Experimental and Computational Investigations of Heat Transfer in Aero Engine Outlet Guide Vane (OGV)

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dc.contributor.authorDhanasegaran, Radheesh
dc.contributor.departmentChalmers tekniska högskola / Institutionen för mekanik och maritima vetenskapersv
dc.contributor.departmentChalmers University of Technology / Department of Mechanics and Maritime Sciencesen
dc.date.accessioned2019-07-03T14:51:37Z
dc.date.available2019-07-03T14:51:37Z
dc.date.issued2018
dc.description.abstractIn modern aircraft gas turbine engines, the turbine rear structure (TRS) located downstream of the low-pressure turbine (LPT), plays a significant role in de-swirling the flow from the LPT and currently considered as a potential LPT noise reduction device. The TRS is composed of the outlet guide vanes (OGVs) which establish a structural support between the aft bearing support and the main engine case. In future aero-engine designs, the flow that exits from the LPT will have greater amounts of swirl, which imposes a new demand on the TRS aero-design. Furthermore, as the engine conditions are subjected to change, during the take-off and landing, apart from its regular operations, the swirl angle at the inlet of OGV will be very large, leading to even large operating range. While operating at these off-design conditions, the vanes are subjected to the high amount of aerodynamic and thermal loads. Therefore, the heat transfer characteristics need to be studied in detail for an efficient design of these components. In the present study, an experimental and computational investigation of heat transfer is carried out on an OGV. The experiments are carried out at the Chalmers Turbine Test facility which is an annular cascade tunnel with an upstream LPT 1.5 stage. The heat transfer measurement is performed on the vane and hub sector. The heated model is prepared by the rapid prototyping and allows a uniform heat supply to the highly three-dimensional surface of the OGV and hub. Infrared (IR) Thermography is used to measure the vane and hub surface temperature leading to the estimation of the heat transfer distribution. The IR camera and reference thermal sensors are well calibrated before the experiments. A commercial CFD solver is used to solve the governing flow and heat transfer equations with the SST k-! and Standard k- turbulence models for adiabatic solving and SST k-! model for Conjugate solution. The results from the computational studies are validated with the experimental data. The major aim of this study is to establish an accurate technique for measurements of the heat transfer distribution on OGVs.
dc.identifier.urihttps://hdl.handle.net/20.500.12380/255757
dc.language.isoeng
dc.relation.ispartofseriesExamensarbete - Institutionen för mekanik och maritima vetenskaper : 2018:80
dc.setspec.uppsokTechnology
dc.subjectMaskinteknik
dc.subjectHållbar utveckling
dc.subjectRymd- och flygteknik
dc.subjectEnergi
dc.subjectStrömningsmekanik och akustik
dc.subjectMechanical Engineering
dc.subjectSustainable Development
dc.subjectAerospace Engineering
dc.subjectEnergy
dc.subjectFluid Mechanics and Acoustics
dc.titleExperimental and Computational Investigations of Heat Transfer in Aero Engine Outlet Guide Vane (OGV)
dc.type.degreeExamensarbete för masterexamensv
dc.type.degreeMaster Thesisen
dc.type.uppsokH
local.programmeApplied mechanics (MPAME), MSc
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