Profiled Endwall Design Using Genetic Algorithms With Different Objective Functions

2011 ◽  
Author(s):  
Jamie McIntosh ◽  
Richard MacPherson ◽  
Grant Ingram ◽  
Simon Hogg
Keyword(s):  
High Pressure ◽  
Genetic Algorithms ◽  
Design Process ◽  
Turbine Blades ◽  
Design System ◽  
Steam Turbines ◽  
Objective Functions ◽  
Design Decisions ◽  
Gas Turbine Blades ◽  
Trade Offs

Profiled endwalls are a widely researched technology for reducing the secondary loss in turbines. Most designs in the literature have been produced directly by manufacturers and although general performance information is given the detailed design decisions are kept confidential. This paper outlines a simple design system for profiled endwalls that uses genetic algorithms to find an acceptable design. As the design process is produced in an academic environment full details of the design process, geometries produced, objective functions and the various trade-offs involved in the design are available and discussed in the paper. Two designs were produced using the design system: one using secondary kinetic energy as the objective function of the design system and the second using a U-cubed integral. The different designs that are produced with the different objective functions are discussed in detail in the paper. Finally profiled endwalls have traditionally been used in the high pressure stages of gas turbine blades, the paper also discusses the merits and challenges in applying these technologies to the high pressure and intermediate pressure stages of steam turbines.

High-Pressure Gas Turbine Vane Turbulent Flows and Heat Transfer Predicted by RANS/LES/DES

2017 ◽  
Author(s):  
Ping Dong ◽  
R. S. Amano
Keyword(s):  
Heat Transfer ◽  
High Pressure ◽  
Gas Turbine ◽  
Turbulent Flows ◽  
Film Cooling ◽  
Turbine Blades ◽  
Suction Side ◽  
Gas Turbine Blades ◽  
Flow And Heat Transfer ◽  
Turbine Vane

The lifetime of the modern gas turbines greatly depends on the durability of hot section components operating at high temperatures. Film cooling is key to air cooling technologies in modern gas turbine and widely used in high-temperature and high-pressure blades as an active cooling scheme. The requirements of accurate prediction of aerodynamic flow and heat transfer in gas turbine blades lay the essential foundation of cooling effectiveness improvement and working life estimation. In recent days, Large Eddy Simulations (LES) is considered as a useful tool to predict turbulent flows and heat transfer around gas turbine blades, but, comparing to the Reynolds-Averaged Navier–Stokes (RANS) methods, the LES method usually needs more computing resource and depends on computational power and mesh quality. In this paper, LES/DES (Detached Eddy Simulation) predictions were compared to RANS prediction with interest in the accuracy and improvement of turbulent flow and heat transfer phenomena around NASA’s C3X high-pressure gas turbine vane with leading edge cooling film. RANS/LES/DES were detailed and further investigated to assess their ability to predict flow and heat transfer in boundary layer around C3X vane. The current predictions showed that the mix between film cooling injections and free stream resulted in complex flow and heat transfer in the boundary layer on the external vane surface. The predictions of the aerodynamic load along the C3X vane with RANS/LES/DES were almost identical and agreed well with the experimental results. However, the heat transfer predictions with RANS/LES/DES were different. The transition prediction showed the best agreement with the experiment data in the most region. The LES prediction only partially agreed with the experimental data before separation point on the suction side and mild pressure gradient region on the pressure side. The DES and RANS predictions agreed with the experiment data after separation point on the suction side and most region on the pressure side.

scholarly journals The Effect of Heat Transfer on Turbine Performance

2020 ◽  
Vol 142 (09) ◽  
pp. 56-57
Author(s):  
Lachlan J. Jardine ◽  
Robert J. Miller
Keyword(s):  
Heat Transfer ◽  
High Pressure ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Large Temperature ◽  
Gas Turbine Blades ◽  
Turbine Performance ◽  
Very High

Abstract For over 50 years, high-pressure gas turbine blades have been cooled using air bled from the compressor. This cooling results in very high rates of heat transfer, both within the fluid and within the blade, shown in figure 1. The heat transfer often occurs across large temperature differences and is thus highly irreversible. It is therefore surprising that little is understood about the effect of this heat transfer on turbine performance.

scholarly journals Application of additive laser technologies in the gas turbine blades design process

2017 ◽  
Vol 891 ◽  
pp. 012255
Author(s):  
I V Shevchenko ◽  
A N Rogalev ◽  
S K Osipov ◽  
N M Bychkov ◽  
I I Komarov
Keyword(s):  
Gas Turbine ◽  
Design Process ◽  
Turbine Blades ◽  
Gas Turbine Blades ◽  
Laser Technologies

