Endwall heat transfer measurements in an annular cascade of nozzle guide vanes at engine representative Reynolds and Mach numbers

Spencer, M. C.; Jones, T. V.; Lock, Gary

doi:10.1016/0142-727x(95)00102-v

Cited by 30 publications

(10 citation statements)

References 3 publications

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“…Having knowledge of the heat transfer that occurs on the surface of the turbine endwalls and how that effects the vanes would be very beneficial to accurately creating a cooling system for the vane and endwall. Because of this many different experiments have been done to create a better understanding the effects that heated endwalls have on the overall heat transfer in Spencer et al[22] performed heat transfer measurements on the endwalls of a large annular cascade. They used a transient liquid crystal technique to measure the heat transfer over the endwall of the cascade.…”

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confidence: 99%

Experimental Heat Transfer Distributions Over an Aft Loaded Vane With a Large Leading Edge at Very High Turbulence Levels

Varty

Ames

2016

Volume 8: Heat Transfer and Thermal Engineering

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Vane heat transfer distributions have been acquired on an aft loaded vane with a large leading edge over a range of turbulence conditions and across a range of Reynolds numbers. The large leading edge was designed to reduce heat transfer levels around the vane stagnation region and provide an opportunity to internally cool the region using a double wall cooling method. Heat transfer measurements were acquired in a linear cascade using a constant heat flux technique. The cascade was designed in a four vane, three full passage configuration with inlet bleeds flows and exit tailboards shaped along streamlines. Heat transfer measurements were acquired at exit chord Reynolds numbers of 500,000, 1,000,000, and 2,000,000 over seven turbulence conditions. The turbulence conditions included a low turbulence condition (Tu ≈ 0.7%), a small grid (M = 3.175 cm) at far and near locations (Tu ≈ 3.5% & 7.9%), a larger grid (Tu ≈ 8.0%), an aero-combustor closely coupled to the cascade and with a decay spool in between (Tu ≈ 13.5% and 9.3%) as well as with a new very high turbulence generator (Tu ≈ 17.4%). Heat transfer levels in the stagnation region are correlated in terms of approach flow Reynolds number and turbulence conditions and compared with recent large cylindrical leading edge test surface data using the TRL parameter. The surface heat transfer measurements are presented at different Reynolds numbers in terms of Stanton number based on exit conditions. These comparisons provide useful information on the level of turbulence augmentation in laminar regions of the flow as well as the onset location and length of transition. Midspan surface static pressure distributions were acquired at all the conditions and were used as a basis to determine experimental isentropic Mach number distributions. These data are reported in part but were also used to help generate the free-stream boundary condition for a boundary layer calculation. Predictive comparisons generated from boundary layer calculations (STAN7) using an algebraic turbulence model (ATM) and a well-known transition model (Mayle) are provided. At low turbulence levels the close comparisons provide confidence in the experimental technique. At higher turbulence levels the comparisons may provide a better indication of the physics of response of vane heat transfer to the external turbulence. These data are expected to help clarify the physics of vane heat transfer at very high turbulence levels.

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confidence: 99%

Experimental Heat Transfer Distributions Over an Aft Loaded Vane With a Large Leading Edge at Very High Turbulence Levels

Varty

Ames

2016

Volume 8: Heat Transfer and Thermal Engineering

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“…The work by Harvey and Jones [5]. Gaugler and Rus-.sell [8], and Spencer et al [9] is an example of such analysis. Other work done in this area includes the work by Harvey et al [10], Kang and Thole [II], and Kang et al [12] on the effects of the secondary flows on end wall heat transfer characteristics; the work by Friedrich et al [13] and Knost and Thole [14,15] on the effectiveness of end wall cooling; the work by Harvey et al [16].…”

Section: Review Of Past Literaturementioning

confidence: 96%

Effect of Simulated Combustor Temperature Nonuniformity on HP Vane and End Wall Heat Transfer: An Experimental and Computational Investigation

