ePrints@IIScePrints@IISc Home | About | Browse | Latest Additions | Advanced Search | Contact | Help

Effect of Incoming Wakes on Losses of a Low-Pressure Turbine of a Gas Turbine Engine

Tandon, V and Jagadeesh, G and Ramana Murty, SV (2021) Effect of Incoming Wakes on Losses of a Low-Pressure Turbine of a Gas Turbine Engine. In: Symposium on Applied Aerodynamics and Design of Aerospace Vehicles, SAROD 2018, 29 Nov - 1 Dec 2018, Bengaluru; India, pp. 75-88.

Full text not available from this repository.
Official URL: https://doi.org/10.1007/978-981-15-9601-8_6


Modern civil aircraft engines are known for their high bypass ratio fans that are powered by many low-pressure turbine (LPT) stages (Mahallati et al. in J Turbomach 135/011010, 1). LPT can contribute as much as 30% of the weight of an aero engine (Sondergaard et al. in Toward the expansion of low-pressure turbine airfoil design space, 2; Curtis et al. in J Turbomach 119(3), 3). Aerofoils of modern LPT blades are subjected to increasingly stronger pressure gradients as designers require higher blade loading in an effort to reduce weight and costly number of LPT blades of an engine, which leads to better reliability and maintainability. This decrease in number of LPT blades results in increase of thrust/weight ratio, thus reducing the fuel consumption. But highly loaded aerofoils can reduce aerodynamic performance, and its influences can be seen more in unsteady environment. Hence, reduction of losses in unsteady environment, improves the turbine performance which is a challenging task. Therefore, there are persistent efforts towards the generation of �high-lift� blade profiles. As a result, industry and research communities are motivated for further deep research efforts in LPT aerodynamics (Sarkar in J Turbomach ASME 131, 4). In this paper, the effect of the incoming wakes shed from the upstream HPT blade on the downstream highly loaded transonic LPT vane are studied to better understand the LPT flow physics. In this paper, wakes shed from upstream HPT blade are simulated by cylinders of three different radius which are of the order of actual HPT rotor blade trailing edge radius ~0.8 mm, so that only the influence of wakes on vane losses can be studied. From these three cases, it is observed that incoming wakes does not always lead to increase in vane loss coefficient. For some cases, it is observed that the loss coefficient is 12.64% lower than the vane without any incoming wakes. © 2021, Springer Nature Singapore Pte Ltd.

Item Type: Conference Paper
Publication: Lecture Notes in Mechanical Engineering
Publisher: Springer Science and Business Media Deutschland GmbH
Additional Information: The copyright for this article belongs to Springer Science and Business Media Deutschland GmbH
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 10 Aug 2021 09:30
Last Modified: 10 Aug 2021 09:30
URI: http://eprints.iisc.ac.in/id/eprint/69129

Actions (login required)

View Item View Item