Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine

Abstract Good effect from using rotor blade cascades, the pressure side’s profile of which has a bend near the trailing edge at an angle of no larger than 15°, is confirmed from the results of experimental studies.

Gespeichert in:

Autor*in:	Mamaev, B. I. [verfasserIn] Valeev, M. R.

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2010

Schlagwörter:	Suction Side Pressure Side Profile Loss Aerodynamic Efficiency Stage Efficiency

Anmerkung:	© Pleiades Publishing, Ltd. 2010

Übergeordnetes Werk:	Enthalten in: Thermal engineering - Berlin : Springer Science + Business Media, 1996, 57(2010), 9 vom: Sept., Seite 786-789
Übergeordnetes Werk:	volume:57 ; year:2010 ; number:9 ; month:09 ; pages:786-789

Links:	Volltext

DOI / URN:	10.1134/S0040601510090107

Katalog-ID:	SPR020447787

Internformat


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912			\|a GBV_ILN_2026
912			\|a GBV_ILN_2027
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912			\|a GBV_ILN_2039
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912			\|a GBV_ILN_2049
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publishDate	2010
allfields	10.1134/S0040601510090107 doi (DE-627)SPR020447787 (SPR)S0040601510090107-e DE-627 ger DE-627 rakwb eng Mamaev, B. I. verfasserin aut Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine 2010 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Pleiades Publishing, Ltd. 2010 Abstract Good effect from using rotor blade cascades, the pressure side’s profile of which has a bend near the trailing edge at an angle of no larger than 15°, is confirmed from the results of experimental studies. Suction Side (dpeaa)DE-He213 Pressure Side (dpeaa)DE-He213 Profile Loss (dpeaa)DE-He213 Aerodynamic Efficiency (dpeaa)DE-He213 Stage Efficiency (dpeaa)DE-He213 Valeev, M. R. aut Enthalten in Thermal engineering Berlin : Springer Science + Business Media, 1996 57(2010), 9 vom: Sept., Seite 786-789 (DE-627)37627459X (DE-600)2130271-6 1555-6301 nnns volume:57 year:2010 number:9 month:09 pages:786-789 https://dx.doi.org/10.1134/S0040601510090107 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4012 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 57 2010 9 09 786-789
spelling	10.1134/S0040601510090107 doi (DE-627)SPR020447787 (SPR)S0040601510090107-e DE-627 ger DE-627 rakwb eng Mamaev, B. I. verfasserin aut Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine 2010 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Pleiades Publishing, Ltd. 2010 Abstract Good effect from using rotor blade cascades, the pressure side’s profile of which has a bend near the trailing edge at an angle of no larger than 15°, is confirmed from the results of experimental studies. Suction Side (dpeaa)DE-He213 Pressure Side (dpeaa)DE-He213 Profile Loss (dpeaa)DE-He213 Aerodynamic Efficiency (dpeaa)DE-He213 Stage Efficiency (dpeaa)DE-He213 Valeev, M. R. aut Enthalten in Thermal engineering Berlin : Springer Science + Business Media, 1996 57(2010), 9 vom: Sept., Seite 786-789 (DE-627)37627459X (DE-600)2130271-6 1555-6301 nnns volume:57 year:2010 number:9 month:09 pages:786-789 https://dx.doi.org/10.1134/S0040601510090107 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4012 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 57 2010 9 09 786-789
allfields_unstemmed	10.1134/S0040601510090107 doi (DE-627)SPR020447787 (SPR)S0040601510090107-e DE-627 ger DE-627 rakwb eng Mamaev, B. I. verfasserin aut Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine 2010 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Pleiades Publishing, Ltd. 2010 Abstract Good effect from using rotor blade cascades, the pressure side’s profile of which has a bend near the trailing edge at an angle of no larger than 15°, is confirmed from the results of experimental studies. Suction Side (dpeaa)DE-He213 Pressure Side (dpeaa)DE-He213 Profile Loss (dpeaa)DE-He213 Aerodynamic Efficiency (dpeaa)DE-He213 Stage Efficiency (dpeaa)DE-He213 Valeev, M. R. aut Enthalten in Thermal engineering Berlin : Springer Science + Business Media, 1996 57(2010), 9 vom: Sept., Seite 786-789 (DE-627)37627459X (DE-600)2130271-6 1555-6301 nnns volume:57 year:2010 number:9 month:09 pages:786-789 https://dx.doi.org/10.1134/S0040601510090107 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4012 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 57 2010 9 09 786-789
