Heat transfer analyses of film-cooled HP turbine vane considering effects of swirl and hot streak

Wang, Zhiduo; Dian, Wang; Wang, Wenwen; Feng, Zhenping

doi:10.1016/j.applthermaleng.2018.07.044

Cited by 41 publications

(29 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For a typical time-mean temperature field in turbine inlet, the region with peak temperature locates near the midspan, while near the tip and hub of the vane, there are cool regions with lower temperatures. Temperature distortion factors (TDFs) are used to quantify temperature non-uniformity of hot streak [9]. There are several definitions of TDFs in current studies [9][10][11].…”

Section: Thermal Parameter Definitionmentioning

confidence: 99%

“…Temperature distortion factors (TDFs) are used to quantify temperature non-uniformity of hot streak [9]. There are several definitions of TDFs in current studies [9][10][11]. The overall TDF (OTDF) is a measure of the divergence of the hottest gas streak from the mean temperature [9].…”

Section: Thermal Parameter Definitionmentioning

confidence: 99%

“…However, in real turbine stage inlet boundary, the distributions of velocity, turbulence and temperature show large non-uniform both in radial and circumferential directions [8]. The non-uniform distributions of velocity and turbulence can be caused by intensive residual swirl flow at the exit of lean-burn combustor which is widely applied to ensure combustion stability and lower NOx emissions [9]. The non-uniform distributions of temperature named as hot streak (HS) is caused by the discrete nature of fuel nozzles and coolant flow of combustor lining [8].…”

Section: Introductionmentioning

confidence: 99%

“…The non-uniform distributions of temperature named as hot streak (HS) is caused by the discrete nature of fuel nozzles and coolant flow of combustor lining [8]. It is noted that a 25 K under prediction of the blade metal temperature can cause a halving of blade life span [9]. However, for typical military engines, the temperature ratio can reach up to 1.24 of the mass averaged temperature [10].…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

The Combined Influences of Hot Streak and Swirl on the Cooling Performances of C3X Guide Vane with or without TBCs

Shi¹,

Huang²,

Lu³

et al. 2021

Preprint

View full text Add to dashboard Cite

This paper studied the combined influences of the hot streak and swirl on the cooling performances of the NASA C3X guide vane coated with or without TBCs. The results show that: (1) Even under uniform velocity inlet conditions, the hot streak core can be stretched as it impinges the leading edge which causes higher heat load on the suction side of the forward portion. (2) The swirl significantly affects circumferential and radial migration of the hot streak core in the NGV passage. On the passage inlet plane, positive swirl leads to a hotter tip region on the suction side. In comparison, negative swirl leads to a hotter hub region on the pressure side. (3) Under the influence of swirl, migration of coolant improve the coverage of film cooling close to the midspan, while in the regions close to the hub and tip end-wall, the overall cooling performance decrease simultaneously. (4) In the regions with enough internal cooling, the cooling effectiveness increment is always larger than that in other regions. Besides, the overall cooling effectiveness increment decreases on the region covered by film cooling for the coated vane, especially in the region with negative local heat flux.

show abstract

Section: Thermal Parameter Definitionmentioning

confidence: 99%

Section: Thermal Parameter Definitionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

The Combined Influences of Hot Streak and Swirl on the Cooling Performances of C3X Guide Vane with or without TBCs

Shi¹,

Huang²,

Lu³

et al. 2021

Preprint

View full text Add to dashboard Cite

show abstract

“…The effects of the change of incident angle of swirl and the effects of radial transfer of vortex causes that the adhesion of the film coolant deteriorates, which reduces the cooling efficiency of film cooling and increase the temperature load of the vane surface. However, the radial angles towards the tip of the vane for film hole, negative incidence near the hub facilitates adhesion of the leading edge film coolant [14].…”

Section: Introductionmentioning

confidence: 99%

Influence of non-uniform inflow swirl and hot streak on turbine vane

Zhang

Chen

2020

View full text Add to dashboard Cite

The turbine vane bears higher and higher temperature of upstream flow with the higher requirements for the engine thrust. The heat resistance of turbine vanes is a severe problem for the lifetime of turbine vanes. Therefore, it is essential to study the flow field and heat transfer of the vane to find better ways to improve the heat resistance of the turbine and increase the thrust of the engine. To improve the efficiency of the turbine vanes, the present paper conducted researches on the heat transfer and the pressure loss of turbine vanes under different radius ratio of swirl and hot streak. The numerical applies CFD 3D RANs solver with the SST turbulent model to get the influence of non-uniform inflow velocity and temperature distribution on turbine vanes. The present numerical model utilizes turbine vane C3X. Considering the viscosity of the fluid causes shear stress on the wall, the paper set the boundary layers mesh in the numerical model. The size of the first boundary layer mesh is 10-6 m. The results show that the hot fluid on the suction side migrates towards the hub, and the hot fluid on the pressure side migrates towards the shroud while there are coupling effect of the swirl and hot streak. The larger the radius ratio of the hot streak and the swirl (RHS) is, the higher the temperature of the local high-temperature regions exist on the suction side of leading edge and the pressure side of the trailing edge is, and the higher the pressure loss is.Keywords High pressure turbine · RHS · The non-uniform flow · The pressure loss

show abstract

Numerical prediction of heat transfer characteristics on a turbine nozzle guide vane under various combustor exit hot‐streaks

Mansouri¹

2021

Heat Trans

View full text Add to dashboard Cite

The precise prediction of the aerothermal conditions at the outlet of modern combustors of aero engines is of primary interest in the aerothermal design of high‐pressure turbines. The use of high swirling flows to stabilize the flame in the new generation of lean‐burn combustors (LBCs) leads to shorter combustor length and high degrees of unsteady temperature. These aspects generate high levels of turbulence and complex temperature nonuniformity patterns at the combustor–turbine interface. Therefore, the nozzle guide vane (NGV) located at the interface exhibits a high inlet temperature gradient called a hot‐streak. The transport mechanism of the hot‐streak across the NGV needs to be decrypted to increase turbine service life and enhance its performance. In this context, the present study aims to examine numerically the effect of three new distorted hot‐streak gradients on the heat transfer characteristics across a turbine NGV. An innovative LBC is used to generate the three inlet hot‐streaks, which are highly swirled and distorted similar to real aero‐engine conditions. The use of such a generation approach avoids any simplification associated with uniform or circular contours that are widely used by researchers. A solid NGV cascade developed by NASA is adopted for the investigations. The results show significant differences in the thermal field on the cascade at each distorted thermal condition. The transport of the hot‐streak behaves differently under axial and swirl conditions. The presence of a swirl induces flow mixing and results in thermal load increasing on the cascade surfaces (NGV, hub, and shroud).

show abstract

Heat transfer analyses of film-cooled HP turbine vane considering effects of swirl and hot streak

Cited by 41 publications

References 18 publications

The Combined Influences of Hot Streak and Swirl on the Cooling Performances of C3X Guide Vane with or without TBCs

The Combined Influences of Hot Streak and Swirl on the Cooling Performances of C3X Guide Vane with or without TBCs

Influence of non-uniform inflow swirl and hot streak on turbine vane

Numerical prediction of heat transfer characteristics on a turbine nozzle guide vane under various combustor exit hot‐streaks

Contact Info

Product

Resources

About