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

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.

Download Full-text

Effect of Slot Area Ratio and Slot Angle on Swirl Cooling in a Gas Turbine Blade Leading Edge

Journal of Aerospace Engineering ◽

10.1061/(asce)as.1943-5525.0001161 ◽

2020 ◽

Vol 33 (5) ◽

pp. 04020046

Author(s):

Hamza Fawzy ◽

Qun Zheng ◽

Naseem Ahmad

Keyword(s):

Gas Turbine ◽

Turbine Blade ◽

Leading Edge ◽

Area Ratio ◽

Gas Turbine Blade ◽

Blade Leading Edge

Download Full-text

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

Volume 5A: Heat Transfer ◽

10.1115/gt2015-42400 ◽

2015 ◽

Cited By ~ 8

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.

Download Full-text