Gas Turbine Stator-Well Flow and Heat Transfer.
Lead Research Organisation:
University of Bath
Department Name: Mechanical Engineering
Abstract
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People |
ORCID iD |
| James Andrew Scobie (Primary Supervisor) | |
| James PARRY (Student) |
Studentship Projects
| Project Reference | Relationship | Related To | Start | End | Student Name |
|---|---|---|---|---|---|
| EP/R511833/1 | 30/09/2017 | 31/12/2022 | |||
| 2440303 | Studentship | EP/R511833/1 | 30/09/2020 | 29/09/2023 | James PARRY |
| Description | A new methodology for resolving temperatures in conjugate problems has been implemented into the opensource simulation software OpenFOAM. To achieve this, a new solver and conjugate boundary condition has been developed using C++ and implemented into OpenFOAM. This new method has been validated using experimental results from the University of Bath's Compressor Cavity rig. The software has demonstrated not only good agreement with the experimental results, but also validated the assumed temperatures in the fluid predicted by theoretical models that are unable to be captured by experiments. The model has demonstrated it is suitable to act as a predictive tool, able to predict results independently from experiments. |
| Exploitation Route | The coding methodology is implemented into the opensource software OpenFOAM, so will be available to anyone looking to use the software. The applications for the code are not solely limited to turbomachinery, but any scenario where heat transfer occurs, particularly those with highly rotational fluid flows. |
| Sectors | Aerospace Defence and Marine |
| Description | Next generation and future aero-engines will feature core compressors with smaller dimensions and higher overall pressure ratios. This is in order maximise efficiency within the system, requiring high Turbine Entry Temperatures, while making the engine weight as low as possible. Due to the high temperatures experienced in the high-pressure compressors and turbines, the rotating discs in the core can experience radial growth. This can be an issue for the blades attached to these discs, where the radial growth can risk contact with the stationary outer casing and lead to damage to the engine. Understanding the temperature distributions in the discs is vital for engine designers; with accurate predictions of the radial growth dictating the clearance margins needed for maximising efficiency of the engine. The methodology and code developed can be used as a predictive tool for estimating the temperature of both the air in the engine as well as the metal discs, capturing the conjugate heat transfer between the two. This is of interest in industry in the design of these future engines. |
| First Year Of Impact | 2022 |
| Sector | Aerospace, Defence and Marine,Energy |
| Impact Types | Economic |