Related Papers
Applied Mechanics and Materials
The Use of Compound Cooling Holes for Film Cooling at the End Wall of Combustor Simulator
2014 •
Shahin Salimi
Gas turbine cooling can be classified into two different schemes; internal and external cooling. In internal cooling method, the coolant provided by compressor is forced into the cooling flow circuits inside turbine components. Meanwhile, for the external cooling method, the injected coolant is directly perfused from coolant manifold to save downstream components against hot gases. Furthermore, in the latter coolant scheme, coolant is used to quell the heat transfer from hot gas stream to a component. There are several ways in external cooling. Film cooling is one of the best cooling systems for the application on gas turbine blades. This study concentrates on the comparison of experimental, computational and numerical investigations of advanced film cooling performance for cylindrical holes at different angles and different blowing ratios in modern turbine gas.
International Journal of Turbo and Jet Engines
Full Coverage Discrete Hole Film Cooling: The Influence of Hole Size
1985 •
Gordon Andrews
Film Cooling Effectiveness Using Cylindrical and Compound Cooling Holes at the End Wall of Combustor Simulator
A numerical 3-D simulation has been performed to investigate fluid flow and heat transfer characteristics of a film cooling injected through cylindrical and compound angle oriented holes with alignment angle of 30 degree adjacent to the end wall surface for a Pratt and Whitney gas turbine engine by ANSYS FLUENT 14.0. The results indicate that employing compound angle cooling holes injection gives much better protection to the components rather that obtained when simple angle cooling holes were used. Copyright © 2014 Penerbit Akademia Baru - All rights reserved.
Compound Cooling Holes for Film Cooling of Combustor Simulator: A Review
2015 •
Ehsan Kianpour
Gas turbine cooling can be classified into two different schemes; internal and external cooling. In the internal cooling method, the coolant provided by compressor is forced into the cooling flow circuits inside turbine components. Meanwhile, for the external cooling method, the injected coolant is directly perfused from coolant manifold to save downstream components from hot gases. Furthermore, in the latter coolant scheme, coolant is used to quell the heat transfer from hot gas stream to a component. There are several ways in external cooling. Film cooling is one of the best cooling systems for the application on gas turbine blades. This study concentrates on the comparison of experimental, computational and numerical investigations of advanced film cooling performance for cylindrical holes at different angles and different blowing ratios in modern gas turbines. Copyright © 2014 Penerbit Akademia Baru All rights reserved.
International Journal of Geomechanics
Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor
2015 •
Ehsan Kianpour
This research was done to analyze the effects of two different blowing ratios of BR=1.25 and BR=3.18 on the film cooling effectiveness at the combustor outlet, whereas the cylindrical and row trench holes with alignment angle of +60 degrees were considered. In the current research, a three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analyzed with a commercial finite volume package FLUENT 6.2.26. This study has been carried out with Reynolds-averaged Navier-Stokes turbulence model (RANS) on internal cooling passages. The combustor combines the interaction of two rows of dilution jets, which are staggered in the stream-wise direction and aligned in the span-wise direction, with that of film cooling along the combustor liner walls. The entire findings of the study showed that trenched holes performed much more efficiently at both blowing ratios, especially at BR=3.18.
Heat and Mass Transfer
Numerical investigations of cooling holes system role in the protection of the walls of a gas turbine combustion chamber
2011 •
ahlem ali
WIT transactions on engineering sciences
Effect Of Blowing Rate On The Film CoolingCoverage On A Multi-holed Plate: Application OnCombustor Walls
2004 •
Vladimir Sabelnikov
Multi-holed film cooling systems are the most effective and widely used cooling techniques applied to gas turbine blades and combustor liners to obtain resistance in extremely high temperature operating conditions. This paper reports on measurements in flows generated by jets issuing from a 10:1 scaled multi-holed plate for a blowing ratio varying from 0.2 to 11. The plate geometry is similar to geometries encountered within current combustion chamber walls. The test section has 138 holes arranged on 12 staggered rows. The holes are spaced 6.74 diameters apart in the spanwise direction and 5.84 diameters apart in the downstream direction. The holes angle inclination is 30 degrees with respect to the plate surface. Mean velocity vectors and turbulent Reynolds shear stresses are measured using a two-component Laser Doppler Anemometry system. An investigation is performed to study the effects of adjacent jets flow interactions and jet-to-cross-flow combinations on the film cooling cove...
Journal of Turbomachinery
Cooling Optimization Theory—Part I: Optimum Wall Temperature, Coolant Exit Temperature, and the Effect of Wall/Film Properties on Performance
2016 •
Thomas Povey
IOP Conference Series: Materials Science and Engineering
Effusion Cooling In Gas Turbine Combustion Chambers - A Comprehensive Review
2020 •
Shahid Saleem
Effusion cooling technique is an advanced concept for reducing the wall temperature in combustion chamber liners and gas turbine blades by injecting cross flow secondary fluid (coolant) through an array of holes having small diameter at close spacing. From last two decades, extensive works have been done for improving the life of hot components of gas turbines by different cooling methods. This paper discusses the review of the literature related to the geometrical parameter effects and factors affecting the adiabatic effectiveness of effusion cooling.
Gas Turbine and Combustion Chamber- A Review of the Cooling Techniques, The Problem of Scale Effect and Types of Flow
IJIRST - International Journal for Innovative Research in Science and Technology
This paper briefly reviews some of the work on advanced the liner cooling techniques - specifically laminated porous wall cooling, angled-multirole (effusion) cooling and composite metal matrix liner cooling. The concept definition, heat transfer design procedure and design problems including key materials and fabrication considerations associated with each basic concept will be reviewed. Combustion characteristics and pollutant emissions are studied for different fuels. The influence of droplet diameter on pollutant emissions at all conditions is studied. The fuel and oxidizer are supplied at ambient conditions. The concept of high swirl flows has been adopted to achieve high internal recirculation rates, residence time and increased dilution of the fresh reactants in the primary combustion zone, resulting in flameless combustion mode. Numerical computation has been applied to investigate the temperature field in a gas turbine combustion chamber. The simulation assumed that pressure imbalance conditions of air flow between primary and secondary inlets occur.
