Heat transfer and film-cooling for the endwall of a first stage turbine vane

Thole, Karen A.; Knost, Daniel G.

doi:10.1016/j.ijheatmasstransfer.2005.07.036

Cited by 70 publications

(11 citation statements)

References 36 publications

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“… 15. Predicted streamlines on hub waii expected, there is no difference in the flow pattem for the two cases.…”

mentioning

confidence: 82%

“…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]. Hartland et al [17].…”

Section: Review Of Past Literaturementioning

confidence: 99%

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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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“… 15. Predicted streamlines on hub waii expected, there is no difference in the flow pattem for the two cases.…”

mentioning

confidence: 82%

Section: Review Of Past Literaturementioning

confidence: 99%

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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“…The result is in agreement with studies of the impact of combustor-turbine interface leakage flow at low momentum flux ratios, several of which report increased secondary flows. 20,31,32…”

Section: Effect Of Vane Potential Field Coolant Mass Flux Ratio Andmentioning

confidence: 99%

“…For the example with cooling flow at a low mass flux ratio (Figure 14 flow at low momentum flux ratios, several of which report increased secondary flows. 20,31,32 High mass flux ratio with corresponding high momentum flux ratio. As discussed previously, rows of discrete cooling holes blowing at moderate mass and momentum flux ratios can be used to boost near-wall momentum and reduce secondary flows.…”

Section: Effect Of Vane Potential Field Coolant Mass Flux Ratio Andmentioning

confidence: 99%

Improving turbine endwall cooling uniformity by controlling near-wall secondary flows

Thomas

Povey

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, we propose a design philosophy for cooling high-pressure nozzle guide vane endwalls, which exploits the momentum of cooling jets to control vane secondary flows thereby improving endwall cooling uniformity. The impact of coolant-to-mainstream pressure ratio, hole inclination angle, hole diameter, vane potential field, and overall mass flux ratios are considered. Arguments are developed by examining detailed experimental studies conducted in a large-scale low-speed cascade tunnel with engine-realistic combustor geometry and turbulence profiles. Computational fluid dynamics predictions validated by the same are used to extend the parameter space. We show that the global flow field is highly sensitive to the inlet total pressure profile, which in turn can be modified by introducing relatively low mass flow rates of cooling gas at engine realistic coolant-to-mainstream pressure ratios and mass flux ratios. This interaction effect must be understood for successful design of optimised endwall cooling schemes, an effect which is not sufficiently emphasized in much of the literature on this topic. Design guidelines are given that we hope will be of use in industry.

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“…Friedrichs et al (1996Friedrichs et al ( ) (1997Friedrichs et al ( ) (1999 presented detailed measurements of different cooling hole patterns. Blair (1974), and Granser and Schulenberg (1990), and Thole and Knost (2005) investigated the performance of a continuous cooling slot upstream of the vane. Their studies showed a significant variation of cooling effectiveness across the pitch, with the majority of cooling being convected towards the suction side.…”

Section: Vane Coolingmentioning

confidence: 99%

Development and Aerothermal Investigation of Integrated Combustor Vane Concept

Jacobi

Rosic

2015

Volume 2A: Turbomachinery

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This paper presents the development and aerothermal investigation of the Integrated Combustor Vane concept for power generation gas turbines with individual can combustors. In this novel concept, first introduced in 2010 [1], the conventional Nozzle Guide Vanes (NGVs) are removed and flow turning is achieved by vanes that extend the combustor walls. The concept is developed using the inhouse CFD code TBLOCK. Aerothermal experiments are conducted using a modular high speed linear cascade, designed to model the flow at the combustor-vane interface. The facility comprises two can combustor transition ducts and either four Conventional Vanes (CVs) or two Integrated Vanes (IVs). The experimental study validates the linear CFD-simulations of the IV development. Annular full stage CFD-simulations, used to evaluate aerodynamics, heat transfer and stage efficiency, confirm the trends of the linear numerical and experimental results and thus demonstrate the concept’s potential for real gas turbine applications. Results show a reduction of the total pressure loss coefficient at the exit of the stator vanes by more than 25% due to a reduction in profile- and endwall-loss. Combined with an improved rotor performance these aerodynamic benefits result in a gain in stage efficiency of above 1%, illustrated by unsteady stage simulations. A distinct reduction in HTC levels on vane surfaces, in the order of 25%–50%, and endwalls is observed and attributed to an altered state of boundary layer thickness. The development of IV’s endwall- and LE-cooling geometry shows a superior surface coverage of cooling effectiveness, and the cooling requirements for the first vane are expected to be halved. Moreover, by halving the number of vanes, simplifying the design and eliminating the need for vane LE film cooling, manufacturing and development costs can be significantly reduced.

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Heat transfer and film-cooling for the endwall of a first stage turbine vane

Cited by 70 publications

References 36 publications

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

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

Improving turbine endwall cooling uniformity by controlling near-wall secondary flows

Development and Aerothermal Investigation of Integrated Combustor Vane Concept

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