title>Aircraft Engineering and Aerospace Technology</title><description>Purpose
– This paper aims to validate and analyse the NASA35 axial compressor performance based on a numerical approach.
Design/methodology/approach
– Knowledge about flow property change during compressor operation at high and relatively low speed is still limited. This work provides a numerical approach to address these problems. Validation of numerical methods is proposed to generate confidence the numerical approach adopted, and after that, analysis of compressor performance at different operation conditions is carried out.
Findings
– The numerical methods proposed are proved capable in predicting compressor performance. Changes of flow property during compressor operation are discussed and explained.
Research limitations/implications
– The current numerical work is carried out based on the first stage of the NASA35 axial compressor, where the interactive effects from adjacent stage are not counted in. Furthermore, the steady-state simulation enforces an averaging of flow at rotor-stator interface, where the transient rotor-stator interaction is removed.
Practical implications
– This work validates the numerical methods used in the prediction of NASA35 axial compressor performance, and a similar numerical approach can be used for other turbomachinery simulation cases.
Originality/value
– This work reinforces the understanding of axial compressor operation and provides reliable results for further investigation of a similar type of compressor. In addition, details of flow field within the NASA35 compressor during operation are given and explained which experiments still have difficult to achieve.</description><subject>Aerospace engineering</subject><subject>Boundary conditions</subject><subject>Compressors</subject><subject>Computer simulation</subject><subject>Design engineering</subject><subject>Design specifications</subject><subject>Efficiency</subject><subject>Engineering</subject><subject>Entropy</subject><subject>Gas turbine engines</subject><subject>Low speed</subject><subject>Mathematical models</subject><subject>Methods</subject><subject>Numerical analysis</subject><subject>Numerical methods</subject><subject>Numerical prediction</subject><subject>Performance prediction</subject><subject>Pressure distribution</subject><subject>Rotor stator interactions</subject><subject>Rotors</subject><subject>Simulation</subject><subject>Stators</subject><subject>Studies</subject><subject>Turbocompressors</subject><subject>Turbomachinery</subject><subject>Turbulence models</subject><subject>Validation studies</subject><issn>1748-8842</issn><issn>0002-2667</issn><issn>1758-4213</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2015</creationdate><recordtype>article</recordtype><sourceid>AFKRA</sourceid><sourceid>AZQEC</sourceid><sourceid>BENPR</sourceid><sourceid>CCPQU</sourceid><sourceid>DWQXO</sourceid><sourceid>GNUQQ</sourceid><recordid>eNptkE1LxDAQhoMouK7-AG8FL16iM0mzSY9lWT9A9OB6DtM0hS7tZk22qP_elvWieBjmPTzvMDyMXSLcIIK5LVflmoPkAlBxAC2P2Ay1MjwXKI-nnBtuTC5O2VlKGwBcKJAzxtfhg2KdstT2Q0f7Nmyz0GTP5WspVUafLXWZC_0u-pRCPGcnDXXJX_zsOXu7W62XD_zp5f5xWT5xJ3O95wakAKoqjboiUeRkhHcNmbp2Bai60aAWWoOrxpGaEGjMylSLvEKTSyPn7PpwdxfD--DT3vZtcr7raOvDkCwapWQhChAjevUH3YQhbsfvrAADWiuNOFJ4oFwMKUXf2F1se4pfFsFOAu0k0IK0k0A7CRw7cOj43kfq6n8rv5zLbzMtbto</recordid><startdate>20151005</startdate><enddate>20151005</enddate><creator>Xiang, Junting</creator><creator>Schlüter, Jorg Uwe</creator><creator>Duan, Fei</creator><general>Emerald Group Publishing Limited</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7RQ</scope><scope>7TB</scope><scope>7WY</scope><scope>7XB</scope><scope>8AF</scope><scope>8FD</scope><scope>8FE</scope><scope>8FG</scope><scope>ABJCF</scope><scope>AFKRA</scope><scope>ARAPS</scope><scope>AZQEC</scope><scope>BENPR</scope><scope>BEZIV</scope><scope>BGLVJ</scope><scope>CCPQU</scope><scope>D1I</scope><scope>DWQXO</scope><scope>F28</scope><scope>FR3</scope><scope>GNUQQ</scope><scope>H8D</scope><scope>HCIFZ</scope><scope>K6~</scope><scope>KB.</scope><scope>L.-</scope><scope>L6V</scope><scope>L7M</scope><scope>M0F</scope><scope>M1Q</scope><scope>M2P</scope><scope>M7S</scope><scope>P5Z</scope><scope>P62</scope><scope>PDBOC</scope><scope>PQBIZ</scope><scope>PQEST</scope><scope>PQQKQ</scope><scope>PQUKI</scope><scope>PTHSS</scope><scope>Q9U</scope></search><sort><creationdate>20151005</creationdate><title>Towards simulation of NASA35 axial compressor</title><author>Xiang, Junting ; Schlüter, Jorg Uwe ; Duan, Fei</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c347t-80320abb717ba294a82ecfa8ddc905df7056770cb70c37a10a0cb58b64b184383</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2015</creationdate><topic>Aerospace engineering</topic><topic>Boundary conditions</topic><topic>Compressors</topic><topic>Computer simulation</topic><topic>Design engineering</topic><topic>Design specifications</topic><topic>Efficiency</topic><topic>Engineering</topic><topic>Entropy</topic><topic>Gas turbine engines</topic><topic>Low speed</topic><topic>Mathematical models</topic><topic>Methods</topic><topic>Numerical analysis</topic><topic>Numerical methods</topic><topic>Numerical prediction</topic><topic>Performance prediction</topic><topic>Pressure distribution</topic><topic>Rotor stator interactions</topic><topic>Rotors</topic><topic>Simulation</topic><topic>Stators</topic><topic>Studies</topic><topic>Turbocompressors</topic><topic>Turbomachinery</topic><topic>Turbulence models</topic><topic>Validation