Plasma Assisted Re-Ignition of Aeroengines under High Altitude Conditions
Re-ignition of aeroengines under high altitude conditions is of great importance to the safety and use of lean-burn flame. This study is focused on the experimental and numerical characterization of flow dynamics and flame re-ignition in a rectangular burner. A ring-needle type plasma actuator was c...
| Main Authors: | , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2022-01-01
|
| Series: | Aerospace |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2226-4310/9/2/66 |
| _version_ | 1797483914647830528 |
|---|---|
| author | Ghazanfar Mehdi Sara Bonuso Maria Grazia De Giorgi |
| author_facet | Ghazanfar Mehdi Sara Bonuso Maria Grazia De Giorgi |
| author_sort | Ghazanfar Mehdi |
| collection | DOAJ |
| description | Re-ignition of aeroengines under high altitude conditions is of great importance to the safety and use of lean-burn flame. This study is focused on the experimental and numerical characterization of flow dynamics and flame re-ignition in a rectangular burner. A ring-needle type plasma actuator was considered and run by high-voltage (HV) nanopulsed plasma generator. The electrical power delivered to the fluid and an optimal value of reduced electric field (E<sub>N</sub>) was calculated considering non-reactive flow. Smoke flow visualizations using a high-speed camera and proper orthogonal decomposition (POD) were performed to recognize the most dominant flow structures. Experimental results revealed the transport effects due to plasma discharge, such as the induced flow, that could have a strong impact on the recirculation zone near the corners of combustor, improving the mixing performance and reducing the ignition delay time. Two different numerical tools (ZDPlasKin and Chemkin) were used to investigate the ignition characteristics. ZDPlasKin calculated the thermal effect and the plasma kinetic of nanopulsed plasma discharge at the experimentally measured E<sub>N</sub>. Finally, based on the output of ZDPlasKin, Chemkin estimated the flame ignition at low pressure and low temperature conditions. It was noticed that time required to achieve the maximum flame temperature with plasma actuation is significantly less than the auto-ignition time (‘clean case’, simulation result of the model without considering the plasma effect). Maximum reduction in ignition time was observed at inlet pressure 1 bar (3.5 × 10<sup>−5</sup> s) with respect to the clean case (1.1 × 10<sup>−3</sup> s). However, as the inlet pressure is reduced, the ignition delay time was increased. At 0.6 bar flame ignition occurred in clean case at 0.0048 s and at 0.0022 s in presence of the plasma actuation, a further decrease of the pressure up to 0.4 bar leads the ignition at 0.0027 s and 0.0063 s in clean and plasma actuation, respectively. |
| first_indexed | 2024-03-09T22:53:50Z |
| format | Article |
| id | doaj.art-0350f834c4a945beb5f481f5cee05891 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T22:53:50Z |
| publishDate | 2022-01-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-0350f834c4a945beb5f481f5cee058912023-11-23T18:14:07ZengMDPI AGAerospace2226-43102022-01-01926610.3390/aerospace9020066Plasma Assisted Re-Ignition of Aeroengines under High Altitude ConditionsGhazanfar Mehdi0Sara Bonuso1Maria Grazia De Giorgi2Department of Engineering for Innovation, University of Salento, Via per Monteroni, 73100 Lecce, ItalyDepartment of Engineering for Innovation, University of Salento, Via per Monteroni, 73100 Lecce, ItalyDepartment of Engineering for Innovation, University of Salento, Via per Monteroni, 73100 Lecce, ItalyRe-ignition of aeroengines under high altitude conditions is of great importance to the safety and use of lean-burn flame. This study is focused on the experimental and numerical characterization of flow dynamics and flame re-ignition in a rectangular burner. A ring-needle type plasma actuator was considered and run by high-voltage (HV) nanopulsed plasma generator. The electrical power delivered to the fluid and an optimal value of reduced electric field (E<sub>N</sub>) was calculated considering non-reactive flow. Smoke flow visualizations using a high-speed camera and proper orthogonal decomposition (POD) were performed to recognize the most dominant flow structures. Experimental results revealed the transport effects due to plasma discharge, such as the induced flow, that could have a strong impact on the recirculation zone near the corners of combustor, improving the mixing performance and reducing the ignition delay time. Two different numerical tools (ZDPlasKin and Chemkin) were used to investigate the ignition characteristics. ZDPlasKin calculated the thermal effect and the plasma kinetic of nanopulsed plasma discharge at the experimentally measured E<sub>N</sub>. Finally, based on the output of ZDPlasKin, Chemkin estimated the flame ignition at low pressure and low temperature conditions. It was noticed that time required to achieve the maximum flame temperature with plasma actuation is significantly less than the auto-ignition time (‘clean case’, simulation result of the model without considering the plasma effect). Maximum reduction in ignition time was observed at inlet pressure 1 bar (3.5 × 10<sup>−5</sup> s) with respect to the clean case (1.1 × 10<sup>−3</sup> s). However, as the inlet pressure is reduced, the ignition delay time was increased. At 0.6 bar flame ignition occurred in clean case at 0.0048 s and at 0.0022 s in presence of the plasma actuation, a further decrease of the pressure up to 0.4 bar leads the ignition at 0.0027 s and 0.0063 s in clean and plasma actuation, respectively.https://www.mdpi.com/2226-4310/9/2/66plasma assisted ignitionflow structuresnanopulsed plasmaignition delay timelow temperaturelow pressure |
| spellingShingle | Ghazanfar Mehdi Sara Bonuso Maria Grazia De Giorgi Plasma Assisted Re-Ignition of Aeroengines under High Altitude Conditions Aerospace plasma assisted ignition flow structures nanopulsed plasma ignition delay time low temperature low pressure |
| title | Plasma Assisted Re-Ignition of Aeroengines under High Altitude Conditions |
| title_full | Plasma Assisted Re-Ignition of Aeroengines under High Altitude Conditions |
| title_fullStr | Plasma Assisted Re-Ignition of Aeroengines under High Altitude Conditions |
| title_full_unstemmed | Plasma Assisted Re-Ignition of Aeroengines under High Altitude Conditions |
| title_short | Plasma Assisted Re-Ignition of Aeroengines under High Altitude Conditions |
| title_sort | plasma assisted re ignition of aeroengines under high altitude conditions |
| topic | plasma assisted ignition flow structures nanopulsed plasma ignition delay time low temperature low pressure |
| url | https://www.mdpi.com/2226-4310/9/2/66 |
| work_keys_str_mv | AT ghazanfarmehdi plasmaassistedreignitionofaeroenginesunderhighaltitudeconditions AT sarabonuso plasmaassistedreignitionofaeroenginesunderhighaltitudeconditions AT mariagraziadegiorgi plasmaassistedreignitionofaeroenginesunderhighaltitudeconditions |