Experimental Study of Impact of In-Service Deterioration on Thermal Performance of High-Pressure Nozzle Guide Vanes

Michaud, Mathias; Chowdhury, Nafiz H. K.; Povey, Thomas

doi:10.1115/1.4055864

Cited by 5 publications

(3 citation statements)

References 44 publications

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“…Hub mounted systems have been used in the ECAT facility (Burdett and Povey, 2022a;Kirollos et al, 2017;Michaud et al, 2022b), the von Karman Institute CT3 facility (Sieverding and Arts, 1992) and the Chalmers University LPT-OGV facility (Jonsson et al, 2018;Jonsson, 2021). The existing ECAT facility downstream traverse system (Michaud et al, 2022b) mounts onto a backing plate downstream of the NGV ring. The system features a large central bearing on the machine axis, around which the traverse system rotates.…”

Section: Literature Reviewmentioning

confidence: 99%

“…The Engine Component Aero-Thermal (ECAT) facility (Kirollos et al, 2017) is a nozzle guide vane (NGV) test facility designed to characterize the aero-thermal performance of engine parts. The facility operates at engine-matched Mach and Reynolds numbers and has been used for studies of NGV capacity (Burdett et al, 2021), heat transfer (Michaud et al, 2022a), and aerodynamic performance Povey, 2022a, 2022b;Michaud et al, 2022b). The inlet flow can be conditioned to be uniform in total temperature and pressure, or to operate with an upstream combustor simulator (Kirollos et al, 2017).…”

Section: Introductionmentioning

confidence: 99%

“…This data is used to set the row pressure ratio, and to establish the temperature boundary conditions for overall effectiveness measurements. When operating with non-uniform inlet conditions (temperature distortion and swirling flow) traverse measurements have been performed using a hub-mounted downstream traverse system (see Burdett and Povey (2022a), Kirollos et al (2017), and Michaud et al (2022b)). This system has the advantage that it can be used to survey the entire 360° annulus (in 40 segments), but the disadvantage that it necessitates removal of the NGVs to survey the inlet cassette plane, shown in Figure 1 (a).…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Ultra-Compact Traverse System for Transonic Annular Cascade

Amend¹,

Povey*²

2022

Proceedings of Global Power &Amp; Propulsion Society

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This paper describes the design and commissioning of an ultra-compact traverse system for the Engine Component Aerothermal (ECAT) facility at the University of Oxford, an engine-parts facility operating at engine-representative Mach and Reynolds numbers. The traverse system was required to be unusually compact to integrate within an existing upstream cassette system. The system has been used to perform detailed surveys of inlet total pressure, temperature, flow angles, velocity, and turbulence. The design and commissioning are described in detail. Example data is also provided. It is hoped that the novel design will be useful for other engineers involved in facility design.

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Section: Literature Reviewmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Ultra-Compact Traverse System for Transonic Annular Cascade

Amend¹,

Povey*²

2022

Proceedings of Global Power &Amp; Propulsion Society

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Lean-Burn Combustor Simulator for an Engine-Component Test Facility: An Experimental and Computational Study

Amend

Lubbock

Ornano

et al. 2023

Journal of Turbomachinery

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The computational and experimental assessment of a lean-burn low-NOx combustor simulator for an engine component test facility is presented. The Engine Component Aero-Thermal (ECAT) facility is a full-scale engine-parts facility, designed for the study of the aero-thermal performance of fully cooled high-pressure nozzle guide vanes (NGVs). The facility operates with non-dimensionally matched engine conditions in terms of Reynolds number, Mach number and coolant-to-mainstream pressure ratio. The combustor simulator is designed to replicate lean-burn conditions of swirl and temperature distortion upstream of the nozzle guide vanes. The purpose is to allow the study of flow capacity, aerodynamic performance (with film cooling), and thermal performance (overall effectiveness) in the presence of engine-realistic inlet distortions. Detailed experimental measurements with multi-hole probes and thermocouples are presented and compared to results from RANS Simulations. Additional simulations were performed to understand how the elevated back pressure and vane potential field affect the non-dimensional profiles of pressure loss, residual swirl and temperature at the combustor-turbine interface. This is perhaps the most comprehensive study to date of a combustor simulator in an engine-scale research facility, providing unique insight into the known challenges of simulator design, scaling issues when moving from low to high Reynolds number, and limitations of CFD in this flow environment.

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Impact of Temperature Ratio on Overall Cooling Performance: Low-Order-Model-Based Analysis of Experiment Design

Naidu

Povey

2023

Journal of Turbomachinery

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This paper describes low-order-model-based analysis of the design of an experiment to be used for parametric studies of adiabatic film and overall cooling effectiveness for fully cooled systems (internal and film) under wide ranges of mainstream-to-coolant temperature ratio variation, in the range 0.50 < T0m/T0c < 2.30. The purpose is to improve understanding of—and validation of—the scaling process from typical rig conditions to engine conditions. We are primarily interested in the variation in overall effectiveness when the controlling non-dimensional groups change in a natural co-dependent way with changes in temperature ratio: that is, the practical situation of interest to engine designers. We distinguish this from the situation in which individual non-dimensional groups are varied in isolation: a situation that we believe is essentially impossible to meaningfully approximate in practice, despite a body of literature purporting to do the same. Design and commissioning data from a new high temperature (600 K) test facility is presented, with detailed uncertainty analysis. We show that a typical nozzle guide vane which at engine conditions (TR = 2.00) would have overall cooling effectiveness of 0.450, would be expected to have overall effectiveness of 0.418 at typical rig conditions (TR = 1.20). That is, typical scaling from engine-to-rig result is −7.1%, and typical scaling from rig-to-engine is +7.7%, This result is important for first order estimation of overall cooling performance at engine conditions.

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Experimental Study of Impact of In-Service Deterioration on Thermal Performance of High-Pressure Nozzle Guide Vanes

Cited by 5 publications

References 44 publications

Ultra-Compact Traverse System for Transonic Annular Cascade

Ultra-Compact Traverse System for Transonic Annular Cascade

Lean-Burn Combustor Simulator for an Engine-Component Test Facility: An Experimental and Computational Study

Impact of Temperature Ratio on Overall Cooling Performance: Low-Order-Model-Based Analysis of Experiment Design

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