studies</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Xiang, Junting</creatorcontrib><creatorcontrib>Schlüter, Jorg Uwe</creatorcontrib><creatorcontrib>Duan, Fei</creatorcontrib><collection>CrossRef</collection><collection>Career & Technical Education Database</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>ABI/INFORM Collection</collection><collection>ProQuest Central (purchase pre-March 2016)</collection><collection>STEM Database</collection><collection>Technology Research Database</collection><collection>ProQuest SciTech Collection</collection><collection>ProQuest Technology Collection</collection><collection>Materials Science & Engineering Collection</collection><collection>ProQuest Central UK/Ireland</collection><collection>Advanced Technologies & Aerospace Collection</collection><collection>ProQuest Central Essentials</collection><collection>ProQuest Central</collection><collection>Business Premium Collection</collection><collection>Technology Collection</collection><collection>ProQuest One Community College</collection><collection>ProQuest Materials Science Collection</collection><collection>ProQuest Central Korea</collection><collection>ANTE: Abstracts in New Technology & Engineering</collection><collection>Engineering Research Database</collection><collection>ProQuest Central Student</collection><collection>Aerospace Database</collection><collection>SciTech Premium Collection</collection><collection>ProQuest Business Collection</collection><collection>Materials Science Database</collection><collection>ABI/INFORM Professional Advanced</collection><collection>ProQuest Engineering Collection</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>ABI/INFORM Trade & Industry</collection><collection>Military Database</collection><collection>Science Database</collection><collection>Engineering Database</collection><collection>Advanced Technologies & Aerospace Database</collection><collection>ProQuest Advanced Technologies & Aerospace Collection</collection><collection>Materials Science Collection</collection><collection>ProQuest One Business</collection><collection>ProQuest One Academic Eastern Edition (DO NOT USE)</collection><collection>ProQuest One Academic</collection><collection>ProQuest One Academic UKI Edition</collection><collection>Engineering Collection</collection><collection>ProQuest Central Basic</collection><jtitle>Aircraft Engineering and Aerospace Technology</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Xiang, Junting</au><au>Schlüter, Jorg Uwe</au><au>Duan, Fei</au><au>Renuganth Varatharajoo, Prof</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Towards simulation of NASA35 axial compressor</atitle><jtitle>Aircraft Engineering and Aerospace Technology</jtitle><date>2015-10-05</date><risdate>2015</risdate><volume>87</volume><issue>6</issue><spage>571</spage><epage>583</epage><pages>571-583</pages><issn>1748-8842</issn><issn>0002-2667</issn><eissn>1758-4213</eissn><abstract>Purpose
– This paper aims to validate and analyse the NASA35 axial compressor performance based on a numerical approach.
Design/methodology/approach
– Knowledge about flow property change during compressor operation at high and relatively low speed is still limited. This work provides a numerical approach to address these problems. Validation of numerical methods is proposed to generate confidence the numerical approach adopted, and after that, analysis of compressor performance at different operation conditions is carried out.
Findings
– The numerical methods proposed are proved capable in predicting compressor performance. Changes of flow property during compressor operation are discussed and explained.
Research limitations/implications
– The current numerical work is carried out based on the first stage of the NASA35 axial compressor, where the interactive effects from adjacent stage are not counted in. Furthermore, the steady-state simulation enforces an averaging of flow at rotor-stator interface, where the transient rotor-stator interaction is removed.
Practical implications
– This work validates the numerical methods used in the prediction of NASA35 axial compressor performance, and a similar numerical approach can be used for other turbomachinery simulation cases.
Originality/value
– This work reinforces the understanding of axial compressor operation and provides reliable results for further investigation of a similar type of compressor. In addition, details of flow field within the NASA35 compressor during operation are given and explained which experiments still have difficult to achieve.</abstract><cop>Bradford</cop><pub>Emerald Group Publishing Limited</pub><doi>10.1108/AEAT-03-2015-0073</doi><tpages>13</tpages></addata></record> |
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| identifier | ISSN: 1748-8842 |
| ispartof | Aircraft Engineering and Aerospace Technology, 2015-10, Vol.87 (6), p.571-583 |
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| source | Emerald A-Z Current Journals |
| subjects | Aerospace engineering Boundary conditions Compressors Computer simulation Design engineering Design specifications Efficiency Engineering Entropy Gas turbine engines Low speed Mathematical models Methods Numerical analysis Numerical methods Numerical prediction Performance prediction Pressure distribution Rotor stator interactions Rotors Simulation Stators Studies Turbocompressors Turbomachinery Turbulence models Validation studies |
| title | Towards simulation of NASA35 axial compressor |
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