Multi-Field Coupling Analysis on the Film-Cooling of a Turbine Guide Vane

2013 ◽  
Author(s):  
Zhan Wang ◽  
Jian-Jun Liu ◽  
Chao Zhang
Keyword(s):  
Thermal Stress ◽  
High Temperature ◽  
Creep Strain ◽  
Film Cooling ◽  
Guide Vane ◽  
Temperature Gradients ◽  
Coupling Method ◽  
Coupling Analysis ◽  
Field Coupling ◽  
Turbine Guide Vane

Multi-field coupling method is used to assess the film-cooling properties of a turbine guide vane. The creep strain is used to evaluate the film-cooling validness, in order to take into account the effects of both temperature and thermal stress. Because of the high temperature gradients, thermal stress is much higher than the aerodynamic stress in a guide vane. It is found that large creep strain may be generated where the cooling holes locate, especially near the shower-head and upper endwall. For the shower-head film cooling, three types of holes (cylindrical, fan-shaped, double-jet) were studied. The results showed that fan-shaped and double-jet holes were suitable for the cooling of the shower-head of the guide vane. For the endwall, adding more cooling holes could reduce the area of high temperature and also reduce the creep strain.

scholarly journals Multi-field coupling analysis on the film-cooling with transverse and arched trenches

2019 ◽  
Vol 14 (1) ◽  
pp. JTST0012-JTST0012
Author(s):  
Zhan WANG ◽  
Chao ZHANG ◽  
Wen-jing DU ◽  
Shu-jia LI
Keyword(s):  
Film Cooling ◽  
Coupling Analysis ◽  
Field Coupling

scholarly journals Numerical Investigation of Single-Row Double-Jet Film Cooling of a Turbine Guide Vane under High-Temperature and High-Pressure Conditions

Energies ◽  
2022 ◽  
Vol 15 (1) ◽  
pp. 287
Author(s):  
Jin Hang ◽  
Jingzhou Zhang ◽  
Chunhua Wang ◽  
Yong Shan
Keyword(s):  
Film Cooling ◽  
Guide Vane ◽  
Suction Surface ◽  
Positive Potential ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness ◽  
Injection Angle ◽  
Jet In Crossflow ◽  
Cooling Enhancement ◽  
Turbine Guide Vane

Single-row double-jet film cooling (DJFC) of a turbine guide vane is numerically investigated in the present study, under a realistic aero-thermal condition. The double-jet units are positioned at specific locations, with 57% axial chord length (Cx) on the suction side or 28% Cx on the pressure side with respect to the leading edge of the guide vane. Three spanwise spacings (Z) in double-jet unit (Z = 0, 0.5d, and 1.0d, here d is the film hole diameter) and four spanwise injection angles (β = 11°, 17°, 23°, and 29°) are considered in the layout design of double jets. The results show that the layout of double jets affects the coupling of adjacent jets and thus subsequently changes the jet-in-crossflow dynamics. Relative to the spanwise injection angle, the spanwise spacing in a double-jet unit is a more important geometric parameter that affects the jet-in-crossflow dynamics in the downstream flowfield. With the increase in the spanwise injection angle and spanwise spacing in the double-jet unit, the film cooling effectiveness is generally improved. On the suction surface, DJFC does not show any benefit on film cooling improvement under smaller blowing ratios. Only under larger blowing ratios does its positive potential for film cooling enhancement start to show. Compared to the suction surface, the positive potential of the DJFC on enhancing film cooling effectiveness behaves more obviously on the pressure surface. In particular, under large blowing ratios, the DJFC plays dual roles in suppressing jet detachment and broadening the coolant jet spread in a spanwise direction. With regard to the DJFC on the suction surface, its main role in film cooling enhancement relies on the improvement of the spanwise film layer coverage on the film-cooled surface.

scholarly journals An Enhanced Flow-Thermo-Structural Modeling and Validation for the Integrated Analysis of a Film Cooling Nozzle Guide Vane

