Thesis
Aerothermal study of high-pressure turbine rotor tips and casing at engine representative conditions with high-speed rotation
- Abstract:
-
Modern aircraft engines operate at high turbine entry temperatures to increase the cycle efficiency. The combustors employ intricate cooling techniques, to survive such high temperatures, resulting in distorted temperature profiles at the combustor exit. Further, extensive platform cooling, upstream of the Nozzle Guide Vanes (NGVs), results in additional radial distortions in the stage inlet temperature profile. Consequently, a rotating High-Pressure (HP) turbine blade is subjected to high...
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Authors
Contributors
+ Chana, K
- Institution:
- University of Oxford
- Division:
- MPLS
- Department:
- Engineering Science
- Sub department:
- Engineering Science
- Role:
- Supervisor
+ Beard, P
- Role:
- Supervisor
+ Rolls-Royce
More from this funder
- Funder identifier:
- http://dx.doi.org/10.13039/501100000767
- Grant:
- Funded under Rolls Royce UTC agreement
- DOI:
- Type of award:
- DPhil
- Level of award:
- Doctoral
- Awarding institution:
- University of Oxford
- Language:
-
English
- Keywords:
- Subjects:
- Deposit date:
-
2023-07-30
Terms of use
- Copyright holder:
- Singh, D
- Copyright date:
- 2022
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