Novel End-End System for Combustor Design and Analysis

2021 ◽  
Author(s):  
Ashwin Kannan ◽  
Jonathan Thewlis ◽  
Akin Keskin
Keyword(s):  
Design Process ◽  
Traditional Approach ◽  
Automated Design ◽  
Design System ◽  
Efficiency Gain ◽  
Parametric Approach ◽  
Parametric Generation ◽  
3D Cad ◽  
Trade Offs ◽  
Modelling Approach

Abstract High quality geometry creation is a key step in the design process for complex modern turbomachinery subsystems such as an annular combustor assembly. In particular, parametric generation of 3D CAD geometry is an enabler for design studies and multi-disciplinary analysis. In a traditional approach, 3D CAD models are either created in a bespoke manner with respect to the engine of interest or if a parametric approach is used, the geometry is for one particular combustor configuration, which typically leads to insufficient flexibility for topological variations. In either of these cases for every combustor design, substantial manual efforts are involved in geometry creation as well as in geometry manipulation towards creation of a truncated sector model suitable for meshing and analysis. A more flexible and fully parametric approach in highly integrated and automated design processes during all product design phases is therefore necessary. The present paper focuses on the exploitation and integration of a novel geometry modelling approach into an existing and well-established combustor design and analysis system called Prometheus in order to achieve a massive step toward a fully End-to-End (E2E) system. The new system is enabling rapid combustor design and analysis by combining feature-based geometry modelling approach that enables automatic creation of an analysis compatible combustor assembly with a geometry-centric optimization system. The automated design system can manipulate 3D geometry, to create necessary script files for meshing, simulation and post-processing for a typical CFD analysis, and execute the process to analyze different designs with respect to defined design objectives and constraints. The improved system enables engineers to assess different design concepts quickly early in the design process by providing best trade-offs between design objectives but also allows the use of detailed simulation models and boundary conditions in later more mature designs stages. The paper will discuss the robustness and flexibility of the underlying parametric CAD approach, how it augments the downstream processes, which is able to handle and translate significant topological changes throughout the E2E system. It will also clearly demonstrate the efficiency gain of the automated combustor design process, which enables design engineers to make better decision faster.

Chemical partitioning of elements in Ni-base MC-carbide reinforced eutetic superalloys

1983 ◽  
Vol 41 ◽  
pp. 250-251
Author(s):  
E. F. Koch ◽  
E. L. Hall ◽  
S. W. Yang
Keyword(s):  
Alloy Composition ◽  
Volume Fraction ◽  
Lattice Mismatch ◽  
Turbine Blades ◽  
Eutectic Alloys ◽  
Alloy Matrix ◽  
X Ray ◽  
Gas Turbine Blades ◽  
Analytical Electron ◽  
Analytical Electron Microscope

The plane-front solidified eutectic alloys consisting of aligned tantalum monocarbide fibers in a nickel alloy matrix are currently under consideration for future aircraft and gas turbine blades. The MC fibers provide exceptional strength at high temperatures. In these alloys, the Ni matrix is strengthened by the precipitation of the coherent γ' phase (ordered L12 structure, nominally Ni3Al). The mechanical strength of these materials can be sensitively affected by overall alloy composition, and these strength variations can be due to several factors, including changes in solid solution strength of the γ matrix, changes in they γ' size or morphology, changes in the γ-γ' lattice mismatch or interfacial energy, or changes in the MC morphology, volume fraction, thermal stability, and stoichiometry. In order to differentiate between these various mechanisms, it is necessary to determine the partitioning of elemental additions between the γ,γ', and MC phases. This paper describes the results of such a study using energy dispersive X-ray spectroscopy in the analytical electron microscope.

Will Love Tear Us Apart: Adapting the Lyrical to the Ludic

CounterText ◽  
2016 ◽  
Vol 2 (2) ◽  
pp. 217-235
Author(s):  
Gordon Calleja
Keyword(s):  
Design Process ◽  
Game Design ◽  
Digital Games ◽  
Design Decisions ◽  
The Core ◽  
Lyrical Poetry ◽  
Insight Into ◽  
Made In

This paper gives an insight into the design process of a game adaptation of Joy Division's Love Will Tear Us Apart (1980). It outlines the challenges faced in attempting to reconcile the diverging qualities of lyrical poetry and digital games. In so doing, the paper examines the design decisions made in every segment of the game with a particular focus on the tension between the core concerns of the lyrical work being adapted and established tenets of game design.

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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