Energies ◽  
2019 ◽  
Vol 12 (14) ◽  
pp. 2775 ◽  
Author(s):  
Peng Guan ◽  
Yan-Ting Ai ◽  
Cheng-Wei Fei
Keyword(s):  
Thermal Stress ◽  
Film Cooling ◽  
Guide Vane ◽  
Integrated Design ◽  
Integrated Analysis ◽  
Inlet Temperature ◽  
Temperature Sensitive ◽  
Computational Accuracy ◽  
Nozzle Guide Vane ◽  
Nozzle Guide

The target of this paper is to develop an enhanced flow-thermo-structural (FTS) model with high computational accuracy, to perform the integrated analysis of film cooling nozzle guide vane (NGV). An efficient turbulence model and weak spring approach are utilized in the enhanced FTS model. In respect of the power balance principle of aeroengine rotor shaft and temperature test of a typical combustor, the mean temperature inlet and five normalization temperature curves were confirmed, respectively. The temperature-sensitive paint (TSP) technology was used to verify the numerical simulation. From this study, we find that the predicted temperature caters for the TSP test well, between which the maximum error is less than 6%, and the maximum thermal stress is 758 MPa around the hole edges and the location of stress concentration keeps the consistency with that of the cracks. The maximum thermal stress increases by 10% with the increasing inlet temperature and reduces by about 16% with the shifting of flame peak from the outer to inner hub. The prediction provides general information on the initiation of cracks on a vane segment. The developed enhanced FTS model is validated to be workable and precise in the integrated analysis of film cooling NGV. The efforts of this study provide an integrated analysis approach of film cooling NGV and are promising to provide guidance for the integrated design of film cooling components besides NGV.

Towards Efficient CFD-Simulations of Engine Like Turbine Guide Vane Film Cooling

2011 ◽  
Author(s):  
Andreas Bradley ◽  
Hossein Nadali Najafabadi ◽  
Matts Karlsson ◽  
Joakim Wren ◽  
Esa Utriainen ◽  
...  
Keyword(s):  
Film Cooling ◽  
Guide Vane ◽  
Cfd Simulations ◽  
Turbine Guide Vane

Reverse-Pass Cooling Systems for Improved Performance

2014 ◽  
Vol 136 (11) ◽  
Author(s):  
Benjamin Kirollos ◽  
Thomas Povey
Keyword(s):  
Heat Transfer ◽  
Heat Exchanger ◽  
Film Cooling ◽  
Guide Vane ◽  
Temperature Gradients ◽  
Pass System ◽  
Forward Pass ◽  
Counter Current ◽  
Lateral Temperature ◽  
Current Arrangement

Total heat transfer between a hot and a cold stream of gas across a nonporous conductive wall is greatest when the two streams flow in opposite directions. This counter-current arrangement outperforms the co-current arrangement because the mean driving temperature difference is larger. This simple concept, whilst familiar in the heat exchanger community, has received no discussion in papers concerned with cooling of hot-section gas turbine components (e.g., turbine vanes/blades, combustor liners, afterburners). This is evidenced by the fact that there are numerous operational systems which would be significantly improved by the application of “reverse-pass” cooling. That is, internal coolant flowing substantially in the opposite direction to the mainstream flow. A reverse-pass system differs from a counter-current system in that the cold fluid is also used for film cooling. Such systems can be realized when normal engine design constraints are taken into account. In this paper, the thermal performance of reverse-pass arrangements is assessed using bespoke 2D numerical conjugate heat transfer models, and compared to baseline forward-pass and adiabatic arrangements. It is shown that for a modularized reverse-pass arrangement implemented in a flat plate, significantly less coolant is required to maintain metal temperatures below a specified limit than for the corresponding forward-pass system. The geometry is applicable to combustor liners and afterburners. Characteristically, reverse-pass systems have the benefit of reducing lateral temperature gradients in the wall. The concept is demonstrated by modeling the pressure and suction surfaces of a typical nozzle guide vane with both internal and film cooling. For the same cooling mass flow rate, the reverse-pass system is shown to reduce the peak temperature on the suction side (SS) and reduce lateral temperature gradients on both SS and pressure side (PS). The purpose of this paper is to demonstrate that by introducing concepts familiar in the heat exchanger community, engine hot-section cooling efficiency can be improved whilst respecting conventional manufacturing constraints.

