scholarly journals Uniform temperature profile for a dense array CPV receiver under non uniform illumination profile

2014 ◽  
Author(s):  
Sara Riera ◽  
Jérôme Barrau ◽  
Arnaud Perona ◽  
Alain Dollet ◽  
Joan I. Rosell ◽  
...  
Keyword(s):  
Temperature Profile ◽  
Uniform Temperature ◽  
Dense Array ◽  
Uniform Illumination

Control Algorithms for Inductors Movement in Induction Heated Calenders

2012 ◽  
Vol 17 (4) ◽  
pp. 51-57
Author(s):  
Andrzej Frązyk ◽  
Piotr Urbanek ◽  
Jacek Kucharski
Keyword(s):  
Temperature Profile ◽  
Induction Heating ◽  
Control Algorithms ◽  
Uniform Temperature ◽  
Cylinder Axis ◽  
Steel Cylinder ◽  
Modern Technologies ◽  
Temperature Amplitude

Abstract Fixed, placed at regular distances inductors for induction heating of a rotating steel cylinder do not provide sufficiently uniform temperature profile along cylinder axis required by modern technologies,. The article examines the influence of inductors movement along the cylinder axis on the reduction of pick-to- pick temperature amplitude.

Thermal and electrical performance of the dense-array concentrating photovoltaic (DA-CPV) system under non-uniform illumination

2019 ◽  
Vol 250 ◽  
pp. 904-915 ◽  
Author(s):  
Xing Ju ◽  
Xinyu Pan ◽  
Zheyang Zhang ◽  
Chao Xu ◽  
Gaosheng Wei
Keyword(s):  
Electrical Performance ◽  
Dense Array ◽  
Uniform Illumination

Inelastic Behaviour of Concrete/Steel Composite Beam in Fire

2007 ◽  
Vol 340-341 ◽  
pp. 131-136
Author(s):  
M. Bill Wong
Keyword(s):  
Temperature Profile ◽  
Cross Section ◽  
Elastic Limit ◽  
Beam Deflection ◽  
Steel Beam ◽  
Uniform Temperature ◽  
Inelastic Behaviour ◽  
Steel Composite ◽  
The Cross ◽  
In Fire

The configuration of a steel beam in a concrete/steel composite floor in fire gives rise to a non-uniform temperature profile across the depth of the cross-section. This temperature profile affects the deflection of the steel beam in two ways: thermal bowing due to non-uniform thermal strains and beam deflection due to imposed loads. The beam deflection becomes larger as the elastic properties of the steel beam deteriorate when the temperature is rising. The deflection increases rapidly when the cross-section of the steel beam starts to yield. This paper presents a method for the calculation of the total deflection of a steel beam in a steel/concrete composite floor in fire when the beam is loaded beyond its elastic limit. In this study, the steel beam is assumed to support the concrete floor slab simply at its ends without composite actions.

scholarly journals Open-Path FTIR Spectral Radiation Intensity Of Hot Combustion Gases – Measurement And Interpretation

2015 ◽  
Vol 22 (2) ◽  
pp. 193-204 ◽  
Author(s):  
Sławomir Cięszczyk
Keyword(s):  
Temperature Profile ◽  
Radiation Intensity ◽  
Combustion Process ◽  
Optical Path Length ◽  
Qualitative Description ◽  
Maximum Temperature ◽  
Uniform Temperature ◽  
Spectral Radiation ◽  
Combustion Gases ◽  
Dominant Feature

Abstract Spectral remote sensing is a very popular method in atmospheric monitoring. The paper presents an approach that involves mid-infrared spectral measurements of combustion processes. The dominant feature in this spectral range is CO2 radiation, which is used to determine the maximum temperature of nonluminous flames. Efforts are also made to determine the temperature profile of hot CO2, but they are limited to the laboratory conditions. The paper presents an analysis of the radiation spectrum of a non-uniform-temperature gas environment using a radiative transfer equation. Particularly important are the presented experimental measurements of various stages of the combustion process. They allow for a qualitative description of the physical phenomena involved in the process and therefore permit diagnostics. The next step is determination of a non-uniform-temperature profile based on the spectral radiation intensity with the 8 m optical path length.

