Interpreting Aerodynamics of a Transonic Impeller from Static Pressure Measurements
This paper investigates the aerodynamics of a transonic impeller using static pressure measurements. The impeller is a high-speed, high-pressure-ratio wheel used in small gas turbine engines. The experiment was conducted on the single stage centrifugal compressor facility in the compressor research...
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| Format: | Article |
| Language: | English |
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Wiley
2018-01-01
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| Series: | International Journal of Rotating Machinery |
| Online Access: | http://dx.doi.org/10.1155/2018/7281691 |
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| _version_ | 1832552437707177984 |
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| author | Fangyuan Lou John Charles Fabian Nicole Leanne Key |
| author_facet | Fangyuan Lou John Charles Fabian Nicole Leanne Key |
| author_sort | Fangyuan Lou |
| collection | DOAJ |
| description | This paper investigates the aerodynamics of a transonic impeller using static pressure measurements. The impeller is a high-speed, high-pressure-ratio wheel used in small gas turbine engines. The experiment was conducted on the single stage centrifugal compressor facility in the compressor research laboratory at Purdue University. Data were acquired from choke to near-surge at four different corrected speeds (Nc) from 80% to 100% design speed, which covers both subsonic and supersonic inlet conditions. Details of the impeller flow field are discussed using data acquired from both steady and time-resolved static pressure measurements along the impeller shroud. The flow field is compared at different loading conditions, from subsonic to supersonic inlet conditions. The impeller performance was strongly dependent on the inducer, where the majority of relative diffusion occurs. The inducer diffuses flow more efficiently for inlet tip relative Mach numbers close to unity, and the performance diminishes at other Mach numbers. Shock waves emerging upstream of the impeller leading edge were observed from 90% to 100% corrected speed, and they move towards the impeller trailing edge as the inlet tip relative Mach number increases. There is no shock wave present in the inducer at 80% corrected speed. However, a high-loss region near the inducer throat was observed at 80% corrected speed resulting in a lower impeller efficiency at subsonic inlet conditions. |
| format | Article |
| id | doaj-art-68949c800a454ad7b3bea7a2ebd553ae |
| institution | Kabale University |
| issn | 1023-621X 1542-3034 |
| language | English |
| publishDate | 2018-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Rotating Machinery |
| spelling | doaj-art-68949c800a454ad7b3bea7a2ebd553ae2025-02-03T05:58:37ZengWileyInternational Journal of Rotating Machinery1023-621X1542-30342018-01-01201810.1155/2018/72816917281691Interpreting Aerodynamics of a Transonic Impeller from Static Pressure MeasurementsFangyuan Lou0John Charles Fabian1Nicole Leanne Key2Purdue University, West Lafayette, IN 47907, USAPurdue University, West Lafayette, IN 47907, USAPurdue University, West Lafayette, IN 47907, USAThis paper investigates the aerodynamics of a transonic impeller using static pressure measurements. The impeller is a high-speed, high-pressure-ratio wheel used in small gas turbine engines. The experiment was conducted on the single stage centrifugal compressor facility in the compressor research laboratory at Purdue University. Data were acquired from choke to near-surge at four different corrected speeds (Nc) from 80% to 100% design speed, which covers both subsonic and supersonic inlet conditions. Details of the impeller flow field are discussed using data acquired from both steady and time-resolved static pressure measurements along the impeller shroud. The flow field is compared at different loading conditions, from subsonic to supersonic inlet conditions. The impeller performance was strongly dependent on the inducer, where the majority of relative diffusion occurs. The inducer diffuses flow more efficiently for inlet tip relative Mach numbers close to unity, and the performance diminishes at other Mach numbers. Shock waves emerging upstream of the impeller leading edge were observed from 90% to 100% corrected speed, and they move towards the impeller trailing edge as the inlet tip relative Mach number increases. There is no shock wave present in the inducer at 80% corrected speed. However, a high-loss region near the inducer throat was observed at 80% corrected speed resulting in a lower impeller efficiency at subsonic inlet conditions.http://dx.doi.org/10.1155/2018/7281691 |
| spellingShingle | Fangyuan Lou John Charles Fabian Nicole Leanne Key Interpreting Aerodynamics of a Transonic Impeller from Static Pressure Measurements International Journal of Rotating Machinery |
| title | Interpreting Aerodynamics of a Transonic Impeller from Static Pressure Measurements |
| title_full | Interpreting Aerodynamics of a Transonic Impeller from Static Pressure Measurements |
| title_fullStr | Interpreting Aerodynamics of a Transonic Impeller from Static Pressure Measurements |
| title_full_unstemmed | Interpreting Aerodynamics of a Transonic Impeller from Static Pressure Measurements |
| title_short | Interpreting Aerodynamics of a Transonic Impeller from Static Pressure Measurements |
| title_sort | interpreting aerodynamics of a transonic impeller from static pressure measurements |
| url | http://dx.doi.org/10.1155/2018/7281691 |
| work_keys_str_mv | AT fangyuanlou interpretingaerodynamicsofatransonicimpellerfromstaticpressuremeasurements AT johncharlesfabian interpretingaerodynamicsofatransonicimpellerfromstaticpressuremeasurements AT nicoleleannekey interpretingaerodynamicsofatransonicimpellerfromstaticpressuremeasurements |