Aerothermal Performance of Shroudless Turbine Blade Tips with Relative Casing Movement Effects

Virdi, Amarjit S.; Zhang, Q.; He, L.; Li, H. D.; Hunsley, R.

doi:10.2514/1.b35331

Cited by 58 publications

(21 citation statements)

References 50 publications

(47 reference statements)

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“…The y + of the first grid point away from the tip was between 1 and 3, with a mean value of 2 whilst the remainder of the blade had an average y + of 3. This was considered sufficient to ensure resolution of the viscous sub-layer and is consistent with recent aerodynamic work of Schabowski et al (2014) [37] (tip y + ≈ 4) and aerothermal work of Virdi et al (2015) [38] (tip y + largely between 1 and 3) who demonstrated close agreement between CFD and experiment. Figure 7 shows the experimentally measured tip surface heat flux along the camber line.…”

Section: Computational Set-upsupporting

confidence: 86%

An experimental and computational study of tip clearance effects on a transonic turbine stage

Jackson

Wheeler

Ainsworth

2015

International Journal of Heat and Fluid Flow

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This paper describes an experimental and computational investigation into the influence of tip clearance on the blade tip heat load of a high-pressure (HP) turbine stage. Experiments were performed in the Oxford Rotor facility which is a 1 1 2 stage, shroudless, transonic, high pressure turbine. The experiments were conducted at an engine representative Mach number and Reynolds number. Rotating frame instrumentation was used to capture both aerodynamic and heat flux data within the rotor blade row. Two rotor blade tip clearances were tested (1.5 % and 1.0 % of blade span). The experiments were compared with computational fluid dynamics (CFD) predictions made using a steady Reynolds-averaged Navier-Stokes (RANS) solver. The experiments and computational predictions were in good agreement. The blade tip heat transfer was observed to increase with reduced tip gap in both the CFD and the experiment. The augmentation of tip heat load at smaller clearances was found to be due to the ingestion of high relative total temperature fluid near the casing, generated through casing shear.

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Section: Computational Set-upsupporting

confidence: 86%

An experimental and computational study of tip clearance effects on a transonic turbine stage

Jackson

Wheeler

Ainsworth

2015

International Journal of Heat and Fluid Flow

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“…Another factor pertinent to the present interest is the relative movement of casing. This can clearly affect the extent of transonic portion of the tip flow as shown computationally by Zhang et al (2011b); Coull and Atkins (2015); Virdi et al (2015). Some recent data for a rotating facility have been gathered by Acharya (2016a, 2016b).…”

Section: Discussionmentioning

confidence: 95%

“…The dependence of heat transfer patterns on OTL flow regime can be further examined by studying the sensitivity of the flow to tip gap size. Circumferentially averaged heat transfer coefficients (HTCs) along axial chord for a transonic flat tip are shown in Figure 7 (Virdi et al, 2015). The subsonic flow part (x/Cx<0.5) shows a classic trend of decreasing heat transfer with smaller tip gaps.…”

Section: Overall Heat Transfer Characteristics In High Speed Flowmentioning

confidence: 99%

Turbine blade tip aero-thermal management: Some recent advances and research outlook

Zhang

2017

J. Glob. Power Propuls. Soc.

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This article provides an overview of some recent progress in understanding HP turbine blade shroudless tip heat transfer and aerodynamics, especially in a transonic regime. The review is mostly based on the experimental and numerical efforts the authors have been involved in during the past ten years. Some fundamental flow physics especially in high speed Over-Tip-Leakage (OTL) flows are highlighted, including tip choking, shock waves, and the roles played by flow turbulence, etc. These mechanisms bring qualitative differences in tip heat transfer and loss generation, and prospects in tip aerothermal management and control. Of great interest is the strong OTL flow–coolant interaction, which can dramatically affect the tip aerodynamics, and thus would challenge any “optimized” tip geometry based on an uncooled configuration. It is suggested that optimal tip aero-thermal configurations should be an iterative process between blade tip shaping and cooling injection scheme. Combining tip geometry shaping and cooling injection patterns concurrently may provide more extensive exploitation of tip aerothermal design space.

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“…Dunn and Haldeman 14 and Virdi et al. 15 also investigated the heat transfer performance of the blade tip with experimental measurement.…”

Section: Introductionmentioning

confidence: 99%

“…Zhang and He 13 found that the tip choking caps the tip leakage mass flow rate in the transonic condition. Dunn and Haldeman 14 and Virdi et al 15 also investigated the heat transfer performance of the blade tip with experimental measurement.…”

Section: Introductionmentioning

confidence: 99%

Effects of the novel rib layouts on the tip leakage flow pattern and heat transfer performance of turbine blade

Jiang

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The steady simulation with flow field and heat transfer performance for different rib layouts is investigated. By referring the GE-E3 turbine blade tip (Case 1) profile as a prototype model, four kinds of rib layouts of full rib structure (Case 2), half rib structure connected with suction side (Case 3), half rib structure connected with pressure side (Case 4), and half rib structure in the rear squealer cavity (Case 5) was designed. The availability of k-ω turbulence model was validated through comparison of heat transfer coefficient distribution with the experimental data. The area-averaged heat transfer coefficients of Case 5 decreases up to 11.3%, 3.1%, 11.3%, and 2.8% in comparison to Cases 1, 2, 3, and 4. The total pressure coefficient of Case 5 reduces by 1.4%, 2.7%, and 4.0% compared to Cases 1, 2, and 3. The results reveal that, among the five novel rib layout cases, Case 5 obtains the optimal comprehensive performance under the performance of considering tip heat transfer and cascade loss. Further investigation on the influence of Cases 1 and 5 at different rotational speeds on the flow field and heat transfer characteristics of the tip clearance is also illustrated and discussed.

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Aerothermal Performance of Shroudless Turbine Blade Tips with Relative Casing Movement Effects

Abstract: This is the accepted version of the paper.This version of the publication may differ from the final published version. Permanent repository link

Cited by 58 publications

References 50 publications

An experimental and computational study of tip clearance effects on a transonic turbine stage

An experimental and computational study of tip clearance effects on a transonic turbine stage

Turbine blade tip aero-thermal management: Some recent advances and research outlook

Effects of the novel rib layouts on the tip leakage flow pattern and heat transfer performance of turbine blade

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