Improved Compressor Exit Diffuser for an Industrial Gas Turbine
Cycle studies carried out for the medium pressure ratio gas turbine THM 1304 of 10 MW power output manufactured by MAN Turbomaschinen AG GHH BORSIG predicted that the overall efficiency of the multistage compressor, composed of a ten-stage axial and a single-stage centrifugal compressor, would impro...
Gespeichert in:
| Veröffentlicht in: | Journal of turbomachinery 2002-01, Vol.124 (1), p.19-26 |
|---|---|
| Hauptverfasser: | , , , , |
| Format: | Artikel |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | 26 |
|---|---|
| container_issue | 1 |
| container_start_page | 19 |
| container_title | Journal of turbomachinery |
| container_volume | 124 |
| creator | Orth, U Ebbing, H Krain, H Weber, A Hoffmann, B |
| description | Cycle studies carried out for the medium pressure ratio gas turbine THM 1304 of 10 MW power output manufactured by MAN Turbomaschinen AG GHH BORSIG predicted that the overall efficiency of the multistage compressor, composed of a ten-stage axial and a single-stage centrifugal compressor, would improve by 0.8 percent if the efficiency of the back stage centrifugal unit could be raised by 4 percent. It was expected that this would result in a noticeable improvement of the thermal gas turbine efficiency. The paper describes the aerodynamic design process used for the stage optimization, applying today’s advanced design tools for blade generation and three-dimensional aerodynamic calculation methods. Additionally, it describes the manufacturing procedure for the resulting three-dimensional blades and the experimental verification of the design approach. |
| doi_str_mv | 10.1115/1.1413476 |
| format | Article |
| fullrecord | <record><control><sourceid>proquest_cross</sourceid><recordid>TN_cdi_proquest_miscellaneous_27218103</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>27218103</sourcerecordid><originalsourceid>FETCH-LOGICAL-a308t-d0a6e6ae69c8c627636134f6566a174ea2d93420e9085e95ce464bd8c9724f0e3</originalsourceid><addsrcrecordid>eNpFkE1LAzEQhoMoWKsHz172ouBha7L52OQkUmstFLxU8BbS7AS27IdmdkX_vSkteJpheOZh5iXkmtEZY0w-sBkTjItSnZAJk4XOtaH0lEyo1iaXVHyckwvEHaWMcykm5HHVfsb-G6ps3qcOEPuYLX7qIXuuQxgRYhbSxHXZqqtGHGLtmmzpMNuMcVt3cEnOgmsQro51St5fFpv5a75-W67mT-vccaqHvKJOgXKgjNdeFaXiKl0ZlFTKsVKAKyrDRUHBUC3BSA9CiW2lvSkLESjwKbk7eNO1XyPgYNsaPTSN66Af0RZlwTSjPIH3B9DHHjFCsJ-xbl38tYzafUSW2WNEib09Sh1614ToOl_j_wKXNHn3zpsD57AFu-vH2KVfrZCCG8X_AIInbOk</addsrcrecordid><sourcetype>Aggregation Database</sourcetype><iscdi>true</iscdi><recordtype>article</recordtype><pqid>27218103</pqid></control><display><type>article</type><title>Improved Compressor Exit Diffuser for an Industrial Gas Turbine</title><source>ASME Transactions Journals (Current)</source><creator>Orth, U ; Ebbing, H ; Krain, H ; Weber, A ; Hoffmann, B</creator><creatorcontrib>Orth, U ; Ebbing, H ; Krain, H ; Weber, A ; Hoffmann, B</creatorcontrib><description>Cycle studies carried out for the medium pressure ratio gas turbine THM 1304 of 10 MW power output manufactured by MAN Turbomaschinen AG GHH BORSIG predicted that the overall efficiency of the multistage compressor, composed of a ten-stage axial and a single-stage centrifugal compressor, would improve by 0.8 percent if the efficiency of the back stage centrifugal unit could be raised by 4 percent. It was expected that this would result in a noticeable improvement of the thermal gas turbine efficiency. The paper describes the aerodynamic design process used for the stage optimization, applying today’s advanced design tools for blade generation and three-dimensional aerodynamic calculation methods. Additionally, it describes the manufacturing procedure for the resulting three-dimensional blades and the experimental verification of the design approach.