Table of Contents

Table of Contents for Ethnic Studies Review, Vol. 31, No. 2, Winter 2008

Numerical Simulation of Temperature Field in Ultra-Narrow Arc Welding of Thick-Walled Steam Turbine Valve Body Material

The welding problems of large and thick plates are becoming more prominent as the application of large-scale and thick-plate metal structures grows. Due to the issue of excessive welding deformation between the 60mm thick steam turbine valve body and the pipe joint, a new process method is employed to connect. In this paper, the welding technology of flux strip confined arc ultra-narrow gap is proposed to carry out welding test on the ZG13Cr9Mo2Co1NiVNbNB cast steel test block of steam turbine valve body material with a thickness of 60 mm. The welding temperature field is measured by means of a K-type thermocouple and numerical simulation. The results show that the thermal cycle curve obtained by the homogeneous body heat source simulation is basically consistent with the thermal cycle curve measured during the experiment, and the simulation results of the molten pool morphology are also consistent with the actual macroscopic morphology of the weld

Numerical Simulation of Temperature Field in Ultra-Narrow Arc Welding of Thick-Walled Steam Turbine Valve Body Material

The welding problems of large and thick plates are becoming more prominent as the application of large-scale and thick-plate metal structures grows. Due to the issue of excessive welding deformation between the 60mm thick steam turbine valve body and the pipe joint, a new process method is employed to connect. In this paper, the welding technology of flux strip confined arc ultra-narrow gap is proposed to carry out welding test on the ZG13Cr9Mo2Co1NiVNbNB cast steel test block of steam turbine valve body material with a thickness of 60 mm. The welding temperature field is measured by means of a K-type thermocouple and numerical simulation. The results show that the thermal cycle curve obtained by the homogeneous body heat source simulation is basically consistent with the thermal cycle curve measured during the experiment, and the simulation results of the molten pool morphology are also consistent with the actual macroscopic morphology of the weld

Healthy apple snack developed using microwaves

[EN] The MW heating at early or at final stage of drying process to obtain a crispy apple snack was studied. The effect of MW power and time of application was also evaluated on colour, texture, physico-chemical and sensory properties. Apple snack obtained with the MW heating (7.5 min at 3.000 W) at early stage after an osmotic pre-treatment resulted in apple slices more porous and with better sensory attributes than if it is applied at later stage of drying.Fartdinov, D.; Comaposada, J.; Muñoz, I.; De Wit, N.; Gou, P.; Guàrdia, M. (2018). Healthy apple snack developed using microwaves. En IDS 2018. 21st International Drying Symposium Proceedings. Editorial Universitat Politècnica de València. 957-964. https://doi.org/10.4995/IDS2018.2018.7655OCS95796

A Unified Account to Measure Words in Mandarin

Penn Linguistics Conference (PLC 38), Pennsylvania, USA, 28-30 March, 2014Department of Chinese and Bilingual StudiesRefereed conference pape

Sobre la tradición paremiográfica homérica

Fil: Guevara de Álvarez, María Estela

Alive, September-October 1986

A newsletter published for Deaf Catholics in Jacksonville, F

General Characteristics of a Airspeed System using Fuselage Static Vents on a Swept-Wing Airplane

Studies have been made by the NACA wing-flow method of the use of fuselage static orifices between the wing and tail of a swept-wing airplane for possible application to service airspeed installations. The tests were made at zero angle of attack. The results indicate that, although the maximum errors are large, these locations are usable from the consideration that the local Mach numbers at the locations studied are sensitive to variation of the true Mach number within the test Mach number range of 0.7 to 1.2. The maximum errors in Mach number in the subsonic range varied from zero for the most forward location to -0.05 for the most rearward location (indicated Mach number less than true). At Mach numbers above 1.0, the maximum errors were from 0.14 for the most forward location to 0.04 for the most rearward location