ENHANCEMENTS OF THE THERMAL UNIFORMITY INSIDE A GAS-TURBINE DILUTION SECTION USING DIMENSIONAL OPTIMIZATION

2020 ◽  
pp. 1-27
Author(s):  
Tarek ElGammal ◽  
Osama M. Selim ◽  
Ryoichi S. Amano
Keyword(s):  
Pressure Drop ◽  
Response Surface ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Correlation Coefficients ◽  
Optimal Designs ◽  
Surface Model ◽  
Thermal Mixing ◽  
Streamlined Body ◽  
The Cost

Abstract In the dilution section of the gas turbine, the flow and thermal mixing between the cold radial jets and hot mainstream is always a matter of interest to generate a consistent thermal profile, extending the longevity of the turbine blades. Multiple researches explored the topic experimentally and numerically, and new designs have been evaluated, including a central streamlined body with swirlers inside the dilution zone. Moreover, the dimensional aspects (diameter, length, and position) of the streamlined body can help in generating more uniform thermal profiles, but with the cost of increased pressure drop. Various design iterations are needed to be tested and assessed based on minimizing the contradicting uniformity number and pressure drop. Such process is time and resources consuming if not wisely managed. The paper proposes a solution for the current problem by the integration of the “Design of Experiment/ Optimization Algorithms” generator with the computational fluid dynamics solver. The outcomes from three different algorithms (ULH, MOGA-II, and HYBRID) are statistically analyzed to understand inputs-outputs correlations, develop response surface methodology, and help in finding the optimal designs. The suggested HYBRID optimization provided a better optimal curve with improvements of 69% and 15% in the thermal uniformity and pressure drop respectively. The correlation coefficients stressed on the importance of the diameter as the highest influencer with inverse and direct correlations with uniformity and pressure drop, respectively. Finally, the Kriging response surface model enabled more optimal designs and a better understanding of the effective ranges of the three inputs.

Topology Optimization of Serpentine Channels for Minimization of Pressure Loss and Maximization of Heat Transfer Performance As Applied for Additive Manufacturing

2019 ◽  
Author(s):  
Shinjan Ghosh ◽  
Jayanta S. Kapat
Keyword(s):  
Heat Transfer ◽  
Topology Optimization ◽  
Additive Manufacturing ◽  
Pressure Drop ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Inlet Temperature ◽  
Internal Cooling ◽  
Cooling Channels ◽  
Blade Cooling

Abstract Gas Turbine blade cooling is an important topic of research, as a high turbine inlet temperature (TIT) essentially means an increase in efficiency of gas turbine cycles. Internal cooling channels in gas turbine blades are key to the cooling and prevention of thermal failure of the material. Serpentine channels are a common feature in internal blade cooling. Optimization methods are often employed in the design of blade internal cooling channels to improve heat-transfer and reduce pressure drop. Topology optimization uses a variable porosity approach to manipulate flow geometries by adding or removing material. Such a method has been employed in the current work to modify the geometric configuration of a serpentine channel to improve total heat transferred and reduce the pressure drop. An in-house OpenFOAM solver has been used to create non-traditional geometries from two generic designs. Geometry-1 is a 2-D serpentine passage with an inlet and 4 bleeding holes as outlets for ejection into the trailing edge. Geometry-2 is a 3-D serpentine passage with an aspect ratio of 3:1 and consists of two 180-degree bends. The inlet velocity for both the geometries was used as 20 m/s. The governing equations employ a “Brinkman porosity parameter” to account for the porous cells in the flow domain. Results have shown a change in shape of the channel walls to enhance heat-transfer in the passage. Additive manufacturing can be employed to make such unconventional shapes.

Exergoeconomic Analysis of Intercooled, Reheated and Recuperated Gas Turbine Cycles With Air Film Blade Cooling

2018 ◽  
Author(s):  
Waleed El-Damaty ◽  
Mohamed Gadalla
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
Power Plants ◽  
Turbine Blades ◽  
Cost Calculation ◽  
Theory Approach ◽  
Cooling Systems ◽  
Thermodynamic Performance ◽  
Exergoeconomic Analysis ◽  
The Cost

For many years, thermodynamic analysis was considered to be the principal tool that is used to predict the performance of a power plant. Recently, the environmental effect and the cost of power plants have been considered as important as the thermodynamic performance in design of power plants. Thus, researchers started to adopt a relevantly new approach called the exergoeconomic analysis which combines the thermodynamic technicalities as well as the economic analysis to design power plants. The exergoeconomic analysis provides crucial information that helps in foreseeing not only the thermodynamic performance but also all economic variables related to power plants. Increasing the efficiency of the power plant has been the major concern in power plants. Thus, the global approach of reaching high turbine inlet temperatures to improve the efficiency of power plants, has exposed the turbine blades to some serious problems. Thereby, cooling the turbine blades has become an important aspect that needs to be taken care of during the power plant operation. In this paper, a cooled gas turbine with intercooler, recuperator and reheater is adopted where it is incorporated with a cooling system. An exergoeconomic analysis accompanied by a sensitivity analysis was performed on the gas turbine cycle to determine the exergo-economic factor and the relative cost difference in addition to study the effect of different variables on the gas turbine thermal and exergetic efficiency, net specific work and the total cost rate. Average cost theory approach was adopted from various thermo-economic methodologies to determine the cost calculation during this investigation. The results showed a reduction in the total coolant mass flow rate in the base case where no cooling systems are integrated from 3.349 kg/s to 3.01 kg/s, 2.995 kg/s and 2.977 kg/s in the case of integrating the cooling systems triple stage Maisotsenko desiccant, triple stage precooling Maisotsenko desiccant and triple stage extra cooling Maisotsenko desiccant, respectively. Accordingly, the thermal efficiency has increased to reach 52.69%, 52.89% and 53.12% by the integration of TS-MD, TS-PMD and TS-EMD cooling systems, respectively.

scholarly journals Comparative analysis of automated and non-automated production of turbine blades

2016 ◽  
Vol 1 (11) ◽  
pp. 25-31
Author(s):  
В. Полетаев ◽  
V. Poletaev ◽  
Е. Цветков ◽  
E. Tsvetkov
Keyword(s):  
Comparative Analysis ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Turbine Blades ◽  
Efficient Production ◽  
Automated Production ◽  
The Cost ◽  
One Machine

Existing production of turbine blades is arranged on the principle “one machine – one part – one product”. This concept does not meet the requirements of today to ensure the required “price – quality” ratio of the product. The only solution to improve the efficient production to process turbine blades on the base of multifunctional machining centers allows increasing efficiency of turbine blade manufacture, and provides advantages to manufacturers of GTE on the gas turbine markets. Automated production of the turbine blades developed by NPO “Saturn” has greatly enhanced the quality of GTE blade wheel manufacture and reduced the cost of their production.

UDIMET L-605

Alloy Digest ◽  
2004 ◽  
Vol 53 (12) ◽  
Keyword(s):  
Corrosion Resistance ◽  
High Temperature ◽  
Physical Properties ◽  
Tensile Properties ◽  
Gas Turbine ◽  
Oxidation Resistance ◽  
Turbine Blades ◽  
Heat Treating ◽  
Gas Turbine Blades ◽  
Temperature Performance

Abstract Udimet L-605 is a high-temperature aerospace alloy with excellent strength and oxidation resistance. It is used in applications such as gas turbine blades and combustion area parts. This datasheet provides information on composition, physical properties, and tensile properties as well as creep. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, and joining. Filing Code: CO-109. Producer or source: Special Metals Corporation.

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