Papers by Keyword: Turbine Blade

Abstract: The study investigates the application of centrifugal casting process in the production of a complex shape component, Pelton turbine bucket. The bucket materials examined were functionally graded aluminium A356 alloy and A356-10%SiC_p composite. A permanent mould for the casting of the bucket was designed with a Solidworks software and fabricated by the combination of CNC machining and welding. Oil hardening non-shrinking die steel (OHNS) was chosen for the mould material. The OHNS was heat treated and a hardness of 432 BHN was obtained. The mould was put into use, the buckets of A356 Alloy and A356-10%SiCp composite were cast, cut and machined into specimens. Some of the specimens were given T6 heat treatment and the specimens were prepared according to the designed investigations. The micrographs of A356-10%SiC_p composite shows more concentration of SiC_p particles at the inner periphery of the bucket. The maximum hardness of As-Cast A356 and A356-10%SiC_p composite were 60 BRN and 95BRN respectively, recorded at the inner periphery of the bucket. And these values appreciated to 98BRN and 122BRN for A356 alloy and A356-10%SiC_p composite respectively after heat treatment. The prediction curves of the ultimate tensile stress and yield tensile stress show the same trend as the hardness curves.

Abstract: Ni-based superalloys are used as turbine blade material in which creep-fatigue is an important damage mechanism. Simulation and experiment methods are used to investigate and predicte the failure mechanism of the first stage high pressure turbine blades of an aeroengine after 600 hours service. The high pressure turbine blades were made of Ni-base superalloy DZ4, fabricated by DS investment casting. The largest stress point was obtained by finite element analysis. During the fatigue test, the high temperature and low cycle fatigue/creep load simulating the real working condition were applied on the blades until they fractured. And then several examinations were carried out to identify the fracture’s main cause, such as visual examination, SEM fractography and microstructural characterization. In conclusion, the fracture of the high pressure turbine blades was mainly caused by the interaction of the fatigue and creep. Besides, the oxidation accelerated the blades fracture.

Abstract: The goal of this research is to investigate cratered hole geometries on film cooling performance. Five kinds of cratered holes, namely, the concentric crater, the circular crater, the downstream offset crater, the upstream offset crater, and the direct crater are being studied along with the conventional flush hole. All craters has the same depth of 0.5 hole diameter. Through numerical simulation with CFX at a single blowing ratio of 0.5 and Reynold number of 11000, we analyze and compare the performance and behavior of five kinds of cratered holes with the conventional cylindrical hole. The simulation employs k-ε turbulent model and wall function. Film cooling effectiveness is achieved for all cases. Among all cases, concentric cratered hole perform the best which increases averaged film cooling effectiveness by 64% at X/D=5.35. All cratered holes appear some performance improvement compared to the baseline case. For cratered holes, film lateral convergence and stream-wise attaching performance was both enhanced owing to the expansional configuration of the crater and the consequent backflow region.

Abstract: The simulation process of centrifugal casting using titanium aluminide intermetallic alloys has been described in the context of the low-pressure duct turbine blade designed for the gas-turbine engine. Initially, the preliminary theoretical calculations have been performed together with experimental casting when developing the casting production technologies. The obtained results allowed setting a range of the boundary conditions for computing simulation of pouring and solidification. ProCast the computing simulation system for the casting processes has been used. Various alternatives of the casting layout in the mold as well as the gating system configurations have been examined by means of this system. In the course of simulation process such faults have been detected as formation of shrinkages into the shroud platform and (or) blade footing; or significant decrease in technological yield when the risers’ dimensions expand or the casts’ number decreases in the mold. Considering the results of the performed computer experiments, the most efficient gating system has been ultimately defined to obtain the casts using titanium aluminide intermetallic alloys by centrifugal casting.

