Experimental and numerical investigation of jet impingement cooling onto a concave leading edge of a generic gas turbine blade

2021 ◽  
Vol 164 ◽  
pp. 106862
Author(s):  
Marius Forster ◽  
Bernhard Weigand
Keyword(s):  
Numerical Investigation ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Leading Edge ◽  
Jet Impingement ◽  
Gas Turbine Blade ◽  
Impingement Cooling

Influence of converging conical hole angles on jet impingement blade cooling of gas turbine blade leading edge

2022 ◽  
Author(s):  
S. Sathish ◽  
S. Seralathan ◽  
Mohan Sai Narayan Ch ◽  
V. Mohammed Rizwan ◽  
U. Prudhvi Varma ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Leading Edge ◽  
Jet Impingement ◽  
Gas Turbine Blade ◽  
Blade Cooling ◽  
Blade Leading Edge

Comparison of Showerhead Jet Impingement Configurations on Leading Edge of a Gas Turbine Blade

2019 ◽  
Author(s):  
Alankrita Singh ◽  
B. V. S. S. S. Prasad
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Test Section ◽  
Flow Characteristics ◽  
Leading Edge ◽  
Jet Impingement ◽  
Turbulent Intensity ◽  
Gas Turbine Blade ◽  
Mean Velocity ◽  
Jet Interactions

Abstract Anemometry measurements are made on three novel, equilaterally staggered showerhead cooling configurations of jet impingement, for the leading edge of a gas turbine blade. In all the configurations, there are five jet impingement tubes in the form of a showerhead, wherein the central jet is circular and the remaining four neighboring jets have either circular or ±45° chamfer at one of its end. Flow characteristics of these jet configurations are analyzed by determining the mean velocity and the turbulent intensity of jets. The differences in the flow characteristics of these arrangements occur due to the changes in jet velocity profile and jet-to-jet interactions. The turbulent intensity is primarily responsible for augmentation in heat transfer of the test section. The uniform cooling of test section is represented by an “uniformity index” a high value of which is desirable for material durability. The Nusselt number is correlated with Reynolds number and turbulent intensity for all the three configurations.

Novel Gas Turbine Blade Leading Edge Cooling Configuration Using Advanced Double Swirl Chambers

2015 ◽  
Author(s):  
Karsten Kusterer ◽  
Gang Lin ◽  
Takao Sugimoto ◽  
Dieter Bohn ◽  
Ryozo Tanaka ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Leading Edge ◽  
Gas Turbine Blade ◽  
Stagnation Line ◽  
Impingement Cooling ◽  
Cooling Technology ◽  
Cooling Air ◽  
Blade Leading Edge

The Double Swirl Chambers (DSC) cooling technology, which has been introduced and developed by the authors, has the potential to be a promising cooling technology for further increase of gas turbine inlet temperature and thus improvement of the thermal efficiency. The DSC cooling technology establishes a significant enhancement of the local internal heat transfer due to the generation of two anti-rotating swirls. The reattachment of the swirl flows with the maximum velocity at the center of the chamber leads to a linear impingement effect on the internal surface of the blade leading edge nearby the stagnation line of gas turbine blade. Due to the existence of two swirls both the suction side and the pressure side of the blade near the leading edge can be very well cooled. In this work, several advanced DSC cooling configurations with a row of cooling air inlet holes have been investigated. Compared with the standard DSC cooling configuration the advanced ones have more suitable cross section profiles, which enables better accordance with the real blade leading edge profile. At the same time these configurations are also easier to be manufactured in a real blade. These new cooling configurations have been numerically compared with the state of the art leading edge impingement cooling configuration. With the same configuration of cooling air supply and boundary conditions the advanced DSC cooling presents 22–26% improvement of overall heat transfer and 3–4% lower total pressure drop. Along the stagnation line the new cooling configuration can generate twice the heat flux than the standard impingement cooling channel. The influence of spent flow in the impinging position and impingement heat transfer value is in the new cooling configurations much smaller, which leads to a much more uniform heat transfer distribution along the chamber axial direction.

Leading Edge Cooling of a Gas Turbine Blade With Double Swirl Chambers

2014 ◽  
Author(s):  
Karsten Kusterer ◽  
Gang Lin ◽  
Dieter Bohn ◽  
Takao Sugimoto ◽  
Ryozo Tanaka ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Maximum Velocity ◽  
Leading Edge ◽  
Inlet Temperature ◽  
Gas Turbine Blade ◽  
Impingement Cooling ◽  
Swirl Flows ◽  
Blade Leading Edge

The gas turbine blade leading edge area has locally extremely high thermal loads, which restrict the further increase of turbine inlet temperature or the decrease of the amount of coolant mass flow to improve the thermal efficiency. Jet impingement heat transfer is the state of the art cooling configuration, which has long been used in this area. In the present study, a modified double swirl chambers cooling configuration has been developed for the gas turbine blade leading edge. The double swirl chambers cooling (DSC) technology is introduced by the authors and comprises a significant enhancement of heat transfer due to the generation of two anti-rotating swirls. In DSC cooling the reattachment of the swirl flows with the maximum velocity at the middle of the chamber leads to a linear impingement effect, which is most suitable for the leading edge cooling for a gas turbine blade. In addition, because of the two swirls both suction side and pressure side of the blade near the leading edge can be very well cooled. In this work, a comparison among three different internal cooling configurations for the leading edge (impingement cooling, swirl chamber and double swirl chambers) has been investigated numerically. With the same inlet slots and the same Reynolds number based on hydraulic diameter of channel the DSC cooling shows overall higher Nusselt number ratio than that in the other two cooling configurations. Downstream of the impingement point, due to the linear impingement effect, the DSC cooling has twice the heat flux in the leading edge area than the standard impingement cooling channel.

Recent Advances in the Study of Film Cooling on the Gas Turbine Blade

2014 ◽  
Vol 971-973 ◽  
pp. 143-147 ◽  
Author(s):  
Ping Dai ◽  
Shuang Xiu Li
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Gas Turbines ◽  
High Performance ◽  
Leading Edge ◽  
Development Trend ◽  
Research Progress ◽  
Gas Turbine Blade ◽  
New Generation

The development of a new generation of high performance gas turbine engines requires gas turbines to be operated at very high inlet temperatures, which are much higher than the allowable metal temperatures. Consequently, this necessitates the need for advanced cooling techniques. Among the numerous cooling technologies, the film cooling technology has superior advantages and relatively favorable application prospect. The recent research progress of film cooling techniques for gas turbine blade is reviewed and basic principle of film cooling is also illustrated. Progress on rotor blade and stationary blade of film cooling are introduced. Film cooling development of leading-edge was also generalized. Effect of various factor on cooling effectiveness and effect of the shape of the injection holes on plate film cooling are discussed. In addition, with respect to progress of discharge coefficient is presented. In the last, the future development trend and future investigation direction of film cooling are prospected.

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