Windage Torque Reduction in Low-Pressure Turbine Cavities Part 2: Experimental and Numerical Results

Richard Jackson, Gary D. Lock, Carl M. Sangan, James A. Scobie, Zhihui Li, Loizos Christodoulou, Richard Jefferson-Loveday, Stephen Ambrose

Research output: Chapter or section in a book/report/conference proceedingChapter in a published conference proceeding

4 Citations (SciVal)

Abstract

Minimizing the losses within a low-pressure turbine (LPT) system is critical for the design of next-generation ultra-high bypass ratio aero-engines. The stator-well cavity windage torque can be a significant source of loss within the system, influenced by the ingestion of mainstream annulus air with a tangential velocity opposite to that of the rotor.

This paper presents experimental and numerical results of three carefully designed Flow Control Concepts (FCCs) — additional geometric features on the stator surfaces, which were optimized to minimize the windage torque within a scaled, engine-representative stator-well cavity. FCC1 and FCC2 featured rows of guide vanes at the inlet to the downstream and upstream wheel-spaces, respectively. FCC3 combined FCC1 and FCC2. Superposed flows were introduced to the upstream section of the cavity, which modelled the low radius coolant and higher radius leakage between the rotor blades. In addition to torque measurements, total and static pressures were collected, from which the cavity swirl ratio was derived. Additional swirl measurements were collected using a five-hole aerodynamic probe, which traversed radially at the entrance and exit of the cavity.

A cavity windage torque reduction of 55% on the baseline (which has no flow control) was measured for FCC3, at the design condition with superposed flow. For this concept, an increase in the cavity swirl in both the upstream and downstream wheel-spaces was demonstrated experimentally and numerically. With increasing superposed flow, the contribution of FCC1 surpassed FCC2, due to more mass flow entering the downstream wheel-space across the rotor fins (passing FCC1), and less ingestion from the annulus into the upstream wheel-space (passing FCC2). The torque changes from the concepts are explained using the fluid dynamic evidence from experimental swirl measurements and computational simulations. The simulations allow translation to engine-operating conditions and practical information to the engine designer.
Original languageEnglish
Title of host publicationTurbomachinery - Axial Flow Turbine Aerodynamics
Subtitle of host publicationAxial Flow Turbine Aerodynamics
Number of pages11
Volume13B
ISBN (Electronic)9780791887097
DOIs
Publication statusPublished - 28 Sept 2023
EventASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition - Boston, Massachusetts, USA
Duration: 26 Jun 202330 Jun 2023

Publication series

NameProceedings of the ASME Turbo Expo
Volume13B

Conference

ConferenceASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition
Period26/06/2330/06/23

Funding

This project was funded by Clean Sky 2 Joint Undertaking under the European Union’s Horizon 2020 research and innovation program (H2020-GAP-886112-ACUHRA). The authors thank Matt Hawthorne at Added Scientific Ltd for his support in this project. The calculations were performed using the University of Nottingham HPC Facility and Sulis at HPC Midlands Plus, which was funded by EPSRC grant EP/T022108/1. This project was funded by Clean Sky 2 Joint Undertaking under the European Union's Horizon 2020 research and innovation program (H2020-GAP-886112-ACUHRA). The authors thank Matt Hawthorne at Added Scientific Ltd for his support in this project. The calculations were performed using the University of Nottingham HPC Facility and Sulis at HPC Midlands Plus, which was funded by EPSRC grant EP/T022108/1.

FundersFunder number
Horizon 2020 Framework Programme
Engineering and Physical Sciences Research CouncilEP/T022108/1
University of Nottingham
Horizon 2020H2020-GAP-886112-ACUHRA

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