SAMULET Project 1 - High Efficiency Turbomachinery
Lead Research Organisation:
University of Oxford
Department Name: Engineering Science
Abstract
Abstracts are not currently available in GtR for all funded research. This is normally because the abstract was not required at the time of proposal submission, but may be because it included sensitive information such as personal details.
Organisations
Publications
He L
(2009)
Unsteady Conjugate Heat Transfer Modelling
Lad B
(2013)
Use of an Immersed Mesh for High Resolution Modeling of Film Cooling Flows
in Journal of Turbomachinery
Maffulli R
(2014)
Wall Temperature Effects on Heat Transfer Coefficient for High-Pressure Turbines
in Journal of Propulsion and Power
Maffulli R
(2017)
Impact of Wall Temperature on Heat Transfer Coefficient and Aerodynamics for Three-Dimensional Turbine Blade Passage
in Journal of Thermal Science and Engineering Applications
Zhang Q
(2011)
Overtip Shock Wave Structure and Its Impact on Turbine Blade Tip Heat Transfer
in Journal of Turbomachinery
Zhang Q
(2013)
Tip-Shaping for HP Turbine Blade Aerothermal Performance Management
in Journal of Turbomachinery
Zhang Q
(2011)
Overtip Choking and Its Implications on Turbine Blade-Tip Aerodynamic Performance
in Journal of Propulsion and Power
| Description | -The experimental high speed testing and corresponding computational analyses have revealed for the first time that there is a qualitatively different characteristics (opposite trends of variations) in turbine blade tip heat transfer between an engine representative high-speed condition and the conventional low speed conditions. This new finding and underlined physical understanding has significant impact on the basis and wisdom of the turbine blade tip selection and designs. It also forms the basis for a patent fro blade tip aerothermal management. The effort and outcomes of this part of the research has featured in a short film as part of the Oxford Impact (further supported by ESPRC/Oxford Award for Impact Pathway). - A novel blade cooling simulation method, Immersed Mesh Block (IMB) has been developed, implemented, tested and demonstrated in a major industrial Computational Fluid Dynamics (CFD) software system, to be applied in a real design environment for future turbine blade heat transfer and cooling designs. -For engine realistic temperature conditions, there is a significant heat transfer-aerodynamic interaction- convection heat transfer from hot gas to blade has a considerable effect on near-wall boundary layers, which in turn affect the convection heat transfer characteristics. -upgrading of an nationally unique turbine test facility at Oxford. |
| Exploitation Route | Already by the industrial partner, a major UK based leading aerospace manufacturer |
| Sectors | Aerospace Defence and Marine Energy Transport |
| Description | -The experimental high speed testing and corresponding computational analyses have revealed for the first time that there is a qualitatively different characteristics (opposite trends of variations) in turbine blade tip heat transfer between an engine representative high-speed condition and the conventional low speed conditions. This new finding and underlined physical understanding has significant impact on the basis and wisdom of the turbine blade tip selection and designs. It also forms the basis for a patent fro blade tip aerothermal management. The effort and outcomes of this part of the research has featured in a short film as part of the Oxford Impact (further supported by ESPRC/Oxford Award for Impact Pathway). - A particular turbine tip configuration 'Winglet' (which has been selected for aerodynamic benefits) has been shown to be thermally detrimental (in heat transfer) thus has significant implication on the blade lifespan/durability. This new finding is believed to have made an influence on the selection/de-selection of new blade tip configurations in the industrial partner. - A novel blade cooling simulation method, Immersed Mesh Block (IMB) has been developed as part of the project supported by the grant. The method has been implemented, tested and demonstrated in a major industrial Computational Fluid Dynamics (CFD) code, HYDRA, to be applied in a real design environment for future turbine blade heat transfer and cooling designs. As part of a DPhil project supported by the grant, the feedback of convection heat transfer on aerodynamics was investigated. As the result, an extra term is introduced to the commonly known Newton's law of cooling (i.e. the convection heat transfer equation), leading to a new 3-point working method for heat transfer coefficient. This new 3-point method has been published in a learned journal, and more relevantly, integrated to a practical turbine heat transfer and cooling design system. - A major transonic turbine research facility (Oxford Turbine Research Facility (OTRF) has been relocated and upgraded. This is a very unique facility in UK, and a marker of the leading position of Oxford in high speed turbine aerothermal instrumentation and testing. |
| First Year Of Impact | 2012 |
| Sector | Aerospace, Defence and Marine,Energy,Manufacturing, including Industrial Biotechology,Transport |
| Impact Types | Economic |