Full Thermal Experimental Assessment of a Dendritic Turbine Vane Cooling Scheme

Luque, Salvador; Batstone, J.; Gillespie, David R. H.; Povey, Thomas; Romero, Eduardo

doi:10.1115/1.4023940

Cited by 7 publications

(5 citation statements)

References 8 publications

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“…R ESEARCH investment in metal effectiveness (or overall cooling effectiveness) measurement techniques has been driven by the desire to accurately assess the overall thermal performance of nozzle guide vanes or turbine blades at engine-realistic conditions [1][2][3][4][5][6]. The traditional approach of predicting overall thermal performance of such parts from a thermal model with boundary conditions obtained from separate experiments [7][8][9][10] has the disadvantage that errors in underlying measurements can accumulate in the final result.…”

Section: Nomenclaturementioning

confidence: 99%

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Methods to Extract Underlying Boundary Conditions from Transient Metal Effectiveness Measurements

Michaud

Povey

2021

Journal of Thermophysics and Heat Transfer

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Metal effectiveness measurements (or overall cooling effectiveness measurements) are becoming increasingly used to understand complex coupled systems in gas turbine experimental research. Unlike traditional techniques in which individual boundary conditions are measured in isolation and superposed using a thermal model, metal effectiveness measurements give the final result of a complex coupled system. In correctly scaled experiments this allows aerothermal performance at near-engine conditions to be evaluated directly, and is thus powerful both as a research technique and for derisking engine development programs. The technique is particularly useful for evaluating the thermal performance of internally cooled turbine components, because of the complexity and degree of interaction of the underlying boundary conditions. An intrinsic limitation of metal effectiveness measurement data is that the individual boundary conditions (e.g., the internal and external heat transfer coefficients) cannot be directly obtained from the final measurement. Decoupling of these boundary conditions would allow deeper understanding of the systems that are the subject of experiments. The objective of this paper is to present methods to extract the individual underlying boundary conditions from data available in typical metal effectiveness experimental measurements, and to assess the uncertainty associated with decoupling techniques. Although we reference experimental data from advanced facilities for metal effectiveness research throughout, much of the analysis is performed using a low-order heat transfer model to allow the impact of experiment design and measurement errors to be clearly separated at each stage of the analysis.

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Section: Nomenclaturementioning

confidence: 99%

“…These nodes are solved using Eqs. (3)(4)(5), respectively. The simulation parameters are listed in Table 2.…”

Section: Modelingmentioning

confidence: 99%

Methods to Extract Underlying Boundary Conditions from Transient Metal Effectiveness Measurements

Michaud

Povey

2021

Journal of Thermophysics and Heat Transfer

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“…An Figure 21. Typical blade cooling designs, (a) nozzle guide vane [22], (b) turbine vane [23], and (c) turbine blade [19].…”

Section: Convective Cooling With Jet Impingementmentioning

confidence: 99%

Basic Aspects of Gas Turbine Heat Transfer

Naik¹

2017

Heat Exchangers - Design, Experiment and Simulation

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The use of gas turbines for power generation and electricity production in both single cycle and combined cycle plant operation is extensive and will continue to globally grow into the future. Due to its high power density and ability to convert gaseous and liquid fuel into mechanical work with very high thermodynamic efficiencies, significant efforts continue today to further increase both the power output and thermodynamic efficiencies of the gas turbine. In particular, the aerothermal design of gas turbine components has progressed at a rapid pace in the last decade with all gas turbine manufacturers, in order to achieve higher thermodynamic efficiencies. This has been achieved by using higher turbine inlet temperatures and pressures, advanced turbine aerodynamics and efficient cooling systems of turbine airofoils, and advanced high temperature alloys, metallic coatings, and ceramic thermal barrier coatings. In this chapter, issues related to the thermal design of gas turbine blades are highlighted and several heat transfer technologies are examined, such as convective cooling, impingement cooling, film cooling, and application of thermal barrier coatings. Typical methods for validating the thermal designs of gas turbine airofoils are also outlined.

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“…Operating conditions are summarised in Tab. 2 (see also [6][7][8][9]). During a run (in which the mainstream Mach number distribution is matched to engine conditions), the coolant capacity is measured using a calibrated venturi nozzle.…”

Section: Annular Sector Heat Transfer Facilitymentioning

confidence: 99%

Method for Accurately Evaluating Flow Capacity of Individual Film-Cooling Rows of Engine Components

Kirollos

Povey

2017

Journal of Turbomachinery

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A laboratory experimental method and an analysis technique are presented for evaluation of individual film-cooling row flow capacity characteristics. The method is particularly suited to complex systems such as hot section nozzle guide vanes (NGV) with lossy feed system characteristics. The method is believed to be both more accurate and more experimentally efficient than previous techniques. The new analysis technique uses an experimentally calibrated network model to represent the complex feed system and replaces the need for internal loss measurements, which are both demanding and inaccurate. Experiments are performed in the purpose-built University of Oxford Coolant Capacity Rig (CCR), a bench-top, blow-down type facility with atmospheric back-pressure. The design of the CCR is informed by the requirements to assess engine-scale film-cooled components rapidly, accurately, and precisely. Improvements in the experimental method include a differential mass flow rate measurement method (which eliminates the effect of leaks and minimizes the number of rows that must be blanked, ensuring that the internal coupling is as close as possible to the engine condition) and a variable bypass flow which ensures the mass flow measurement nozzle always operates within its calibrated range. We demonstrate the method using two high-pressure (HP) NGV designs: an engine part with relatively uncoupled (in terms of internal loss) cooling rows; and a laser-sintered part with highly coupled cooling rows. We show that the individual-row flow capacity of a high-pressure nozzle guide vane (HPNGV) can be evaluated in the CCR in a single day to a 2σ precision of approximately 0.5% and a 2σ accuracy (bias) of 0.6%. The importance of performing individual-row capacity measurements is demonstrated: failure to scale flow capacity on a row-by-row basis introduces an error of 30% in the engine situation.

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Full Thermal Experimental Assessment of a Dendritic Turbine Vane Cooling Scheme

Cited by 7 publications

References 8 publications

Methods to Extract Underlying Boundary Conditions from Transient Metal Effectiveness Measurements

Methods to Extract Underlying Boundary Conditions from Transient Metal Effectiveness Measurements

Basic Aspects of Gas Turbine Heat Transfer

Method for Accurately Evaluating Flow Capacity of Individual Film-Cooling Rows of Engine Components

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