SAMULET Project 1 - High Efficiency Turbomachinery
Lead Research Organisation:
Loughborough University
Department Name: Aeronautical and Automotive Engineering
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
Cha C
(2012)
Experimental and Numerical Investigation of Combustor-Turbine Interaction Using an Isothermal, Nonreacting Tracer
in Journal of Engineering for Gas Turbines and Power
| Description | The major key finding from this research programme is ability to replicate the temperature traverse delivered by the combustion system to the high-pressure turbine using low-level gas tracing under non-reacting flow conditions. This finding offers the combustion system designer the opportunity to optimise the temperature traverse delivered to the turbine well in advance of final hardware definition. The costs of delivering this improved temperature traverse are also reduced by 2 orders of magnitude. |
| Exploitation Route | Findings from this research programme have now been adopted by Rolls-Royce plc as part of their strategy for defining and developing the temperature traverse demanded by the high-pressure turbine. |
| Sectors | Aerospace, Defence and Marine,Environment,Transport |
| Description | The experimental techniques developed under this research programme have since been adopted many times to help understand and improve the flow field present within the combustor/turbine interface region. Rolls-Royce engines that have benefited directly from these techniques have included the Trent 1000 and Trent XWB large civil fan propulsion units. |
| First Year Of Impact | 2013 |
| Sector | Aerospace, Defence and Marine,Environment,Transport |
| Impact Types | Economic |
| Title | Gas Turbine Engine End-wall Component |
| Description | "The invention relates to an end-wall component of the working gas annulus of a gas turbine engine, the component having a cooling arrangement including one or more rows of ballistic cooling holes through which, in use, dilution cooling air is jetted into the working gas to reduce the working gas temperature adjacent the end-wall." |
| IP Reference | GB1219731.5 |
| Protection | Patent application published |
| Year Protection Granted | 2012 |
| Licensed | Yes |
| Impact | The invention was originally conceived within the Rolls-Royce UTC at Loughborough University to extend the life of the high pressure turbine nozzle guide vane platform of the Rolls-Royce Trent 1000 aero-engine. The new design has since been fully evaluated up to TRL 9 and is now in use on the first Trent 1000-TEN engine. |