Initial experimental results from the new DLR-High Vacuum Plume Test Facility STG

1997 ◽  
Author(s):  
Georg Dettleff ◽  
Klaus Plaehn ◽  
Georg Dettleff ◽  
Klaus Plaehn
Keyword(s):  
High Vacuum ◽  
Experimental Results ◽  
Test Facility

Effects of Wind on the Heat Flow of FPSO Topsides Subject to Fire: An Experimental and Numerical Study

2010 ◽  
Author(s):  
Joon Young Yoon ◽  
Seong Hwan Kim ◽  
Gwon Cheol Yu ◽  
Jung Kwan Seo ◽  
Bong Ju Kim ◽  
...  
Keyword(s):  
Thermal Diffusion ◽  
Numerical Study ◽  
Wind Tunnel Test ◽  
Experimental Results ◽  
Test Facility ◽  
Test Model ◽  
Cfd Simulations ◽  
Fire Engineering ◽  
Diffusion Characteristics ◽  
Fire Loads

The aim of this paper is to examine the effect of wind on the thermal diffusion characteristics of floating production storage and offloading (FSPO) topside models subject to fire. It is motivated by the need to identify the fire loads on FPSO topsides, taking into account the effects of wind speed and direction. The results of an experimental and numerical study undertaken for these purposes are reported here. This paper is part of Phase II of the joint industry project on explosion and fire engineering of FPSOs (EFEF JIP) [1]. An experiment was performed on a 1/14-scale FPSO topside model using a wind tunnel test facility. The locations of the heat source of the fire were varied, as were the speed and direction of the wind, and the temperature distribution was measured. Computational fluid dynamics (CFD) simulations using the ANSYS CFX program were performed on the test model, with the results obtained compared with the experimental results. It is concluded that wind has a significant effect on the thermal diffusion characteristics of the test model and that the CFD simulations are in good agreement with the experimental results. The insights developed in this study will be very useful for the fire engineering of FPSO topsides.

scholarly journals STG-CT: High-vacuum plume test facility for chemical thrusters

2016 ◽  
Vol 2 ◽  
Author(s):  
Martin Grabe
Keyword(s):  
Liquid Helium ◽  
Molecular Hydrogen ◽  
High Vacuum ◽  
Test Facility ◽  
Plume Flow

The STG-CT, operated by the DLR Institute for Aerodynamics and Flow Technology in Göttingen, is a vacuum facility specically designed to provide and maintain a space-like vacuum environment for researching plume flow and plume impingement from satellite reaction control thrusters. Its unique liquid-helium driven cryopump of 30m2 allows maintaining a background pressure <10^-5 mbar even when molecular hydrogen is a plume constituent.

scholarly journals STG-ET: DLR electric propulsion test facility

2017 ◽  
Vol 3 ◽  
Author(s):  
Andreas Neumann
Keyword(s):  
Electric Propulsion ◽  
Vacuum Chamber ◽  
High Vacuum ◽  
Test Facility ◽  
Space Propulsion ◽  
Beam Dump ◽  
Pumping System ◽  
Thrust Measurement ◽  
Electric Space

DLR operates the High Vacuum Plume Test Facility Göttingen – Electric Thrusters (STG-ET). This electric propulsion test facility has now accumulated several years of EP-thruster testing experience. Special features tailored to electric space propulsion testing like a large vacuum chamber mounted on a low vibration foundation, a beam dump target with low sputtering, and a performant pumping system characterize this facility. The vacuum chamber is 12.2m long and has a diameter of 5m. With respect to accurate thruster testing, the design focus is on accurate thrust measurement, plume diagnostics, and plume interaction with spacecraft components. Electric propulsion thrusters have to run for thousands of hours, and with this the facility is prepared for long-term experiments. This paper gives an overview of the facility, and shows some details of the vacuum chamber, pumping system, diagnostics, and experiences with these components.

Design and Testing of a Can Combustor for a Small Gas Turbine Application

2013 ◽  
Author(s):  
K. V. L. Narayana Rao ◽  
N. Ravi Kumar ◽  
G. Ramesha ◽  
M. Devathathan
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Gas Turbines ◽  
Pressure Loss ◽  
High Energy ◽  
Experimental Results ◽  
High Mass ◽  
Test Facility ◽  
Design Requirements

Can type combustors are robust, with ease of design, manufacturing and testing. They are extensively used in industrial gas turbines and aero engines. This paper is mainly based on the work carried out in designing and testing a can type combustion chamber which is operated using JET-A1 fuel. Based on the design requirements, the combustor is designed, fabricated and tested. The experimental results are analysed and compared with the design requirements. The basic dimensions of the combustor, like casing diameter, liner diameter, liner length and liner hole distribution are estimated through a proprietary developed code. An axial flow air swirler with 8 vanes and vane angle of 45 degree is designed to create a re-circulation zone for stabilizing the flame. The Monarch 4.0 GPH fuel nozzle with a cone angle of 80 degree is used. The igniter used is a high energy igniter with ignition energy of 2J and 60 sparks per minute. The combustor is modelled, meshed and analysed using the commercially available ansys-cfx code. The geometry of the combustor is modified iteratively based on the CFD results to meet the design requirements such as pressure loss and pattern factor. The combustor is fabricated using Ni-75 sheet of 1 mm thickness. A small combustor test facility is established. The combustor rig is tested for 50 Hours. The experimental results showed a blow-out phenomenon while the mass flow rate through the combustor is increased beyond a limit. Further through CFD analysis one of the cause for early blow out is identified to be a high mass flow rate through the swirler. The swirler area is partially blocked and many configurations are analysed. The optimum configuration is selected based on the flame position in the primary zone. The change in swirler area is implemented in the test model and further testing is carried out. The experimental results showed that the blow-out limit of the combustor is increased to a good extent. Hence the effect of swirler flow rate on recirculation zone length and flame blow out is also studied and presented. The experimental results showed that the pressure loss and pattern factor are in agreement with the design requirements.

