Aerodynamic and heat transfer performances of a highly loaded transonic turbine rotor with upstream generic rim seal cavity

Mansouri, Zakaria

Abstract

In turbine disk cavity, rim seals are fitted between the stator and its adjacent rotor disk. A coolant air injected through the turbine disk cavity to prevent the ingress of mainstream hot gases. The purpose of this paper is to investigate numerically the effect of the upstream purge flow on the aero and thermal performances of a high pressure turbine rotor. The investigations are conducted on a generic rim seal cavity inspired from a realistic turbofan engine. Four purge fractions (PF) equal to 0.2%, 0.5%, 1.0% and 1.5% of the mainstream are considered. The simulations are done by solving the three-dimensional Reynolds averaged Navier-Stokes and energy transport equations. The results include the effect of the PF on the cooling effectiveness, the sealing effectiveness, the secondary flows with losses and the heat transfer behavior, within the cavity and across the rotor passage. The low PF of 0.2% provided a low cooling effectiveness, a moderate sealing effectiveness and minimum losses. The high PF of 1.5% gave a high cooling effectiveness, a best sealing effectiveness and maximum losses. The medium PF of 1.0% supplied a compromise between the aerodynamic and thermal design needs with good cooling and sealing efficiencies and a tolerable level of losses.

Citation

Mansouri, Z. (2021). Aerodynamic and heat transfer performances of a highly loaded transonic turbine rotor with upstream generic rim seal cavity. Propulsion and Power Research, 10(4), 317-331. https://doi.org/10.1016/j.jppr.2021.11.003

• Journal Article Type: Article
• Acceptance Date: Nov 22, 2021
• Online Publication Date: Dec 24, 2021
• Publication Date: 2021-12
• Deposit Date: Jul 14, 2022
• Publicly Available Date: Jul 15, 2022
• Journal: Propulsion and Power Research
• Print ISSN: 2212-540X
• Electronic ISSN: 2212-540X
• Publisher: Elsevier
• Peer Reviewed: Peer Reviewed
• Volume: 10
• Issue: 4
• Pages: 317-331
• Series ISSN: 2212-540X
• DOI: https://doi.org/10.1016/j.jppr.2021.11.003
• Keywords: Axial turbine; Thermal characteristics; Aerodynamic losses; Generic cavity; Purge flow; Rim seal; Numerical simulation
• Public URL: https://nottingham-repository.worktribe.com/output/8953027
• Publisher URL: https://www.sciencedirect.com/science/article/pii/S2212540X21000584?via%3Dihub
• Additional Information: This article is maintained by: Elsevier; Article Title: Aerodynamic and heat transfer performances of a highly loaded transonic turbine rotor with upstream generic rim seal cavity; Journal Title: Propulsion and Power Research; CrossRef DOI link to publisher maintained version: https://doi.org/10.1016/j.jppr.2021.11.003; Content Type: article; Copyright: © 2021 Beihang University. Publishing services by Elsevier B.V. on behalf of KeAi Communications Co. Ltd.