Aerodynamic and heat transfer design optimization of internally cooling turbine blade based different surrogate models

Yu, Kun; Yang, Xi; Yue, Zhufeng

doi:10.1007/s00158-010-0583-x

Cited by 33 publications

(12 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The y-plus values in the tip region are at the range of 30-100, and it can get an accurate result according to the study of Kuahai Yu et al 35 Meanwhile, the y-plus values at the range of 30-300 are reliable in the standard wall function.…”

Section: Grid Independence Studymentioning

confidence: 92%

“…In order to improve the accuracy of calculation results, the grids of blade tip and film cooling holes are meshed, respectively (Figure 4). The y-plus values in the tip region are at the range of 30-100, and it can get an accurate result according to the study of Kuahai Yu et al 35 Meanwhile, the y-plus values at the range of 30-300 are reliable in the standard wall function.…”

Section: Grid Independence Studymentioning

confidence: 92%

See 1 more Smart Citation

Investigation on heat transfer of a rotor blade tip with various film cooling holes arrangements and groove depths

Tong

Gou

et al. 2015

Advances in Mechanical Engineering

Self Cite

View full text Add to dashboard Cite

In this article, the effects of film cooling holes arrangement and groove depth on the heat transfer and film cooling performance of blade tip are investigated. For this numerical research, a high-pressure turbine blade with the squealer tip is applied, and the tip clearance is given to be 0.8 mm (1% of the blade span). Simultaneously, a typical tip cooling technology of film holes in the groove floor is used. The number of film holes is fixed at 10, and two kinds of holes arrangements are considered: (1) equidistance distribution and (2) dense distribution near the leading edge. Three groove depths are studied with the values of 1.5, 2.0, and 2.5 mm (1.875%, 2.5%, and 3.125% of the blade span, respectively). The results show that the area-averaged film cooling effectiveness is higher when the holes distribute densely near the leading edge, and the cooling effect of the groove depth with 2.0 mm is obviously high compared with the other two depths.

show abstract

Section: Grid Independence Studymentioning

confidence: 92%

Section: Grid Independence Studymentioning

confidence: 92%

Investigation on heat transfer of a rotor blade tip with various film cooling holes arrangements and groove depths

Tong

Gou

et al. 2015

Advances in Mechanical Engineering

Self Cite

View full text Add to dashboard Cite

show abstract

“…the blade tip), where the fluid flow is turbulent. For the prism elements, the height of first mesh is 0.01 and the number of layers is more than 11, which ensures that the wall grid y + values (30‒80) can satisfy the requirement of applied turbulent model (Yu et al , 2011). To improve both the calculation precision and efficiency, it is essential to perform a grid independence analysis (Figure 4) (Arisi et al , 2015).…”

Section: Computation Detailsmentioning

confidence: 99%

Numerical investigation of high pressure turbine blade tip-shaping effects on the aerothermal and dynamic performance

Tong¹,

Gou²,

Li³

et al. 2019

MMMS

Self Cite

View full text Add to dashboard Cite

Purpose In order to improve the engine reliability and efficiency, an effective way is to reform the turbine blade tip conformation. The paper aims to discuss this issue. Design/methodology/approach The present research provides several novel tip-shaping structures, which are considered to control the blade tip loss. Four different tip geometries have been studied: flat tip, squealer tip, flat tip with streamwise ribs and squealer tip with streamwise ribs. The tip heat transfer and leakage flow are both analyzed in detail, for example the tip heat transfer coefficient, tip flow and local pressure distributions. Findings The results show that the squealer seal and streamwise rib can reduce the tip heat transfer and leakage loss, especially for the squealer tip with streamwise ribs. The tip and near-tip flow patterns at the different locations of axial chord reflect that both the squealer seal and streamwise rib structure can control the tip leakage flow loss. In addition, the analysis of the aerodynamic parameters (the static pressure and turbine efficiency) also indicates that the squealer tip with streamwise ribs obtains the highest adiabatic efficiency with an increase of 2.34 percent, compared with that of the flat tip case. Originality/value The analysis of aerothermal and dynamic performance can provide a reference for the blade tip design and treatment.

show abstract

“…Since the 1970s, computer-aided engineering has been widely used for designing the product and optimization with an affordable computer speed, storage, and accuracy. With high demand in the degree of accuracy and achieving convergence for the complicated-structure of the gas turbine blade to predict the heat transfer coefficients (HTC), the expenditure for performing the simulation has been complicated due to a high computational resource [1]. As a consequence, it is essential to find a surrogate model in order to overcome the problem of computational cost in engineering applications.…”

Section: Introductionmentioning

confidence: 99%

Multi-Fidelity Surrogate Models for Predicting Averaged Heat Transfer Coefficients on Endwall of Turbine Blades

et al. 2021

View full text Add to dashboard Cite

This paper proposes a multi-fidelity surrogate (MFS) model for predicting the heat transfer coefficient (HTC) on the turbine blades. First, the low-fidelity (LF) and high-fidelity (HF) surrogates were built using LF-data from numerical simulation and HF-data from an experiment. To evaluate the prediction by these two surrogates, the averaged HTC distribution on the endwall of the gas turbine blade predicted by these two surrogates was compared for input variables as Reynolds number (Re) and boundary layer (BL) thickness. This shows that the prediction by LF surrogate is saturated with an increase in Re, while has monotonic behavior with an increase in BL thickness, which is contrary in general. The prediction by HF surrogate is linear with Re and is increased with BL thickness up to 30 mm and then decreased after 30 mm. Following this, a one-dimensional projection of the two-dimensional HTC distribution was presented to show the prediction tendency of the surrogates by varying the Re and fixing the BL thickness, and vice versa. Second, the MFS was built by combining the LF and HF data. The HTC distribution by the MFS model for the same input variables was shown with the HF data points. It is observed that the prediction by MFS is agreed well with the high-fidelity data. The MFS’s one-dimensional projection of the two-dimensional HTC distribution was compared with the LF surrogate prediction by varying the Re and fixing the BL thickness, and vice versa. This shows that the MFS model has more variations due to the included LF data. It is worth to mention that the averaged HTC distribution with an increase in boundary layer thickness predicted by the MFS is agreed well with the LF and HF data in the available dataset and has a large confidence interval between 30 and 50 mm due to the unavailable data in the specified range. To check the MFS accuracy, the root-mean-square error (RMSE) and error rate were evaluated to compare with the experimental uncertainty for a wide range of high-fidelity data. The present study shows that MFS would be expected to be an effective model for saving computing time and experimental costs.

show abstract

Aerodynamic and heat transfer design optimization of internally cooling turbine blade based different surrogate models

Cited by 33 publications

References 16 publications

Investigation on heat transfer of a rotor blade tip with various film cooling holes arrangements and groove depths

Investigation on heat transfer of a rotor blade tip with various film cooling holes arrangements and groove depths

Numerical investigation of high pressure turbine blade tip-shaping effects on the aerothermal and dynamic performance

Multi-Fidelity Surrogate Models for Predicting Averaged Heat Transfer Coefficients on Endwall of Turbine Blades

Contact Info

Product

Resources

About