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Title: The influence of fan root flow on the aerodynamics of a low-pressure compressor transition duct
Authors: Walker, Alastair Duncan
Mariah, I.
Tsakmakidou, D.
Vadhvana, H.
Hal, C.
Issue Date: 2019
Publisher: © Rolls Royce. Published by ASME
Citation: WALKER, A.D. ... et al., 2019. The Influence of Fan Root Flow on the Aerodynamics of a Low-Pressure Compressor Transition Duct. Presented at the ASME International Gas Turbine and Aeroengine Congress and Exposition, Phoenix, AR, USA, June 17 – 21.
Series/Report no.: ASME paper;GT2019-92048
Abstract: To reduce fuel-burn and CO2 emissions from aero gas turbines there is a drive towards very-high bypass ratio and smaller ultra-high-pressure ratio core engine technologies. However, this makes the design of the ducts connecting various compressor spools more challenging as the higher required radius change increases their aerodynamic loading. This is exacerbated for the duct which feeds the engine core as it must accept the relatively low-quality flow produced by the fan root. This is characterised by a hub-low pressure profile and large secondary flow structures which will inevitably increase loss and the likelihood of flow separation. Additionally, the desire for shorter, lighter nacelles means that the engine intake may be unable provide a uniform inlet flow to the fan when the aircraft is at an angle of attack or subject to cross winds. Any inlet distortion this generates can also further degrade the quality of the flow entering the core of the engine. This paper uses a combination of experiments and CFD to examine the effects of the inlet flow on the aerodynamics of an engine section splitter and transition duct designed to feed the low-pressure spool of a high bypass ratio turbofan. A fully annular test facility incorporating a 1½ stage axial compressor was used to compare the system performance of a rotor that produced a nominally flat profile with one that had a notably hub deficient flow. A RANS CFD model, employing a mixing plane between the rotor and Engine Section Stator (ESS) and a Reynolds Stress turbulence model, was then validated and used to further investigate the effects of increased inlet boundary layer thickness and bulk swirl distortion at rotor inlet. Overall, changes to the inlet condition were seen to have a surprisingly small effect on the flow at duct exit – i.e. the flow presented to the downstream compressor. Changes to the inlet did, however, generate increased secondary flows and degrade the performance of the ESS. This resulted in notably increased total pressure loss; in excess of 12% for the hub-low inlet and in excess of 30% at high inlet swirl where the flow in the ESS separated. However, the increased ESS wake structures, and the enhanced mixing, delayed separation in the duct suggesting that, overall the design was reasonably robust, albeit with a significant penalty in system loss.
Description: This paper is in closed access.
Sponsor: It was funded by the Aerospace Technology Institute as part of the iCORE (Integrated Core Technologies) program.
Version: Published
URI: https://dspace.lboro.ac.uk/2134/37468
Publisher Link: https://event.asme.org/Turbo-Expo
Appears in Collections:Closed Access (Aeronautical and Automotive Engineering)

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