Abstract: Presented paper deals with modelling of a twisted blade with rhombic shroud as one-dimensional continuum by means of Rayleigh beam finite elements with varying cross-sectional parameters along the finite elements. The blade is clamped into a rotating rigid disk and the shroud is considered to be a rigid body. Since the finite element models based on the Rayleigh beam theory tend to slightly overestimate natural frequencies and underestimate deflections in comparison with finite element models including shear deformation effects, parameter tuning of the blade is performed.

Abstract: The paper presents a comparison between Coordinate Measuring Machine and 3D white light scanning technologies as applied to the dimensional inspection of turbo-machinery parts such as turbine blade. The results were compared with the CAD model and each other. The results indicate that, even both methods are enough accurate with a slightly better accuracy for CMM, the operational speed and the variety of scanable surfaces give significant advantages to the 3D scanning method when prototypes require dimensional inspection by an alternative rapid route especially when dealing with objects with thin walls or sharp edges.

Abstract: Because of growing global concern for the increasing energy demand and the resulting environmental impact of fossil fuel based energy sources, renewable and environmental friendly energy sources are critically sought. Wind turbines are generally conceived as the key renewable energy sources, but more innovative solutions should augment the classical design and control of wind turbines in order to improve the energy conversion efficiency. For areas outside the integrated grid system and harsh operation conditions in particular vertical axis wind turbines show promising results. This turbine design is previously considered less efficient, and thus the performance has not been sufficiently documented. This paper attempts to contribute in better understanding of the wind flow around the rotor, and the way the rotor components react to the resulting pressure. The turbine is first modeled in 3D CAD system and simulated in a flow simulator in a virtual wind tunnel. Then the iso-lines of velocity and pressure distribution are plotted at selected sections of the turbine plane and the profiles are studied to characterize the fluctuations of the dynamic pressure and identify the vulnerable zone of the turbine blades and the structure.

Abstract: Design of Turbo machinery is complex and efficiency is directly related to material performance, material selection is of prime importance. Temperature limitations are the most crucial limiting factors to gas turbine efficiencies. This paper presents the life of GTD 111 applied to gas turbine blade based on LCF and TMF test results. The LCF tests were conducted under various strain ranges based on gas turbine operating conditions. In addition, IP (in-phase) and OP (out of-phase) TMF tests were conducted under various strain ranges. The paper will focus light on above issues and each plays an important role within the Gas Turbine Material literature and ultimately influences on planning and development practices. It is expected that this comprehensive contribution will be very beneficial to everyone involved or interested in Gas Turbines.

Abstract: The effects of Al, Co, Re, and Ru on the stacking fault energy in Ni alloys were analyzed using computational thermodynamics. The effects of adding up to 5 at% Re or Ru to a Ni-15at%Co system were found to be weak at 300 °C, 700 °C, and 900 °C. However, Al addition decreased the stacking fault energy in a Ni-15at%Co-Xat%Ru system, where X = 0, 3, 5. In addition, this decrease in the stacking fault energy due to Al addition became more significant as the amount of Ru increased. Furthermore, in Ni–Co–Al–Ru alloys containing 9at%Al, the addition of 5at%Ru decreased the stacking fault energy as much as the addition of 12.5at%Co at 900 °C. The effects of Co and Ru addition on the γ/γ’ microstructure of Ni-based superalloys were also discussed.

Abstract: Paper presents results of quantitative evaluation of porosity conducted on big, thin walled airfoil turbine blades made from Inconel 713C alloy. To decrease mass, blades are design and manufacture like thin walled cored castings. Manufacturing of big thin walled casting airfoil blades is extremely difficult. During exploitation casting work undergo cycle fatigue. In that cause casting should be free of casting defects, including porosity. Conducted research focused on Inconel 713C superalloy pouring temperature effect on porosity level of cored casted turbine blade. Results were compared to porosity of solid casted turbine blade. It was found that porosity of cored blades is lower than solid blade porosity. In cored blades higher porosity is located on airfoil convex side. Airfoil concave side has lower porosity.