allfieldsGer	10.1134/S0040601510090107 doi (DE-627)SPR020447787 (SPR)S0040601510090107-e DE-627 ger DE-627 rakwb eng Mamaev, B. I. verfasserin aut Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine 2010 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Pleiades Publishing, Ltd. 2010 Abstract Good effect from using rotor blade cascades, the pressure side’s profile of which has a bend near the trailing edge at an angle of no larger than 15°, is confirmed from the results of experimental studies. Suction Side (dpeaa)DE-He213 Pressure Side (dpeaa)DE-He213 Profile Loss (dpeaa)DE-He213 Aerodynamic Efficiency (dpeaa)DE-He213 Stage Efficiency (dpeaa)DE-He213 Valeev, M. R. aut Enthalten in Thermal engineering Berlin : Springer Science + Business Media, 1996 57(2010), 9 vom: Sept., Seite 786-789 (DE-627)37627459X (DE-600)2130271-6 1555-6301 nnns volume:57 year:2010 number:9 month:09 pages:786-789 https://dx.doi.org/10.1134/S0040601510090107 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4012 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 57 2010 9 09 786-789
allfieldsSound	10.1134/S0040601510090107 doi (DE-627)SPR020447787 (SPR)S0040601510090107-e DE-627 ger DE-627 rakwb eng Mamaev, B. I. verfasserin aut Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine 2010 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Pleiades Publishing, Ltd. 2010 Abstract Good effect from using rotor blade cascades, the pressure side’s profile of which has a bend near the trailing edge at an angle of no larger than 15°, is confirmed from the results of experimental studies. Suction Side (dpeaa)DE-He213 Pressure Side (dpeaa)DE-He213 Profile Loss (dpeaa)DE-He213 Aerodynamic Efficiency (dpeaa)DE-He213 Stage Efficiency (dpeaa)DE-He213 Valeev, M. R. aut Enthalten in Thermal engineering Berlin : Springer Science + Business Media, 1996 57(2010), 9 vom: Sept., Seite 786-789 (DE-627)37627459X (DE-600)2130271-6 1555-6301 nnns volume:57 year:2010 number:9 month:09 pages:786-789 https://dx.doi.org/10.1134/S0040601510090107 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4012 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 57 2010 9 09 786-789
language	English
source	Enthalten in Thermal engineering 57(2010), 9 vom: Sept., Seite 786-789 volume:57 year:2010 number:9 month:09 pages:786-789
sourceStr	Enthalten in Thermal engineering 57(2010), 9 vom: Sept., Seite 786-789 volume:57 year:2010 number:9 month:09 pages:786-789
format_phy_str_mv	Article
institution	findex.gbv.de
topic_facet	Suction Side Pressure Side Profile Loss Aerodynamic Efficiency Stage Efficiency
isfreeaccess_bool	false
container_title	Thermal engineering
authorswithroles_txt_mv	Mamaev, B. I. @@aut@@ Valeev, M. R. @@aut@@
publishDateDaySort_date	2010-09-01T00:00:00Z
hierarchy_top_id	37627459X
id	SPR020447787
language_de	englisch
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author	Mamaev, B. I.
spellingShingle	Mamaev, B. I. misc Suction Side misc Pressure Side misc Profile Loss misc Aerodynamic Efficiency misc Stage Efficiency Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine
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topic_title	Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine Suction Side (dpeaa)DE-He213 Pressure Side (dpeaa)DE-He213 Profile Loss (dpeaa)DE-He213 Aerodynamic Efficiency (dpeaa)DE-He213 Stage Efficiency (dpeaa)DE-He213
topic	misc Suction Side misc Pressure Side misc Profile Loss misc Aerodynamic Efficiency misc Stage Efficiency
topic_unstemmed	misc Suction Side misc Pressure Side misc Profile Loss misc Aerodynamic Efficiency misc Stage Efficiency
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title	Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine
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title_full	Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine
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author_browse	Mamaev, B. I. Valeev, M. R.
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author-letter	Mamaev, B. I.
doi_str_mv	10.1134/S0040601510090107
title_sort	improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine
title_auth	Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine
abstract	Abstract Good effect from using rotor blade cascades, the pressure side’s profile of which has a bend near the trailing edge at an angle of no larger than 15°, is confirmed from the results of experimental studies. © Pleiades Publishing, Ltd. 2010
abstractGer	Abstract Good effect from using rotor blade cascades, the pressure side’s profile of which has a bend near the trailing edge at an angle of no larger than 15°, is confirmed from the results of experimental studies. © Pleiades Publishing, Ltd. 2010
abstract_unstemmed	Abstract Good effect from using rotor blade cascades, the pressure side’s profile of which has a bend near the trailing edge at an angle of no larger than 15°, is confirmed from the results of experimental studies. © Pleiades Publishing, Ltd. 2010
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title_short	Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine
url	https://dx.doi.org/10.1134/S0040601510090107
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author2	Valeev, M. R.
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up_date	2024-07-03T16:06:35.963Z
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Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine

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