Shower Head and Trailing Edge Cooling Influence on Transonic Vane Aero PerformanceSource: Journal of Turbomachinery:;2014:;volume( 136 ):;issue: 011::page 111001Author:Saha, Ranjan
,
Fridh, Jens
,
Fransson, Torsten H.
,
Mamaev, Boris I.
,
Annerfeldt, Mats
,
Utriainen, Esa
DOI: 10.1115/1.4028024Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: An experimental investigation on a cooled nozzle guide vane (NGV) has been conducted in an annular sector to quantify aerodynamic influences of shower head (SH) and trailing edge (TE) cooling. The investigated vane is a typical high pressure gas turbine vane, geometrically similar to a real engine component, operated at a reference exit Mach number of 0.89. The investigations have been performed for various coolanttomainstream mass–flux ratios. New loss equations are derived and implemented regarding coolant aerodynamic losses. Results lead to a conclusion that both TE cooling and SH film cooling increase the aerodynamic loss compared to an uncooled case. In addition, the TE cooling has higher aerodynamic loss compared to the SH cooling. Secondary losses decrease with inserting SH film cooling compared to the uncooled case. The TE cooling appears to have less impact on the secondary loss compared to the SH cooling. Areaaveraged exit flow angles around midspan increase for the TE cooling.
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| contributor author | Saha, Ranjan | |
| contributor author | Fridh, Jens | |
| contributor author | Fransson, Torsten H. | |
| contributor author | Mamaev, Boris I. | |
| contributor author | Annerfeldt, Mats | |
| contributor author | Utriainen, Esa | |
| date accessioned | 2017-05-09T01:13:51Z | |
| date available | 2017-05-09T01:13:51Z | |
| date issued | 2014 | |
| identifier issn | 0889-504X | |
| identifier other | turbo_136_11_111001.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/156676 | |
| description abstract | An experimental investigation on a cooled nozzle guide vane (NGV) has been conducted in an annular sector to quantify aerodynamic influences of shower head (SH) and trailing edge (TE) cooling. The investigated vane is a typical high pressure gas turbine vane, geometrically similar to a real engine component, operated at a reference exit Mach number of 0.89. The investigations have been performed for various coolanttomainstream mass–flux ratios. New loss equations are derived and implemented regarding coolant aerodynamic losses. Results lead to a conclusion that both TE cooling and SH film cooling increase the aerodynamic loss compared to an uncooled case. In addition, the TE cooling has higher aerodynamic loss compared to the SH cooling. Secondary losses decrease with inserting SH film cooling compared to the uncooled case. The TE cooling appears to have less impact on the secondary loss compared to the SH cooling. Areaaveraged exit flow angles around midspan increase for the TE cooling. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Shower Head and Trailing Edge Cooling Influence on Transonic Vane Aero Performance | |
| type | Journal Paper | |
| journal volume | 136 | |
| journal issue | 11 | |
| journal title | Journal of Turbomachinery | |
| identifier doi | 10.1115/1.4028024 | |
| journal fristpage | 111001 | |
| journal lastpage | 111001 | |
| identifier eissn | 1528-8900 | |
| tree | Journal of Turbomachinery:;2014:;volume( 136 ):;issue: 011 | |
| contenttype | Fulltext |