scholarly journals Experimental heat transfer in midchord and leading edge turbine blade cooling passages with staggered turbulators

2014 ◽  
Author(s):  
Gerard M. Quinn
Keyword(s):  
Heat Transfer ◽  
Turbine Blade ◽  
Leading Edge ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Experimental Heat ◽  
Experimental Heat Transfer

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.

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.

Flow and Heat Transfer Analysis of Turbine Blade Cooling Passages Using Network Method

2012 ◽  
Author(s):  
Mohammad Alizadeh ◽  
Ali Izadi ◽  
Alireza Fathi ◽  
Hiwa Khaledi
Keyword(s):  
Heat Transfer ◽  
Boundary Conditions ◽  
Turbine Blade ◽  
Numerical Data ◽  
Internal Cooling ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Flow And Heat Transfer ◽  
Network Method ◽  
Cooling Passage

Modern turbine blades are cooled by air flowing through internal cooling passages. Three-Dimensional numerical simulation of these blade cooling passages is too time-consuming because of their complex geometries. These geometrical complexities exist as a result of using various kinds of cooling technologies such as rib turbulators (inline, staggered, or inclined ribs), pin fin, 90 and 180 degree turns (both sharp and gradual turns, with and without turbulators), finned passage, by-pass flow and tip cap impingement. One possible solution to simulate such sophisticated passages is to use the one-dimensional network method, which is presented in the current work. Turbine blade cooling channels are flow passages having multiple inlets and exits. The present in-house developed solver uses a network method for analyzing such a complicated flow pattern. In this method, cooling system is represented by a network of elements connected together at different nodes. Using assumed wall temperature, internal flow and heat transfer is calculated. The final goal of this computation is a set of boundary conditions for conjugate blade heat transfer simulation (coolant side boundary conditions). For validation, it is required to use experimental data that include temperature distribution of blade coolant-side walls. Since there is no experimental work with such data in the open literature, numerical computation is validated using available analytical and published numerical data. Calculated results agree well with analytical and numerical data. In order to exhibit the potential capabilities of the developed code, flow and heat transfer in a complicated internal cooling passage of a typical vane are investigated using the network method.

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