Heat transfer measurements on an intermediate-pressure nozzle guide vane tested in a rotating annular turbine facility, and the modifying effects of a non-uniform inlet temperature profile

2003 ◽  
Vol 217 (4) ◽  
pp. 421-431 ◽  
Author(s):  
T Povey ◽  
K. S. Chana ◽  
T. V. Jones
Keyword(s):  
Heat Transfer ◽  
Temperature Profile ◽  
Heat Transfer Rate ◽  
Transfer Rate ◽  
Guide Vane ◽  
Temperature Gradients ◽  
Inlet Temperature ◽  
Uniform Temperature ◽  
Nozzle Guide Vane ◽  
Nozzle Guide

In modern gas turbine engines there exist significant temperature gradients in the combustor exit flow. These gradients arise because both fuel and dilution air are introduced within the combustor as discrete jets. The effects of this non-uniform temperature field on the aerodynamics and heat transfer rate distributions of nozzle guide vanes and turbine blades is difficult to predict, although an increased understanding of the effects of temperature gradients would enhance the accuracy of estimates of turbine component life and efficiency. Low-frequency measurements of heat transfer rate have been conducted on an annular transonic intermediate-pressure (IP) nozzle guide vane operating downstream of a high-pressure (HP) rotating turbine stage. Measurements were conducted with both uniform and non-uniform inlet temperature profiles. The non-uniform temperature profile included both radial and circumferential gradients of temperature. Experiments were conducted in the isentropic light piston facility at QinetiQ Pyestock, a short-duration engine-size turbine facility with 1.5 turbine stages, in which Mach number, Reynolds number and gas—wall temperature ratios are correctly modelled. Experimental heat transfer results are compared with predictions performed using boundary layer methods.

Effects of Combustor Exit Temperature Profile on Adiabatic Effectiveness of Leakage Flow Film Cooling Over an Axisymmetric Endwall

2013 ◽  
Author(s):  
Yuh Yen Seah ◽  
Ryan Erickson ◽  
Terrence Simon ◽  
Hee-Koo Moon ◽  
Luzeng Zhang
Keyword(s):  
Temperature Distribution ◽  
Temperature Profile ◽  
Film Cooling ◽  
Base Case ◽  
Leakage Flow ◽  
Uniform Temperature ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness ◽  
Cooling Flow ◽  
Exit Temperature

The effects of a representative combustor exit temperature profile on leakage flow film cooling effectiveness were experimentally documented. This was done in a stationary, linear blade row cascade with an axisymmetric blade platform of dolphin-nose-shape. Endwall adiabatic film cooling effectiveness distributions and near-endwall passage thermal fields are documented. Results from the case with a representative combustor exit temperature profile are compared to those with other combustor exit temperature profiles including a base case with a uniform temperature distribution. All cases were done in the same facility over a range of disk cavity leakage flow rates. This study quantifies the sensitivity of endwall film cooling due to coolant in the leakage flow and in the approach flow to the shape of the combustor exit temperature profile. The results indicate that leakage flow film cooling effectiveness is significantly lower with a well-mixed (uniform temperature) combustor exit temperature profile than in cases in which the combustor exit temperature distribution is strongly variable. That is, it is demonstrated that combustor cooling flow aids endwall protection considerably. It is also shown that leakage flow has only a mild influence over the endwall cooling that can be attributed to coolant in the approach flow.

Heat Transfer and Aerodynamics of an Intermediate Pressure Nozzle Guide Vane With and Without Inlet Temperature Non-Uniformity

2003 ◽  
Author(s):  
Kam S. Chana ◽  
T. Povey ◽  
Terry V. Jones
Keyword(s):  
Heat Transfer ◽  
Temperature Profile ◽  
Guide Vane ◽  
Turbine Blades ◽  
Inlet Temperature ◽  
Uniform Temperature ◽  
Intermediate Pressure ◽  
Nozzle Guide Vane ◽  
Nozzle Guide ◽  
Pressure Nozzle

In modern gas turbine engines the combustor exit flow has a non-uniform temperature profile because of the discrete nature of the injection of fuel and dilution air, and the wall cooling flows. The affect of this non-uniform temperature profile on the aerodynamics and heat transfer rate of nozzle guide vanes and turbine blades is difficult to predict, and knowledge of this is important for estimating turbine component life and efficiency. Measurements of heat transfer have been conducted on an annular transonic intermediate pressure nozzle guide vane operating downstream of a high pressure rotating turbine stage. Measurements were made with and without a radial and circumferential inlet temperature profile. The experiments were conducted in the Isentropic Light Piston Facility (ILPF) at QinetiQ, a short duration engine size turbine facility with 1.5 turbine stages, in which Mach number, Reynolds number and gas-to-wall temperature ratios are correctly modelled. Experimental results are compared to predictions performed using boundary layer methods.

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