Film cooling on a turbine guide vane: A numerical analysis with a multigrid technique

2001 ◽  
Vol 215 (1) ◽  
pp. 39-53 ◽  
Author(s):  
S Sarkar ◽  
K Das ◽  
D Basu
Keyword(s):  
Heat Transfer ◽  
Film Cooling ◽  
Guide Vane ◽  
Navier Stokes ◽  
Time Stepping ◽  
Flow And Heat Transfer ◽  
Local Time Stepping ◽  
Turbine Guide Vane ◽  
Nozzle Guide ◽  
Internal Convection

The flow and heat transfer due to film cooling over a turbine nozzle guide vane, which was also cooled by internal convection, were numerically analysed under engine conditions. The time-dependent, two-dimensional, mass-averaged, Navier-Stokes (N-S) equations are solved in the physical plane based on the four-stage Runge-Kutta algorithm in the finite volume formulation. Local time stepping, variable coefficient implicit residual smoothing and a full multigrid technique have been implemented to accelerate the steady state calculations. Turbulence was simulated by the algebraic Baldwin-Lomax (B-L) model. The computed heat transfer distributions with film cooling in conjunction was successful in describing the coolant behavior over the curved suction and pressure surfaces of a turbine blade for varying blowing and temperature ratios.

scholarly journals Artificial intelligence aided design of film cooling scheme on turbine guide vane

2020 ◽  
Vol 9 (4) ◽  
pp. 344-354
Author(s):  
Dike Li ◽  
Lu Qiu ◽  
Kaihang Tao ◽  
Jianqin Zhu
Keyword(s):  
Artificial Intelligence ◽  
Film Cooling ◽  
Guide Vane ◽  
Turbine Guide Vane ◽  
Aided Design

A New Method to Calculate the Coolant Requirements of a High-Temperature Gas Turbine Blade

2005 ◽  
Vol 127 (1) ◽  
pp. 191-199 ◽  
Author(s):  
Leonardo Torbidoni ◽  
J. H. Horlock
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Film Cooling ◽  
Guide Vane ◽  
Coolant Flow ◽  
Computational Method ◽  
Inlet Temperature ◽  
Film Cooling Effectiveness ◽  
Cooling Flow ◽  
High Temperature Gas

Earlier papers by the first author have described a computational method of estimating the cooling flow requirements of blade rows in a high-temperature gas turbine, for convective cooling alone and for convective plus film cooling. This method of analysis and computation, when applied to the whole blade chord was compared to a well-known semi-empirical method. In the current paper, a more sophisticated method is developed from the earlier work and is used to calculate the cooling flow required for a nozzle guide vane (the first blade row) of a high-temperature gas turbine, with given inlet gas temperature and coolant inlet temperature. Now the heat flux through an elementary cross-sectional area of the blade, at given spanwise (y) and chordwise (s) locations, is considered, with a guessed value of the elementary coolant flow [as a fraction dΨs of the external gas flow]. At the given s, integration along the blade length gives the blade metal temperatures at the outer and inner walls, Tbgy and Tbcly. If the value of Tbg at the blade tip y=H is assumed to be limited by material considerations to Tbg,max then the elementary coolant flow rate may be obtained by iteration. Summation along the chord then gives the total coolant flow, for the whole blade. Results using the method are then compared to a simpler calculation applied to the whole blade, which assumes chordwise constant temperatures and constant selected values of cooling efficiency and film-cooling effectiveness.

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