Gas Turbine Blade Heat Transfer Augmentation by Impingement of Air Jets Having Various Configurations

1972 ◽  
Vol 94 (1) ◽  
pp. 51-58 ◽  
Author(s):  
W. Tabakoff ◽  
W. Clevenger
Keyword(s):  
Heat Transfer ◽  
Turbine Blade ◽  
Leading Edge ◽  
Solid Particles ◽  
Turbine Blade Cooling ◽  
Round Jets ◽  
Blade Cooling ◽  
Heat Transfer Augmentation ◽  
Air Jets ◽  
Mass Flow Rates

An experimental investigation of heat transfer characteristics for various configurations of air jets impinging on the leading edge inner surface of the blade wall is presented. Three configurations were investigated, namely a slot jet, a round jet row and an array of round jets. The effect on the heat transfer coefficient of injecting solid particles into the air flow is considered. The study treats an important class of turbine blade cooling for which small cooling mass flow rates are of interest. The experimental facility and procedures are described in detail. A theoretical technique is introduced for predicting the heat transfer in the case of the slot jet configuration. The results are compared to experimental data.

scholarly journals Influence of HTC levels on temperature and stress levels in a leading edge impingement system

2019 ◽  
Vol 3 ◽  
pp. WLAL1F
Author(s):  
Robert Pearce ◽  
Peter Ireland ◽  
Edwin Dane
Keyword(s):  
Heat Transfer ◽  
Turbine Blade ◽  
Cooling System ◽  
Leading Edge ◽  
Main Concern ◽  
Software Environment ◽  
Accurate Analysis ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Stress Levels

Accurate analysis of the performance of a turbine blade cooling system is essential to allow the blade life to be safely predicted. The latter is essential as the business model for an engine can be strongly dependent on the duration between engine shop visits. Some recent heat transfer research has focused on increasing heat transfer levels in order to reduce turbine blade metal temperatures, however for engine designers it is the life of the blade, determined in part by the stress levels within it, that are of main concern. This paper uses heat transfer and stress analysis within the same software environment to examine the influence of the HTC levels in different regions of an engine representative leading edge impingement cooling system on both metal temperature and stress levels. The results of these analyses are then combined to show that, with attention to cooling in different regions of the blade, reductions in stress levels of 6% can be achieved in the most highly stressed regions of the blade with achievable alterations in heat transfer levels.

Experimental Study of Heat Transfer Augmentation Near the Entrance to a Film Cooling Hole in a Turbine Blade Cooling Passage

2009 ◽  
Vol 131 (4) ◽  
Author(s):  
Gerard Scheepers ◽  
R. M. Morris
Keyword(s):  
Heat Transfer ◽  
Experimental Study ◽  
Turbine Blade ◽  
Film Cooling ◽  
Surface Heat ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Heat Transfer Augmentation ◽  
Cooling Hole ◽  
Cooling Passage

Film cooling is extensively used by modern gas turbine blade designers as a means of limiting the blade temperature when exposed to extreme combustor outlet temperatures. The following paper describes an experimental study of heat transfer near the entrance to a film cooling hole in a turbine blade cooling passage. Steady state heat transfer results were acquired by using a transient measurement technique in a 40 times actual rectangular channel, representative of an internal cooling channel of a turbine blade. Platinum thin film gauges were used to measure the inner surface heat transfer augmentation as a result of thermal boundary layer renewal and impingement near the entrance of a film cooling hole. Measurements were taken at various suction ratios, extraction angles, and wall temperature ratios with a main duct Reynolds number of 25,000. A numerical technique based on the resolution of the unsteady conduction equation, using a Crank–Nicholson scheme, is used to obtain the surface heat flux from the measured surface temperature history. Computational fluid dynamics predictions were also made to provide better understanding of the near-hole flow. The results show extensive heat transfer enhancement as a function of extraction angle and suction ratio in the near-hole region and demonstrate good agreement with a corresponding study. Furthermore it was shown that the effect of a wall-to-coolant ratio is of a second order and can therefore be considered negligible compared with the primary variables such as the suction ratio and extraction angle.o

Slot suction from inviscid channel flow

1989 ◽  
Vol 200 ◽  
pp. 265-282 ◽  
Author(s):  
J. N. Dewynne ◽  
S. D. Howison ◽  
J. R. Ockendon ◽  
L. C. Morland ◽  
E. J. Watson
Keyword(s):  
Flow Pattern ◽  
Stagnation Point ◽  
Turbine Blade ◽  
Channel Flow ◽  
Mass Flux ◽  
Channel Wall ◽  
Leading Edge ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Slot Suction

Motivated by a problem in turbine blade cooling, we consider suction from an inviscid channel flow into a slot in the channel wall. The flow is assumed to separate smoothly from the leading edge of the slot and the pressure in the stagnant separated region controls the suction. The mass flux into the slot is found in terms of the pressure; for small values of this flux the predicted flow pattern is found to be quite different from that which would result if there were no separated region. In particular, the stagnation point never penetrates more than approximately 0.05 slot widths into the slot.

Heat transfer and friction in segmental turbine blade cooling channels

10.2514/3.925 ◽  
1997 ◽  
Vol 11 ◽  
pp. 486-488
Author(s):  
N. W. M. Ko ◽  
R. C. K. Leung ◽  
K. Lam ◽  
R. B. Spence ◽  
S. C. Lau
Keyword(s):  
Heat Transfer ◽  
Turbine Blade ◽  
Turbine Blade Cooling ◽  
Cooling Channels ◽  
Blade Cooling

scholarly journals Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

2021 ◽  
Vol 39 (2) ◽  
pp. 403-416
Author(s):  
Chirag Sharma ◽  
Siddhant Kumar ◽  
Aanya Singh ◽  
Kartik R. Bhat Hire ◽  
Vedant Karnatak ◽  
...  
Keyword(s):  
Turbine Blade ◽  
Turbine Blades ◽  
Leading Edge ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Entire Surface ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Advantages And Disadvantages ◽  
Turbine Inlet

Developments in the gas turbine technology have caused widespread usage of the Turbomachines for power generation. With increase in the power demand and a drop in the availability of fuel, usage of turbines with higher efficiencies has become imperative. This is only possible with an increase in the turbine inlet temperature (TIT) of the gas. However, the higher limit of TIT is governed by the metallurgical boundary conditions set by the material used to manufacture the turbine blades. Hence, turbine blade cooling helps in drastically controlling the blade temperature of the turbine and allows a higher turbine inlet temperature. The blade could be cooled from the leading edge, from the entire surface of the blade or from the trailing edge. The various methods of blade cooling from leading edge and its comparative study were reviewed and summarized along with their advantages and disadvantages.

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