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1

Cooling holes with different structures effects on coolant cross flow and heat transfer at the outlet of the combustion chamber

Kianpour Ehsan, Sidik Nor Azwadi Che

Journal of Mechanical and Energy Engineering

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2021

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Vol. 5, No 2

141--148

EN

The major effects of cylindrical and row trenched cooling holes with angles of 𝛼 = 30°, 𝛽 = 0°, 𝛼 = 40°, 𝛽 = 0° and 𝛼 = 50°, 𝛽 = 0° at BR=3.18 on the effectiveness of film cooling near the combustor end wall surface is an important subject to study in detail. In the current study, researchers used a FLUENT package 16/11 to simulate a 3-D model of a Pratt and Whitney gas turbine engine. In this research, RNG turbulence model K-ε model was used to analyze the flow behavior on the passage ways of internal cooling. In the combustor simulator, the dilution jets and cooling flow staggered in the streamwise direction and aligned in the spanwise direction as well. In comparison with the baseline case of cooling holes, the application of trenched hole near the end wall surface increased the effectiveness of film cooling up to 100% for different trench cases.

2

CT inspection of cooled turbine blades

Przysowa Radosław, Chalimoniuk Marek, Grzelka-Gajek Danuta, Shakalo Ruslan, Karpenko Artem

Journal of KONBiN

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2020

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Vol. 50, iss. 3

307--331

EN

To improve the engine efficiency by increasing the gas temperature, multi-layer cooling passages are applied in new designs of gas turbine blades. As a result, traditional non-destructive methods, which have been applied so far in the production control, became insufficient. The aim of this manuscript is to develop an inspection method for cooling passages of turbine blades, which would be helpful in detecting manufacturing defects of blades and their operational failures. GE v/tome/x/m 300 was applied to conduct dimensional control and check the interior of two types of turbine blades from turboshaft engines. The procedure for selecting X-ray parameters was suggested. The thickness of walls in the selected cross-section was measured with the accuracy of 0.01 mm, and the selected manufacturing defects of cooling passages were identified.

PL

W celu zwiększenia sprawności silników przez podniesienie temperatury gazów, w nowych konstrukcjach łopatek turbin gazowych stosuje się wielowarstwowe zespoły kanałów chłodzących. W efekcie, tradycyjne metody nieniszczące, stosowane dotychczas w kontroli produkcji stają się niewystarczające. Celem pracy jest opracowanie metodyki inspekcji kanałów chłodzących łopatek turbin do wykrywania wad produkcyjnych łopatek oraz ich uszkodzeń eksploatacyjnych. Zastosowano tomograf GE v/tome/x/m 300 do kontroli wymiarowej i sprawdzenia poprawności wykonania wnętrza dwóch typów łopatek turbiny silnika turbowałowego. Zaproponowano procedurę doboru parametrów prześwietlania. Zmierzono grubość ścian w wybranych przekrojach z dokładnością 0,01 mm oraz zidentyfikowano wybrane wady produkcyjne kanałów chłodzących.

3

A detailed study of row-trenched holes at the combustor exit on film-cooling effectiveness

Kianpour Ehsan, Sidik Nor Azwadi Che

Mechanics and Mechanical Engineering

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2019

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Vol. 23, nr 1

246--252

EN

To analyse the effects of cylindrical- and rowtrenched cooling holes with an alignment angle of 90 degrees on the film-cooling effectiveness near the combustor end wall surface at a blowing ratio of 3.18, the current research was done. This research included a 3D representation of a Pratt and Whitney gas turbine engine, which was simulated and analysed with a commercial finite volume package Fluent 6.2.26. The analysiswas done with Reynolds-averaged Navier-Stokes turbulence model on internal cooling passages. This combustor simulator was combined with the interaction of two rows of dilution jets, which were staggered in the streamwise direction and aligned in the spanwise direction. In comparison with the baseline case of cooling holes, using row-trenched hole near the end wall surface increased the film-cooling effectiveness 44% in average.

4

Mean and turbulent thermal fields due to film cooling via an eddy heat diffusivity closure

Karcz M.

TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk

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2006

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Vol. 10, No 4

377-390

EN

The two-equation level of turbulent heat flux modelling is considered for application in film cooling instead of the turbulent Prandtl number concept. The investigations involve numerical analysis of mean and fluctuating temperature fields near the coolant injection inlet. The results of the implemented coupled v2- f-k0-E0 model are compared with measurement data for a flat plate cooled with compound angle orientation of discrete in-jection holes. The results of numerical analysis agree very well with the experimental data. The coupled model offers a detailed picture of gas turbine cooling problems without using time-consuming, inherently unsteady models.