An experimental study validating the conditions necessary to prevent the formation and ingestion of aero-inlet vortices
The race to create aircraft engines that push the boundaries of efficiency leads to the creation of engines that are not only larger in size, but have lower ground clearances as well. Under certain flow conditions, a surface to inlet vortex may form. These vortices could potentially damage the engin...
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| Formaat: | Final Year Project (FYP) |
| Taal: | English |
| Gepubliceerd in: |
2014
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| Onderwerpen: | |
| Online toegang: | http://hdl.handle.net/10356/61570 |
| _version_ | 1826128235319001088 |
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| author | Omar Faruq Idris |
| author2 | School of Mechanical and Aerospace Engineering |
| author_facet | School of Mechanical and Aerospace Engineering Omar Faruq Idris |
| author_sort | Omar Faruq Idris |
| collection | NTU |
| description | The race to create aircraft engines that push the boundaries of efficiency leads to the creation of engines that are not only larger in size, but have lower ground clearances as well. Under certain flow conditions, a surface to inlet vortex may form. These vortices could potentially damage the engine through increased instability, wear and even compressor stall. However, the most damaging effect is the ingestion of foreign objects that are lifted by these vortices.
These vortices form only under certain conditions. Studies conducted in the past have revealed the existence of three vortex regions separated by two threshold lines. In order to verify the results obtained through running computational fluid dynamic (CFD) simulations, a physical experimental set up has been designed. A scaled model nacelle was placed in a water tunnel, with the ability to vary the parameters such as ground clearance and velocity ratio. Results obtained through video recordings have been processed, analyzed and a plot of Vi/Vo against H/D yielded a graph of three distinct vortex formation regions; no vortex, unsteady vortex and steady vortex.
The experimental results for the headwind configuration showed that at lower Reynolds number, the vortex threshold line was lowered, thereby supporting the trend proposed by Ho and Jermy, where the Reynolds number affects the vortex formation threshold. The experiment gave further insight into the vortex formation mechanism, where the direction of spin of a vortex formed could be due the location of the vortex with respect to the engine inlet. |
| first_indexed | 2024-10-01T07:21:37Z |
| format | Final Year Project (FYP) |
| id | ntu-10356/61570 |
| institution | Nanyang Technological University |
| language | English |
| last_indexed | 2024-10-01T07:21:37Z |
| publishDate | 2014 |
| record_format | dspace |
| spelling | ntu-10356/615702023-03-04T19:35:25Z An experimental study validating the conditions necessary to prevent the formation and ingestion of aero-inlet vortices Omar Faruq Idris School of Mechanical and Aerospace Engineering New Tze Hao Daniel DRNTU::Engineering::Aeronautical engineering::Aerodynamics DRNTU::Engineering::Aeronautical engineering::Aircraft motors and engines The race to create aircraft engines that push the boundaries of efficiency leads to the creation of engines that are not only larger in size, but have lower ground clearances as well. Under certain flow conditions, a surface to inlet vortex may form. These vortices could potentially damage the engine through increased instability, wear and even compressor stall. However, the most damaging effect is the ingestion of foreign objects that are lifted by these vortices. These vortices form only under certain conditions. Studies conducted in the past have revealed the existence of three vortex regions separated by two threshold lines. In order to verify the results obtained through running computational fluid dynamic (CFD) simulations, a physical experimental set up has been designed. A scaled model nacelle was placed in a water tunnel, with the ability to vary the parameters such as ground clearance and velocity ratio. Results obtained through video recordings have been processed, analyzed and a plot of Vi/Vo against H/D yielded a graph of three distinct vortex formation regions; no vortex, unsteady vortex and steady vortex. The experimental results for the headwind configuration showed that at lower Reynolds number, the vortex threshold line was lowered, thereby supporting the trend proposed by Ho and Jermy, where the Reynolds number affects the vortex formation threshold. The experiment gave further insight into the vortex formation mechanism, where the direction of spin of a vortex formed could be due the location of the vortex with respect to the engine inlet. Bachelor of Engineering (Aerospace Engineering) 2014-06-12T04:53:39Z 2014-06-12T04:53:39Z 2014 2014 Final Year Project (FYP) http://hdl.handle.net/10356/61570 en Nanyang Technological University 78 p. application/pdf |
| spellingShingle | DRNTU::Engineering::Aeronautical engineering::Aerodynamics DRNTU::Engineering::Aeronautical engineering::Aircraft motors and engines Omar Faruq Idris An experimental study validating the conditions necessary to prevent the formation and ingestion of aero-inlet vortices |
| title | An experimental study validating the conditions necessary to prevent the formation and ingestion of aero-inlet vortices |
| title_full | An experimental study validating the conditions necessary to prevent the formation and ingestion of aero-inlet vortices |
| title_fullStr | An experimental study validating the conditions necessary to prevent the formation and ingestion of aero-inlet vortices |
| title_full_unstemmed | An experimental study validating the conditions necessary to prevent the formation and ingestion of aero-inlet vortices |
| title_short | An experimental study validating the conditions necessary to prevent the formation and ingestion of aero-inlet vortices |
| title_sort | experimental study validating the conditions necessary to prevent the formation and ingestion of aero inlet vortices |
| topic | DRNTU::Engineering::Aeronautical engineering::Aerodynamics DRNTU::Engineering::Aeronautical engineering::Aircraft motors and engines |
| url | http://hdl.handle.net/10356/61570 |
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