Numerical Optimization of a Stall Margin Enhancing Recirculation Channel for an Axial Compressor
A proof of concept is provided by computational fluid dynamic simulations of a new recirculating type casing treatment. This treatment aims at extending the stable operating range of highly loaded axial compressors, so to improve the safety of sorties of high-speed, high-performance aircraft powered...
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| Format: | Article |
| Language: | English |
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MDPI AG
2019-05-01
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| Series: | Fluids |
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| Online Access: | https://www.mdpi.com/2311-5521/4/2/88 |
| _version_ | 1819001549138952192 |
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| author | Motoyuki Kawase Aldo Rona |
| author_facet | Motoyuki Kawase Aldo Rona |
| author_sort | Motoyuki Kawase |
| collection | DOAJ |
| description | A proof of concept is provided by computational fluid dynamic simulations of a new recirculating type casing treatment. This treatment aims at extending the stable operating range of highly loaded axial compressors, so to improve the safety of sorties of high-speed, high-performance aircraft powered by high specific thrust engines. This casing treatment, featuring an axisymmetric recirculation channel, is evaluated on the NASA rotor 37 test case by steady and unsteady Reynolds Averaged Navier Stokes (RANS) simulations, using the realizable <i>k</i>-ε model. Flow blockage at the recirculation channel outlet was mitigated by chamfering the exit of the recirculation channel inner wall. The channel axial location from the rotor blade tip leading edge was optimized parametrically over the range −4.6% to 47.6% of the rotor tip axial chord <inline-formula> <math display="inline"> <semantics> <mrow> <msub> <mi>c</mi> <mi>z</mi> </msub> </mrow> </semantics> </math> </inline-formula>. Locating the channel at 18.2% <inline-formula> <math display="inline"> <semantics> <mrow> <msub> <mi>c</mi> <mi>z</mi> </msub> </mrow> </semantics> </math> </inline-formula> provided the best stall margin gain of approximately 5.5% compared to the untreated rotor. No rotor adiabatic efficiency was lost by the application of this casing treatment. The investigation into the flow structure with the recirculating channel gave a good insight into how the new casing treatment generates this benefit. The combination of stall margin gain at no rotor adiabatic efficiency loss makes this design attractive for applications to high-speed gas turbine engines. |
| first_indexed | 2024-12-20T22:50:58Z |
| format | Article |
| id | doaj.art-a4b3b34bd0554617a6a161328e30b944 |
| institution | Directory Open Access Journal |
| issn | 2311-5521 |
| language | English |
| last_indexed | 2024-12-20T22:50:58Z |
| publishDate | 2019-05-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Fluids |
| spelling | doaj.art-a4b3b34bd0554617a6a161328e30b9442022-12-21T19:24:15ZengMDPI AGFluids2311-55212019-05-01428810.3390/fluids4020088fluids4020088Numerical Optimization of a Stall Margin Enhancing Recirculation Channel for an Axial CompressorMotoyuki Kawase0Aldo Rona1Japanese Acquisition Technology & Logistics Agency, Ministry of Defense, Tokyo 190-8533, JapanDepartment of Engineering, University of Leicester, Leicester LE1 7RH, UKA proof of concept is provided by computational fluid dynamic simulations of a new recirculating type casing treatment. This treatment aims at extending the stable operating range of highly loaded axial compressors, so to improve the safety of sorties of high-speed, high-performance aircraft powered by high specific thrust engines. This casing treatment, featuring an axisymmetric recirculation channel, is evaluated on the NASA rotor 37 test case by steady and unsteady Reynolds Averaged Navier Stokes (RANS) simulations, using the realizable <i>k</i>-ε model. Flow blockage at the recirculation channel outlet was mitigated by chamfering the exit of the recirculation channel inner wall. The channel axial location from the rotor blade tip leading edge was optimized parametrically over the range −4.6% to 47.6% of the rotor tip axial chord <inline-formula> <math display="inline"> <semantics> <mrow> <msub> <mi>c</mi> <mi>z</mi> </msub> </mrow> </semantics> </math> </inline-formula>. Locating the channel at 18.2% <inline-formula> <math display="inline"> <semantics> <mrow> <msub> <mi>c</mi> <mi>z</mi> </msub> </mrow> </semantics> </math> </inline-formula> provided the best stall margin gain of approximately 5.5% compared to the untreated rotor. No rotor adiabatic efficiency was lost by the application of this casing treatment. The investigation into the flow structure with the recirculating channel gave a good insight into how the new casing treatment generates this benefit. The combination of stall margin gain at no rotor adiabatic efficiency loss makes this design attractive for applications to high-speed gas turbine engines.https://www.mdpi.com/2311-5521/4/2/88computational fluid dynamicsaxial compressorstall inceptioncasing treatmentparameter optimization |
| spellingShingle | Motoyuki Kawase Aldo Rona Numerical Optimization of a Stall Margin Enhancing Recirculation Channel for an Axial Compressor Fluids computational fluid dynamics axial compressor stall inception casing treatment parameter optimization |
| title | Numerical Optimization of a Stall Margin Enhancing Recirculation Channel for an Axial Compressor |
| title_full | Numerical Optimization of a Stall Margin Enhancing Recirculation Channel for an Axial Compressor |
| title_fullStr | Numerical Optimization of a Stall Margin Enhancing Recirculation Channel for an Axial Compressor |
| title_full_unstemmed | Numerical Optimization of a Stall Margin Enhancing Recirculation Channel for an Axial Compressor |
| title_short | Numerical Optimization of a Stall Margin Enhancing Recirculation Channel for an Axial Compressor |
| title_sort | numerical optimization of a stall margin enhancing recirculation channel for an axial compressor |
| topic | computational fluid dynamics axial compressor stall inception casing treatment parameter optimization |
| url | https://www.mdpi.com/2311-5521/4/2/88 |
| work_keys_str_mv | AT motoyukikawase numericaloptimizationofastallmarginenhancingrecirculationchannelforanaxialcompressor AT aldorona numericaloptimizationofastallmarginenhancingrecirculationchannelforanaxialcompressor |