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Flow characteristics in aeroengine bearing chambers with shallow sump (2019)
Conference Proceeding
Chandra, B., & Simmons, K. (2019). Flow characteristics in aeroengine bearing chambers with shallow sump. https://doi.org/10.1115/GT2019-90320

In an aeroengine oil is supplied to the bearings for lubrication and cooling. Subsequently, it creates a two phase flow environment in the bearing chamber that may contain droplets, mist, wall film, ligaments, froth or foam and liquid pools. After th... Read More about Flow characteristics in aeroengine bearing chambers with shallow sump.

Transient two-phase effects in an Aeroengine bearing chamber scavenge test rig (2014)
Conference Proceeding
Chandra, B., & Simmons, K. (2014). Transient two-phase effects in an Aeroengine bearing chamber scavenge test rig. In ASME 2014 International Mechanical Engineering Congress and Exposition - Volume 1: Advances in Aerospace Technology, (V001T01A046). https://doi.org/10.1115/IMECE2014-37554

Copyright © 2014 by ASME. Aeroengine bearing chambers typically contain bearings, seals, shafts and static parts. Oil is introduced for lubrication and cooling and this creates a two phase flow environment that may contain droplets, mist, film, ligam... Read More about Transient two-phase effects in an Aeroengine bearing chamber scavenge test rig.

Experimental investigation into the performance of shallow aeroengine off-takes (2014)
Conference Proceeding
Simmons, K., & Chandra, B. (2014). Experimental investigation into the performance of shallow aeroengine off-takes. In Volume 5C: Heat Transfer, (V05CT16A022). https://doi.org/10.1115/GT2014-26132

Copyright © 2014 by Rolls-Royce plc. Oil removal (scavenge) from aeroengine bearing chambers is an ongoing challenge for aeroengine designers. Effective scavenging of oil is necessary to avoid excessive heat generation, degradation of oil properties... Read More about Experimental investigation into the performance of shallow aeroengine off-takes.

Performance comparison for aeroengine-type sump geometries (2013)
Conference Proceeding
Keeler, B., Chandra, B., Simmons, K., & Keeler, B. (2013). Performance comparison for aeroengine-type sump geometries. In Volume 1: Advances in Aerodynamicshttps://doi.org/10.1115/IMECE2013-62836

Oil removal from aeroengine bearing chambers presents a challenge for aeroengine designers. Effective scavenging of oil is necessary to avoid excessive heat in the bearing chamber as this may lead to degradation of oil properties and deterioration in... Read More about Performance comparison for aeroengine-type sump geometries.

Liquid and gas flow behaviour in highly rotating environment (2011)
Conference Proceeding
Chandra, B., Simmons, K., Pickering, S., & Tittel, M. (2011). Liquid and gas flow behaviour in highly rotating environment. In Volume 1: Aircraft Engine; Ceramics; Coal, Biomass and Alternative Fuels; Wind Turbine Technology, (337-345). https://doi.org/10.1115/GT2011-46430

In a typical aero engine bearing chamber, oil is introduced to lubricate and cool the bearings as well as the bearing chamber wall. The flow of the oil in the bearing chamber is very complex due to the presence of various forces: gravity, windage, ca... Read More about Liquid and gas flow behaviour in highly rotating environment.

Development of non-destructive heat resistance evaluation system for TBC on gas turbine blade (2010)
Conference Proceeding
Fujioka, T., Sakai, E., Takahashi, T., Fujii, T., Chandra, B., Simmons, K., …Tittel, M. (2010). Development of non-destructive heat resistance evaluation system for TBC on gas turbine blade. In Volume 1: Aircraft Engine; Ceramics; Coal, Biomass and Alternative Fuels; Education; Electric Power; Manufacturing Materials and Metallurgy, (125-131). https://doi.org/10.1115/GT2010-22631

The use of thermal barrier coatings (TBCs) is the key technique for realizing high-efficiency gas turbine combined cycles. Hence, TBCs are applied to various hot gas path components such as combustors, blades, and vanes. The application of a TBC caus... Read More about Development of non-destructive heat resistance evaluation system for TBC on gas turbine blade.