Title:

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

Creator:

Kianpour, Ehsan ; Sidik, Nor Azwadi Che

Subject:

gas turbine engine ; film-cooling ; combustor simulator ; trench hole ; dilution hole

Description:

The major effects of cylindrical and row trenched cooling holes with angles of alpha=30, beta=0, alpha=40, beta=0 and alpha=50, beta=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.

Place of publishing:

Koszalin

Publisher:

Publishing House of the Koszalin University of Technology

Date:

2021

Type:

artykuł w czasopiśmie

Format:

application/pdf

Language:

eng

Is part of:

Journal of Mechanical and Energy Engineering. Vol.5 (45), nr 2, s. 141-148

Rights:

Biblioteka Politechniki Koszalińskiej

Access rights:

internet

License:

Creative Commons BY 4.0