Numerical simulation of turbine blade cooling with respect to blade heat conduction and inlet temperature profiles

1995 ◽  
Author(s):  
A Heselhaus ◽  
D Vogel
Keyword(s):  
Numerical Simulation ◽  
Heat Conduction ◽  
Turbine Blade ◽  
Inlet Temperature ◽  
Temperature Profiles ◽  
Turbine Blade Cooling ◽  
Blade Cooling

Numerical Analysis of Fluid Flow in an Internal Turbine Blade Cooling Passage

1995 ◽  
Author(s):  
Marc L. Babich ◽  
Song-Lin Yang ◽  
Donna J. Michalek ◽  
Oner Arici
Keyword(s):  
Turbine Blade ◽  
High Efficiency ◽  
Stokes Equations ◽  
Numerical Study ◽  
Inlet Temperature ◽  
Internal Cooling ◽  
Grid Turbulence ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Cooling Passage

The need to develop ultra-high efficiency turbines demands the exploration of methods which will improve the thermal efficiency and the specific thrust of the engine. One means of achieving these goals is to increase the turbine inlet temperature. In order to accomplish this, further advances in turbine blade cooling technology will have to be realized. A technique which has only recently been used in the analysis of turbine blade cooling is computational fluid dynamics. The purpose of this paper is to present a numerical study of the flowfield inside of the internal cooling passage of a radial turbine blade. The passage is modeled as two-dimensional and non-rotating. The flowfield solutions are obtained using a pseudo-compressible formulation of the Navier-Stokes equations. The spatial discretization is performed using a symmetric second-order accurate TVD (Total Variational Diminishing) scheme. Calculations are performed on a multi-block-structured grid. Turbulence is modeled using a modified κ-ω model. In the absence of experimental data, results appear to be realistic based on common experiences with fluid mechanics.

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.

Performance evaluation of a transpiration-cooled gas turbine for different coolants and permissible blade temperatures considering the effect of radiation

2011 ◽  
Vol 225 (8) ◽  
pp. 1156-1165 ◽  
Author(s):  
S Kumar ◽  
O Singh
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Radiation Effect ◽  
Turbine Blades ◽  
Cycle Performance ◽  
Inlet Temperature ◽  
Thermodynamic Evaluation ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Gas Turbine Cycle

Successful gas turbine technology is based significantly upon the introduction of new blade materials with increased permissible temperature for gas turbine blades and/or the use of efficient means and methods of turbine blade cooling in order to achieve the highest possible turbine inlet temperature. The gas turbine blade cooling models found in literature indicate that the effect of radiation from elevated temperature gases is generally not considered. However, the radiative heat transfer always occurs owing to the presence of mainly carbon dioxide and water vapour in the combustion products. The present paper deals with the comparative study of transpiration-cooled gas turbine cycle performance with and without taking radiation effect for different coolants and permissible blade temperature. The thermodynamic evaluation shows that, with consideration of the radiation effect, the theoretical coolant requirement increases so as to be close to the actual requirement and hence the cycle performance is affected accordingly. The transpiration-cooled gas turbine cycle performance parameter variations are presented to exemplify the role of cooling technology, cooling means, and material development, taking the radiation effect into account.

scholarly journals Optimization of Gas Turbine Blade Cooling System

2019 ◽  
Vol 8 (11) ◽  
pp. 4176-4181
Keyword(s):  
Turbine Blade ◽  
Gas Turbines ◽  
Cooling System ◽  
Turbine Blades ◽  
Inlet Temperature ◽  
3D Design ◽  
Turbine Blade Cooling ◽  
Pin Fin ◽  
Blade Cooling ◽  
Industrial Sectors

At present, Gas turbines play an essential responsibility in different areas such as jet, generating power and various commercial and industrial sectors. Melting point of the turbine blade may causes the hotness levels which go rapidly raise. Likewise, heavy crack may cause because of Turbine Inlet Temperature (TIT) at turbine blades for the period of expansion procedure of turbine sector. Hence, a highly developed blade cooling system is required for safe operation of turbines. The proposed system deals with the serpentine rip - roughened passage with micro pin fin cooling system and it has been analyzed corresponding to serpentine cooling system. It increases the heat transfer enhancement. Therefore, very warm gases in and around the turbine blade may have a stream temperature at 1500K. On the other side, cool air disclosed to the blade core duct and an entry temperature may have been 650K. The proposed systems with 2D and 3D model were developed by using CATIA. The 3D design is then analyzed using CFD. Further, the corresponding results of serpentine rip - roughened passage and micro pin fin arrangement in serpentine rip-roughened passage are compared and the details are presented.

Exploring the Impact of Elevated Turbine Blade Cooling Effectiveness and Turbine Material Temperatures on Gas Turbine Engine Performance and Cost

2015 ◽  
Author(s):  
Aaron R. Byerley ◽  
August J. Rolling
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Turbine Blade ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Cooling Effectiveness ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Turbine Inlet ◽  
The Impact

Since the 1950’s, the turbine inlet temperatures of gas turbine engines have been steadily increasing as engine designers have sought to increase engine thrust-to-weight and reduce fuel consumption. In turbojets and low-bypass turbofan engines, increasing the turbine inlet temperature boosts specific thrust, which in some cases can support supersonic flight without the use of an afterburner. In high-bypass gas turbine engines, increasing the turbine inlet temperature makes possible higher bypass ratios and overall pressure ratios, both of which reduce specific fuel consumption. Increased turbine inlet temperatures, without sacrificing blade life, have been made possible through advances in blade cooling effectiveness and high-temperature turbine blade materials. Investigating the impact of higher turbine inlet temperatures and the corresponding cooling air flow rates on specific thrust, specific fuel consumption, and engine development cost is the subject of this paper. A physics-based cooling effectiveness correlation is presented for linking turbine inlet temperature to cooling flow fraction. Two cases are considered: 1) a low-bypass, mixed-exhaust, non-afterburning turbofan engine intended to support supercruising at Mach 1.5 and 2) a high-bypass, unmixed-exhaust turbofan engine intended to support highly efficient, long range flight at Mach 0.8. For each of these two cases, both baseline and enhanced cooling effectiveness values as well as both baseline and elevated turbine blade material temperatures are considered. Comparing these cases will ensure that students taking courses in preliminary engine design understand why huge research investments continue to be made in turbine blade cooling and advanced, high-temperature turbine blade material development.

scholarly journals The Influence of Pressure Pulses to an Innovative Turbine Blade Film Cooling System

1998 ◽  
Author(s):  
Siegfried Moser ◽  
Herbert Jericha ◽  
Jakob Woisetschläger ◽  
Arno Gehrer ◽  
Werner Reinalter
Keyword(s):  
Turbine Blade ◽  
Film Cooling ◽  
Cooling System ◽  
Leading Edge ◽  
Inlet Temperature ◽  
Pressure Waves ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Wall Film ◽  
Turbine Vane

The evolution of increasing turbine inlet temperature has led to the necessity of full-coverage film cooling for the first turbine vane and blade. This paper deals with the investigation of the aerodynamic behaviour of the transonic wall film on a leading edge with and without leading edge pressure waves. Here these films are used for turbine blade cooling. The pressure waves are produced with a rotating „Pressure Wave Generator“. The numerical simulations have been realised with a commercial CFD-Program. The experimental data were obtained in a linear cascade.

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