Impact of trailing edge damage on nozzle guide vane aerodynamic performance

Journal article

In this paper, we consider the impact of trailing edge burn-back on the aerodynamic performance of cooled transonic high-pressure nozzle guide vanes. We consider four levels of burn-back ranging from new parts to severely damaged parts. High-fidelity experimental aerodynamic performance data were taken in the Engine Component AeroThermal facility at the University of Oxford, at engine-matched conditions of Mach number, Reynolds number, and coolant-to-mainstream pressure ratio. Experimental data are compared to the results of computational fluid dynamics simulations to provide further insights into the mechanisms affecting performance. We find that for fixed row pressure ratio, increasing burn-back leads to: both increased loading, and increased forward loading; increased film cooling flow due to reloading and increased trailing edge flow due to slot area increase; increased overall boundary layer loss; a significant increase in exit secondary kinetic energy associated with newly formed counterrotating vortices at the edges of the burn-back region; and increased variation in exit whirl angle. We quantify these effects and consider implications for whole-life engine performance.

Authors: Raduev, Z; Jackson, D; Chowdhury, N; Povey, T

• Publication status: Published
• Peer review status: Peer reviewed
• Publisher: American Society of Mechanical Engineers
• Journal: Journal of Turbomachinery
• Volume: 147
• Issue: 10
• Article number: 101007
• Publication date: 2025-03-20
• Acceptance date: 2025-01-13
• DOI: 10.1115/1.4067930
• EISSN: 1528-8900
• ISSN: 0889-504X
• Language: English
• Keywords: computational fluid dynamics (CFD); fluid dynamics and heat transfer phenomena in compressor and turbine components of gas turbine engines; measurement techniques; turbine blade and measurement advancements; turbomachinery blading design; vortex shedding; turbine component erosion