Qureshi

Beretta

Povey

2010

Journal of Engineering for Gas Turbines and Power

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This paper presents experimental measurements and computational predictions of surface and end wall heat transfer for a high-pressure (HP) nozzle guide vane operating as part of a full HP turbine stage in an annular rotating turbine facility, with and without inlet temperature distortion (hot streaks). A detailed aerodynamic survey of the vane surface is also presented. The test turbine was the unshrouded MTI turbine, installed in the Tut bine Test Facility (previously called Isentropic Light Piston Facility) at QinetiQ, Farnborough, UK. This is a short-duration facility, which simulates engine-representative M, Re, nondimensional speed, and gas-to-wall temperature ratio at the turbine inlet. The facility has recently been upgraded to incorporate an advanced second-generation combustor simulator, capable of simulating well-defined, aggressive temperature profiles in both the radial and circumferential directions. This work forms part of the pan-European research program, TATEF ¡I. Measurements of HP vane and end wall heat transfer obtained with inlet temperature distortion are compared with results for uniform inlet conditions. Steady and unsteady computational fiuid dynamics (CFD) predictions have also been conducted on vane and end wall surfaces using the Rolls-Royce CFD code HYDRA to complement the analysis of experimental results. The heat transfer measurements presented in this paper are the first of their kind in that the temperature distortion is representative of an extreme cycle point, and was simulated with good periodicity and with well-defined boundary conditions in the test turbine.

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“…Some other studies have also analysed the end wall heat transfer measurements at elevated turbulence levels. 45 Spencer et al 46 made end wall heat transfer measurements at an inlet free stream turbulence level of 9%, but were unable to compare with the lower turbulence levels due to lack of relevant data. Khalatov et al 47 analysed the augmentation of heat transfer due to high free stream turbulence along the end wall.…”

Section: Heat Transfer Through Turbine End Wallmentioning

confidence: 99%

“…66 Currently, both methods are used to simulate heat transfer within turbine components. 67 Most existing studies 46 compare a CHT simulation for a turbine cascaded to an uncoupled approach. These studies concluded that, 68 for complex geometries and regions of low velocity or flow separation, there is negligible coupling between the flow field and thermal field of a solid leading to incorrect results.…”

Section: Conjugate Heat Transfer Modelmentioning

confidence: 99%

Modelling of heat transfer and fluid flow in the hot section of gas turbines used in power generation: A comprehensive survey

2018

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Summary Power generation is one of the major industries or businesses globally. Although, at present, a major attention has been paid towards the sustainable energy technologies, both gas and steam turbines are still heavily used in the power generation sector worldwide. Usually, gas turbines are used to drive an electrical power generator in simple systems, or they are used in combined cycle plants together with steam turbines. This paper presents a comprehensive review on modelling of heat transfer and fluid flow in hot section of gas turbines used in the power generation sector. Visibly, heat transfer and fluid flow characteristics directly affect the thermal efficiency and the overall performance of the gas turbines. Hence, existing models relating to heat transfer and fluid flow inside gas turbines are discussed in detail. Primarily, methods relating to the first principle modelling, empirical modelling, and finite element modelling are reviewed comprehensively, and then, a discussion is provided together with a comparison among models in terms of their advantages and disadvantages. Moreover, some existing issues such as the environmental impact are discussed which still remain as challenges to the power generation industry together with some of the possible future directions for improvements.

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Endwall heat transfer measurements in an annular cascade of nozzle guide vanes at engine representative Reynolds and Mach numbers

Cited by 30 publications

References 3 publications

Experimental Heat Transfer Distributions Over an Aft Loaded Vane With a Large Leading Edge at Very High Turbulence Levels

Experimental Heat Transfer Distributions Over an Aft Loaded Vane With a Large Leading Edge at Very High Turbulence Levels

Effect of Simulated Combustor Temperature Nonuniformity on HP Vane and End Wall Heat Transfer: An Experimental and Computational Investigation

Modelling of heat transfer and fluid flow in the hot section of gas turbines used in power generation: A comprehensive survey

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