The effectiveness of jet impingement cooling system on the pressure side of the turbine blade RR trent 970-B84
Not available
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| Other Authors: | |
| Format: | Bachelor thesis |
| Language: | English |
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Universiti Teknologi Malaysia
2025
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| Online Access: | https://utmik.utm.my/handle/123456789/42998 |
| Abstract | Abstract here |
| _version_ | 1854975095662968832 |
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| author | Nur Farah Hanis Kamalulzaman |
| author2 | Mohamad Nor Musa, supervisor |
| author_facet | Mohamad Nor Musa, supervisor Nur Farah Hanis Kamalulzaman |
| author_sort | Nur Farah Hanis Kamalulzaman |
| description | Not available |
| format | Bachelor thesis |
| id | utm-123456789-42998 |
| institution | Universiti Teknologi Malaysia |
| language | English |
| publishDate | 2025 |
| publisher | Universiti Teknologi Malaysia |
| record_format | dspace |
| record_pdf | Abstract |
| spelling | utm-123456789-429982025-08-21T08:02:20Z The effectiveness of jet impingement cooling system on the pressure side of the turbine blade RR trent 970-B84 Nur Farah Hanis Kamalulzaman Mohamad Nor Musa, supervisor Mechanical engineering Not available Gas turbine operates at high temperature within the range of 1300�C to 1600�C which could cause wear, failure and fatigue towards the turbine blades if the blades were exposed to this high temperature after certain period. Jet impingement cooling system is one of the methods used in turbine blade cooling due to its high heat transfer rate. This experimental study focuses on the effectiveness of the jet impingement cooling on the pressure side of the RR Trent 970-B84 turbine blade surface based on two parameters which are the nozzle to surface distance and velocity of air with respect to Reynolds number. Four different height to diameter ratio which is 5,10,15 and 20 were tested in this experiment using two different velocity 12.6 m/s and 6.4 m/s respectively. Similar diameter of nozzle was used for both velocity which is 4mm. This experimental study aims to replicate the real-life application by heating up the pressure side model and cool it down to understand the cooling behavior. The temperatures were recorded during heating and cooling process of the pressure side model. Based on the experimental result, the mass flow rate is higher as well as the Nusselt number when the velocity is higher. Aside from that, the highest Nusselt number obtained was at the stagnation point for both velocities. The optimum cooling effect at velocity 6.4 m/s was obtained when the height to diameter ratio is equal to 15 with Nusselt number of 86.0718.The optimum cooling effect for overall experiment was obtained when using velocity of 12.6 m/s at height to diameter ratio equal to 5 with Nusselt number of 149.0403. shafika UTM 66 p. Project Paper (Sarjana Muda Kejuruteraan (Mekanikal)) - Universiti Teknologi Malaysia, 2020 2025-03-11T05:24:24Z 2025-03-11T05:24:24Z 2020 Bachelor thesis https://utmik.utm.my/handle/123456789/42998 vital:148448 valet-20220619-14244 ENG Closed Access UTM Complete Unpublished Completion application/pdf Universiti Teknologi Malaysia |
| spellingShingle | Mechanical engineering Nur Farah Hanis Kamalulzaman The effectiveness of jet impingement cooling system on the pressure side of the turbine blade RR trent 970-B84 |
| thesis_level | Other |
| title | The effectiveness of jet impingement cooling system on the pressure side of the turbine blade RR trent 970-B84 |
| title_full | The effectiveness of jet impingement cooling system on the pressure side of the turbine blade RR trent 970-B84 |
| title_fullStr | The effectiveness of jet impingement cooling system on the pressure side of the turbine blade RR trent 970-B84 |
| title_full_unstemmed | The effectiveness of jet impingement cooling system on the pressure side of the turbine blade RR trent 970-B84 |
| title_short | The effectiveness of jet impingement cooling system on the pressure side of the turbine blade RR trent 970-B84 |
| title_sort | effectiveness of jet impingement cooling system on the pressure side of the turbine blade rr trent 970 b84 |
| topic | Mechanical engineering |
| url | https://utmik.utm.my/handle/123456789/42998 |
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