</description><identifier>ISSN: 0889-504X</identifier><identifier>EISSN: 1528-8900</identifier><identifier>DOI: 10.1115/1.1413476</identifier><identifier>CODEN: JOTUEI</identifier><language>eng</language><publisher>New York, NY: ASME</publisher><subject>Aerodynamics ; Applied fluid mechanics ; Applied sciences ; Continuous cycle engines: steam and gas turbines, jet engines ; Engines and turbines ; Exact sciences and technology ; Fluid dynamics ; Fundamental areas of phenomenology (including applications) ; Mechanical engineering. Machine design ; Physics ; Pump and compressors (turbocompressors, fans, etc.)</subject><ispartof>Journal of turbomachinery, 2002-01, Vol.124 (1), p.19-26</ispartof><rights>2002 INIST-CNRS</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a308t-d0a6e6ae69c8c627636134f6566a174ea2d93420e9085e95ce464bd8c9724f0e3</citedby><cites>FETCH-LOGICAL-a308t-d0a6e6ae69c8c627636134f6566a174ea2d93420e9085e95ce464bd8c9724f0e3</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,4024,27923,27924,27925,38520</link.rule.ids><backlink>$$Uhttp://pascal-francis.inist.fr/vibad/index.php?action=getRecordDetail&idt=13502723$$DView record in Pascal Francis$$Hfree_for_read</backlink></links><search><creatorcontrib>Orth, U</creatorcontrib><creatorcontrib>Ebbing, H</creatorcontrib><creatorcontrib>Krain, H</creatorcontrib><creatorcontrib>Weber, A</creatorcontrib><creatorcontrib>Hoffmann, B</creatorcontrib><title>Improved Compressor Exit Diffuser for an Industrial Gas Turbine</title><title>Journal of turbomachinery</title><addtitle>J. Turbomach</addtitle><description>Cycle studies carried out for the medium pressure ratio gas turbine THM 1304 of 10 MW power output manufactured by MAN Turbomaschinen AG GHH BORSIG predicted that the overall efficiency of the multistage compressor, composed of a ten-stage axial and a single-stage centrifugal compressor, would improve by 0.8 percent if the efficiency of the back stage centrifugal unit could be raised by 4 percent. It was expected that this would result in a noticeable improvement of the thermal gas turbine efficiency. The paper describes the aerodynamic design process used for the stage optimization, applying today’s advanced design tools for blade generation and three-dimensional aerodynamic calculation methods. Additionally, it describes the manufacturing procedure for the resulting three-dimensional blades and the experimental verification of the design approach.</description><subject>Aerodynamics</subject><subject>Applied fluid mechanics</subject><subject>Applied sciences</subject><subject>Continuous cycle engines: steam and gas turbines, jet engines</subject><subject>Engines and turbines</subject><subject>Exact sciences and technology</subject><subject>Fluid dynamics</subject><subject>Fundamental areas of phenomenology (including applications)</subject><subject>Mechanical engineering. Machine design</subject><subject>Physics</subject><subject>Pump and compressors (turbocompressors, fans, etc.)</subject><issn>0889-504X</issn><issn>1528-8900</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2002</creationdate><recordtype>article</recordtype><recordid>eNpFkE1LAzEQhoMoWKsHz172ouBha7L52OQkUmstFLxU8BbS7AS27IdmdkX_vSkteJpheOZh5iXkmtEZY0w-sBkTjItSnZAJk4XOtaH0lEyo1iaXVHyckwvEHaWMcykm5HHVfsb-G6ps3qcOEPuYLX7qIXuuQxgRYhbSxHXZqqtGHGLtmmzpMNuMcVt3cEnOgmsQro51St5fFpv5a75-W67mT-vccaqHvKJOgXKgjNdeFaXiKl0ZlFTKsVKAKyrDRUHBUC3BSA9CiW2lvSkLESjwKbk7eNO1XyPgYNsaPTSN66Af0RZlwTSjPIH3B9DHHjFCsJ-xbl38tYzafUSW2WNEib09Sh1614ToOl_j_wKXNHn3zpsD57AFu-vH2KVfrZCCG8X_AIInbOk</recordid><startdate>20020101</startdate><enddate>20020101</enddate><creator>Orth, U</creator><creator>Ebbing, H</creator><creator>Krain, H</creator><creator>Weber, A</creator><creator>Hoffmann, B</creator><general>ASME</general><general>American Society of Mechanical Engineers</general><scope>IQODW</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope></search><sort><creationdate>20020101</creationdate><title>Improved Compressor Exit Diffuser for an Industrial Gas Turbine</title><author>Orth, U ; Ebbing, H ; Krain, H ; Weber, A ; Hoffmann, B</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a308t-d0a6e6ae69c8c627636134f6566a174ea2d93420e9085e95ce464bd8c9724f0e3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2002</creationdate><topic>Aerodynamics</topic><topic>Applied fluid mechanics</topic><topic>Applied sciences</topic><topic>Continuous cycle engines: steam and gas turbines, jet engines</topic><topic>Engines and turbines</topic><topic>Exact sciences and technology</topic><topic>Fluid dynamics</topic><topic>Fundamental areas of phenomenology (including applications)</topic><topic>Mechanical engineering. Machine design</topic><topic>Physics</topic><topic>Pump and compressors (turbocompressors, fans, etc.)</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Orth, U</creatorcontrib><creatorcontrib>Ebbing, H</creatorcontrib><creatorcontrib>Krain, H</creatorcontrib><creatorcontrib>Weber, A</creatorcontrib><creatorcontrib>Hoffmann, B</creatorcontrib><collection>Pascal-Francis</collection><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><jtitle>Journal of turbomachinery</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Orth, U</au><au>Ebbing, H</au><au>Krain, H</au><au>Weber, A</au><au>Hoffmann, B</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Improved Compressor Exit Diffuser for an Industrial Gas Turbine</atitle><jtitle>Journal of turbomachinery</jtitle><stitle>J. Turbomach</stitle><date>2002-01-01</date><risdate>2002</risdate><volume>124</volume><issue>1</issue><spage>19</spage><epage>26</epage><pages>19-26</pages><issn>0889-504X</issn><eissn>1528-8900</eissn><coden>JOTUEI</coden><abstract>Cycle studies carried out for the medium pressure ratio gas turbine THM 1304 of 10 MW power output manufactured by MAN Turbomaschinen AG GHH BORSIG predicted that the overall efficiency of the multistage compressor, composed of a ten-stage axial and a single-stage centrifugal compressor, would improve by 0.8 percent if the efficiency of the back stage centrifugal unit could be raised by 4 percent. It was expected that this would result in a noticeable improvement of the thermal gas turbine efficiency. The paper describes the aerodynamic design process used for the stage optimization, applying today’s advanced design tools for blade generation and three-dimensional aerodynamic calculation methods. Additionally, it describes the manufacturing procedure for the resulting three-dimensional blades and the experimental verification of the design approach.</abstract><cop>New York, NY</cop><pub>ASME</pub><doi>10.1115/1.1413476</doi><tpages>8</tpages></addata></record> |
| fulltext | fulltext |
| identifier | ISSN: 0889-504X |
| ispartof | Journal of turbomachinery, 2002-01, Vol.124 (1), p.19-26 |
| issn | 0889-504X 1528-8900 |
| language | eng |
| recordid | cdi_proquest_miscellaneous_27218103 |
| source | ASME Transactions Journals (Current) |
| subjects | Aerodynamics Applied fluid mechanics Applied sciences Continuous cycle engines: steam and gas turbines, jet engines Engines and turbines Exact sciences and technology Fluid dynamics Fundamental areas of phenomenology (including applications) Mechanical engineering. Machine design Physics Pump and compressors (turbocompressors, fans, etc.) |
| title | Improved Compressor Exit Diffuser for an Industrial Gas Turbine |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2024-12-24T17%3A55%3A03IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-proquest_cross&rft_val_fmt=info:ofi/fmt:kev:mtx:journal&rft.genre=article&rft.atitle=Improved%20Compressor%20Exit%20Diffuser%20for%20an%20Industrial%20Gas%20Turbine&rft.jtitle=Journal%20of%20turbomachinery&rft.au=Orth,%20U&rft.date=2002-01-01&rft.volume=124&rft.issue=1&rft.spage=19&rft.epage=26&rft.pages=19-26&rft.issn=0889-504X&rft.eissn=1528-8900&rft.coden=JOTUEI&rft_id=info:doi/10.1115/1.1413476&rft_dat=%3Cproquest_cross%3E27218103%3C/proquest_cross%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_pqid=27218103&rft_id=info:pmid/&rfr_iscdi=true |