Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines
The turbine tip geometry can significantly alter the performance of the turbine stage; its design represents a challenge for a variety of reasons. Multiple disciplines are involved in its design and their requirements limit the creativity of the designer. Multi-Disciplinary Design Optimisation (MDO)...
| Main Authors: | , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2018-11-01
|
| Series: | Aerospace |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2226-4310/5/4/116 |
| _version_ | 1819054289653334016 |
|---|---|
| author | Stefano Caloni Shahrokh Shahpar Vassili V. Toropov |
| author_facet | Stefano Caloni Shahrokh Shahpar Vassili V. Toropov |
| author_sort | Stefano Caloni |
| collection | DOAJ |
| description | The turbine tip geometry can significantly alter the performance of the turbine stage; its design represents a challenge for a variety of reasons. Multiple disciplines are involved in its design and their requirements limit the creativity of the designer. Multi-Disciplinary Design Optimisation (MDO) offers the capability to improve the performance whilst satisfying all the design constraints. This paper presents a novel design of a turbine tip achieved via MDO techniques. A fully parametrised Computer-Aided Design (CAD) model of the turbine rotor is used to create the squealer geometry and to control the location of the cooling and dust holes. A Conjugate Heat Transfer Computational Fluid Dynamics (CFD) analysis is performed for evaluating the aerothermal performance of the component and the temperature the turbine operates at. A Finite Element (FE) analysis is then performed to find the stress level that the turbine has to withstand. A bi-objective optimisation reduces simultaneously the aerodynamic loss and the stress level. The Multipoint Approximation Method (MAM) recently enhanced for multi-objective problems is chosen to solve this optimisation problem. The paper presents its logic in detail. The novel geometry offers a significant improvement in the aerodynamic performance whilst reducing the maximum stress. The flow associated with the new geometry is analysed in detail to understand the source of the improvement. |
| first_indexed | 2024-12-21T12:49:16Z |
| format | Article |
| id | doaj.art-2543041592f044e9a559ca79af2afc27 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-12-21T12:49:16Z |
| publishDate | 2018-11-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-2543041592f044e9a559ca79af2afc272022-12-21T19:03:31ZengMDPI AGAerospace2226-43102018-11-015411610.3390/aerospace5040116aerospace5040116Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure TurbinesStefano Caloni0Shahrokh Shahpar1Vassili V. Toropov2CFD Methods, Rolls-Royce plc; PO Box31, Derby DE248BJ, UKCFD Methods, Rolls-Royce plc; PO Box31, Derby DE248BJ, UKSchool of Engineering and Materials Science, Queen Mary University of London, Mile End Road, London E14NS, UKThe turbine tip geometry can significantly alter the performance of the turbine stage; its design represents a challenge for a variety of reasons. Multiple disciplines are involved in its design and their requirements limit the creativity of the designer. Multi-Disciplinary Design Optimisation (MDO) offers the capability to improve the performance whilst satisfying all the design constraints. This paper presents a novel design of a turbine tip achieved via MDO techniques. A fully parametrised Computer-Aided Design (CAD) model of the turbine rotor is used to create the squealer geometry and to control the location of the cooling and dust holes. A Conjugate Heat Transfer Computational Fluid Dynamics (CFD) analysis is performed for evaluating the aerothermal performance of the component and the temperature the turbine operates at. A Finite Element (FE) analysis is then performed to find the stress level that the turbine has to withstand. A bi-objective optimisation reduces simultaneously the aerodynamic loss and the stress level. The Multipoint Approximation Method (MAM) recently enhanced for multi-objective problems is chosen to solve this optimisation problem. The paper presents its logic in detail. The novel geometry offers a significant improvement in the aerodynamic performance whilst reducing the maximum stress. The flow associated with the new geometry is analysed in detail to understand the source of the improvement.https://www.mdpi.com/2226-4310/5/4/116MDOCFDMAMturbineaerodynamicstructuresquealercooling |
| spellingShingle | Stefano Caloni Shahrokh Shahpar Vassili V. Toropov Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines Aerospace MDO CFD MAM turbine aerodynamic structure squealer cooling |
| title | Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines |
| title_full | Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines |
| title_fullStr | Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines |
| title_full_unstemmed | Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines |
| title_short | Multi-Disciplinary Design Optimisation of the Cooled Squealer Tip for High Pressure Turbines |
| title_sort | multi disciplinary design optimisation of the cooled squealer tip for high pressure turbines |
| topic | MDO CFD MAM turbine aerodynamic structure squealer cooling |
| url | https://www.mdpi.com/2226-4310/5/4/116 |
| work_keys_str_mv | AT stefanocaloni multidisciplinarydesignoptimisationofthecooledsquealertipforhighpressureturbines AT shahrokhshahpar multidisciplinarydesignoptimisationofthecooledsquealertipforhighpressureturbines AT vassilivtoropov multidisciplinarydesignoptimisationofthecooledsquealertipforhighpressureturbines |