Gas Turbine Blade Damper Optimization Methodology
The friction damping concept is widely used to reduce resonance stresses in gas turbines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and n...
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| Veröffentlicht in: | Advances in Acoustics and Vibration 2012-01, Vol.2012 (2012), p.218-230 |
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| creator | Giridhar, R. K. Ramaiah, P. V. Krishnaiah, G. Barad, S. G. |
| description | The friction damping concept is widely used to reduce resonance stresses in gas turbines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. This paper presents a methodology that combines three essential phases of friction damping optimization in turbo-machinery. The first phase is to develop an analytical model of blade damper system. The second phase is experimentation and model tuning necessary for response studies while the third phase is evaluating damper performance. The reduced model of blade is developed corresponding to the mode under investigation incorporating the friction damper then the simulations were carried out to arrive at an optimum design point of the damper. Bench tests were carried out in two phases. Phase-1 deals with characterization of the blade dynamically and the phase-2 deals with finding optimal normal load at which the blade resonating response is minimal for a given excitation. The test results are discussed, and are corroborated with simulated results, are in good agreement. |
| doi_str_mv | 10.1155/2012/316761 |
| format | Article |
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K. ; Ramaiah, P. V. ; Krishnaiah, G. ; Barad, S. G.</creator><contributor>Soenarko, Benjamin</contributor><creatorcontrib>Giridhar, R. K. ; Ramaiah, P. V. ; Krishnaiah, G. ; Barad, S. G. ; Soenarko, Benjamin</creatorcontrib><description>The friction damping concept is widely used to reduce resonance stresses in gas turbines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. This paper presents a methodology that combines three essential phases of friction damping optimization in turbo-machinery. The first phase is to develop an analytical model of blade damper system. The second phase is experimentation and model tuning necessary for response studies while the third phase is evaluating damper performance. The reduced model of blade is developed corresponding to the mode under investigation incorporating the friction damper then the simulations were carried out to arrive at an optimum design point of the damper. Bench tests were carried out in two phases. Phase-1 deals with characterization of the blade dynamically and the phase-2 deals with finding optimal normal load at which the blade resonating response is minimal for a given excitation. 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This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.</rights><lds50>peer_reviewed</lds50><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-a457t-1eb126a1d63fb7c7e59d2eb2f6a1cbe056a5aa3d8001be7a3927d6fb3a2c2d303</citedby><cites>FETCH-LOGICAL-a457t-1eb126a1d63fb7c7e59d2eb2f6a1cbe056a5aa3d8001be7a3927d6fb3a2c2d303</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,776,780,27903,27904</link.rule.ids></links><search><contributor>Soenarko, Benjamin</contributor><creatorcontrib>Giridhar, R. K.</creatorcontrib><creatorcontrib>Ramaiah, P. V.</creatorcontrib><creatorcontrib>Krishnaiah, G.</creatorcontrib><creatorcontrib>Barad, S. 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The reduced model of blade is developed corresponding to the mode under investigation incorporating the friction damper then the simulations were carried out to arrive at an optimum design point of the damper. Bench tests were carried out in two phases. Phase-1 deals with characterization of the blade dynamically and the phase-2 deals with finding optimal normal load at which the blade resonating response is minimal for a given excitation. The test results are discussed, and are corroborated with simulated results, are in good agreement.</description><subject>Blades</subject><subject>Dampers</subject><subject>Damping</subject><subject>Excitation</subject><subject>Friction</subject><subject>Load</subject><subject>Mathematical models</subject><subject>Methodology</subject><subject>Optimization</subject><subject>Phases</subject><subject>Studies</subject><issn>1687-6261</issn><issn>1687-627X</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2012</creationdate><recordtype>article</recordtype><sourceid>RHX</sourceid><sourceid>ABUWG</sourceid><sourceid>AFKRA</sourceid><sourceid>AZQEC</sourceid><sourceid>BENPR</sourceid><sourceid>CCPQU</sourceid><sourceid>DWQXO</sourceid><recordid>eNqFkEFLw0AQRoMoWKsnz0LAiyi1O7PJbnLUqlWo1EMFb2GSbOyWNIm7KVJ_vVsjFXrxNLszj4-P53mnwK4BwnCIDHDIQUgBe14PRCQHAuXb_vYt4NA7snbBmABkcc-DMVl_tjKprpR_W1Ku_DtaNsr406bVS_1Fra4r_1m18zqvy_p9fewdFFRadfI7-97rw_1s9DiYTMdPo5vJgIJQtgNQKaAgyAUvUplJFcY5qhQLt8tSxUJBIRHPI8YgVZJ4jDIXRcoJM8w5433vosttTP2xUrZNltpmqiypUvXKJsA4cBYwBIee76CLemUq185RrkUsWBA76qqjMlNba1SRNEYvyawdlGz0JRt9SafP0ZcdPddVTp_6H_isg5VDVEFbOBAYY-Tuk-5O2uhW_9V7cSkhkyCchZ9El-lGxBDRreTOB6IEnZpvgieLFw</recordid><startdate>20120101</startdate><enddate>20120101</enddate><creator>Giridhar, R. 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| source | Wiley Online Library Open Access; Alma/SFX Local Collection; EZB Electronic Journals Library |
| subjects | Blades Dampers Damping Excitation Friction Load Mathematical models Methodology Optimization Phases Studies |
| title | Gas Turbine Blade Damper Optimization Methodology |
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