Numerical investigation of unsteady detonation waves in combustion chamber using Shchelkin spirals
: Pulse Detonation Engine (PDE) is considered to be a propulsive system of future air vehicles. The main objective is to minimizing the Deflagration to Detonation transition run-up distance and time by placing Shchelkin spiral with varying pitch length. Here we have considered blockage-area ratio i...
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| Format: | Article |
| Language: | English |
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Applied Science Innovations Private Limited
2016-09-01
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| Series: | Carbon: Science and Technology |
| Subjects: |
Shchelkin spiral geometry.
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| Online Access: | http://www.applied-science-innovations.com/cst-web-site/CST-8-3-2016/CST-200-8-3-2016-18-28.pdf |
| _version_ | 1811313523022626816 |
|---|---|
| author | Repaka Ramesh C T Dheeraj Kumar Singh Dr. Gurunadh Velidi |
| author_facet | Repaka Ramesh C T Dheeraj Kumar Singh Dr. Gurunadh Velidi |
| author_sort | Repaka Ramesh |
| collection | DOAJ |
| description | : Pulse Detonation Engine (PDE) is considered to be a propulsive system of future air vehicles. The main objective is to minimizing the Deflagration to Detonation transition run-up distance and time
by placing Shchelkin spiral with varying pitch length. Here we have considered blockage-area ratio is 0.5 as optimal value from review of previous studies. In the present study the detonation initiation and propagation is modeled numerically using commercial CFD codes GAMBIT and FLUENT. The unsteady and two-dimensional compressible Reynolds Averaged Navier-Stokes equation is used to simulate the model. Fuel-air mixture of Hydrogen-air is used for better efficiency of PDE. It is very simple straight tube with Shchelkin spirals, one of the methods which is used to initiate detonation is creation of high pressure and temperature chamber region with 0.5cm from closed end of tube where shock will generate and transition into low pressure and temperature region propagates towards end of the tube. Two different zones namely high and low pressure zones are used as interface in modeling and patching has been used to fill the zones with hydrogen and oxygen with different pressure and temperatures hence shock leads to propagate inside the combustion chamber. |
| first_indexed | 2024-04-13T10:55:19Z |
| format | Article |
| id | doaj.art-261382bd812e4d74988a8f55f3ee7f24 |
| institution | Directory Open Access Journal |
| issn | 0974-0546 0974-0546 |
| language | English |
| last_indexed | 2024-04-13T10:55:19Z |
| publishDate | 2016-09-01 |
| publisher | Applied Science Innovations Private Limited |
| record_format | Article |
| series | Carbon: Science and Technology |
| spelling | doaj.art-261382bd812e4d74988a8f55f3ee7f242022-12-22T02:49:32ZengApplied Science Innovations Private LimitedCarbon: Science and Technology0974-05460974-05462016-09-01831828Numerical investigation of unsteady detonation waves in combustion chamber using Shchelkin spiralsRepaka Ramesh 0 C T Dheeraj Kumar Singh1 Dr. Gurunadh Velidi 2M.Tech CFD, Aerospace Department, Upes, Dehradun, IndiaM.Tech CFD, Aerospace Department, Upes, Dehradun, India.Assistant Professor, Aerospace Department, Upes, Dehradun, India: Pulse Detonation Engine (PDE) is considered to be a propulsive system of future air vehicles. The main objective is to minimizing the Deflagration to Detonation transition run-up distance and time by placing Shchelkin spiral with varying pitch length. Here we have considered blockage-area ratio is 0.5 as optimal value from review of previous studies. In the present study the detonation initiation and propagation is modeled numerically using commercial CFD codes GAMBIT and FLUENT. The unsteady and two-dimensional compressible Reynolds Averaged Navier-Stokes equation is used to simulate the model. Fuel-air mixture of Hydrogen-air is used for better efficiency of PDE. It is very simple straight tube with Shchelkin spirals, one of the methods which is used to initiate detonation is creation of high pressure and temperature chamber region with 0.5cm from closed end of tube where shock will generate and transition into low pressure and temperature region propagates towards end of the tube. Two different zones namely high and low pressure zones are used as interface in modeling and patching has been used to fill the zones with hydrogen and oxygen with different pressure and temperatures hence shock leads to propagate inside the combustion chamber.http://www.applied-science-innovations.com/cst-web-site/CST-8-3-2016/CST-200-8-3-2016-18-28.pdfDeflagration-Detonation Transition (DDT)Shchelkin spiral geometry. ------------------------------------------------------------------------------------------------------------Shchelkin spiral geometry |
| spellingShingle | Repaka Ramesh C T Dheeraj Kumar Singh Dr. Gurunadh Velidi Numerical investigation of unsteady detonation waves in combustion chamber using Shchelkin spirals Carbon: Science and Technology Deflagration-Detonation Transition (DDT) Shchelkin spiral geometry. ------------------------------------------------------------------------------------------------------------ Shchelkin spiral geometry |
| title | Numerical investigation of unsteady detonation waves in combustion chamber using Shchelkin spirals |
| title_full | Numerical investigation of unsteady detonation waves in combustion chamber using Shchelkin spirals |
| title_fullStr | Numerical investigation of unsteady detonation waves in combustion chamber using Shchelkin spirals |
| title_full_unstemmed | Numerical investigation of unsteady detonation waves in combustion chamber using Shchelkin spirals |
| title_short | Numerical investigation of unsteady detonation waves in combustion chamber using Shchelkin spirals |
| title_sort | numerical investigation of unsteady detonation waves in combustion chamber using shchelkin spirals |
| topic | Deflagration-Detonation Transition (DDT) Shchelkin spiral geometry. ------------------------------------------------------------------------------------------------------------ Shchelkin spiral geometry |
| url | http://www.applied-science-innovations.com/cst-web-site/CST-8-3-2016/CST-200-8-3-2016-18-28.pdf |
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