Experimental Investigation of the Maximum Heat Transport in Triangular Grooves

1996 ◽  
Vol 118 (3) ◽  
pp. 740-746 ◽  
Author(s):  
H. B. Ma ◽  
G. P. Peterson
Keyword(s):  
Experimental Investigation ◽  
Heat Transport ◽  
Heat Pipes ◽  
Effective Area ◽  
Experimental Results ◽  
Test Facility ◽  
Working Fluid ◽  
Maximum Heat ◽  
Pressure Losses ◽  
Micro Heat Pipes

An experimental investigation was conducted and a test facility constructed to measure the capillary heat transport limit in small triangular grooves, similar to those used in micro heat pipes. Using methanol as the working fluid, the maximum heat transport and unit effective area heat transport were experimentally determined for ten grooved plates with varying groove widths, but identical apex angles. The experimental results indicate that there exists an optimum groove configuration, which maximizes the capillary pumping capacity while minimizing the combined effects of the capillary pumping pressure and the liquid viscous pressure losses. When compared with a previously developed analytical model, the experimental results indicate that the model can be used accurately to predict the heat transport capacity and maximum unit area heat transport when given the physical characteristics of the working fluid and the groove geometry, provided the proper heat flux distribution is known. The results of this investigation will assist in the development of micro heat pipes capable of operating at increased power levels with greater reliability.

Test Results on the ARL 19 Supersonic Blade Cascade

1988 ◽  
Vol 110 (4) ◽  
pp. 450-455 ◽  
Author(s):  
A. Fourmaux ◽  
R. Gaillard ◽  
G. Losfeld ◽  
G. Meauze´
Keyword(s):  
Theoretical Analysis ◽  
Data Reduction ◽  
Experimental Results ◽  
Test Facility ◽  
Experimental Program ◽  
Test Model ◽  
Test Results ◽  
Blade Cascade

This paper presents the ONERA contribution in a joint experimental program on the aerodynamics of supersonic airfoil cascades. The first part deals with the specific ONERA way of running cascade tests: description of the test facility, the test model, the instrumentation, and data reduction. Then, after a brief theoretical analysis of the ARL 19 cascade, some experimental results are presented and discussed.

A Proposal for Shaft Power Prediction of Centrifugal Compressor Under Wet Gas Conditions

2018 ◽  
Author(s):  
Daisuke Kawaguchi ◽  
Katsutoshi Kobayashi ◽  
Lars Eirik Bakken
Keyword(s):  
Liquid Film ◽  
Centrifugal Force ◽  
Centrifugal Compressor ◽  
Science And Technology ◽  
Experimental Results ◽  
Test Facility ◽  
Power Prediction ◽  
Trailing Edge ◽  
Wet Gas ◽  
Shaft Power

In this study, the influence of wet gas on the fluid performance of a centrifugal compressor was evaluated using a test facility in the Norwegian University of Science and Technology, NTNU. The experimental results indicated that the polytropic efficiency decreased with increases in LMF. One factor of decrease of the polytropic efficiency was an increase in the shaft power. Moreover, we hypothesized that the liquid film on the inner wall of the impeller was discharged from the trailing edge at a circumferential speed by a centrifugal force. Then an expression to predict the shaft power under wet gas conditions on the basis of the hypothesis was built and it was verified that the ratio of the predicted and experimental shaft power agreed well.

Experimental Study of Interfacial Contacting Process Controlled by Power Law Creep

1995 ◽  
Vol 117 (3) ◽  
pp. 336-340 ◽  
Author(s):  
Y. Takahashi ◽  
M. Tanimoto
Keyword(s):  
Power Law ◽  
Contact Process ◽  
High Vacuum ◽  
Deformation Mode ◽  
Experimental Results ◽  
Void Coalescence ◽  
Bonding Pressure ◽  
Interfacial Contact ◽  
Asperity Angle ◽  
Power Law Creep

Interfacial contacting processes under a high temperature and a high bonding pressure (T = 973 K, P = 30 MPa) are experimentally studied, using oxygen free copper. The faying surfaces were machined by lathe, resulting in controlled regular surface asperities. The asperity angle of surface ridges was changed from 10 to 60 deg. The change in the interfacial deformation mode with the asperity angle has been investigated. Results show the interfacial contact process is strongly influenced by the asperity angle (shape of surface ridge). The bonding tests were carried out in high vacuum atmosphere (10−4 Pa) so that the surface oxide film need not be considered. Experimental results are in good agreement with the results calculated by a finite element model, in which the interfacial contact is assumed to be produced by power law creep alone. It was thus suggested that void coalescence is governed by power law creep under the present test conditions (T = 973 K and P = 30 MPa) except for the final stage of bonding. Experimental results also suggest that the elementary rate process of interfacial contact due to power law creep is classified into two types; surface folding and interfacial expansion. Here, the surface folding is the phenomenon that two faying surfaces are overlapped to each other and the interfacial expansion means that the bonded interface area is extended along the bond-interface.

scholarly journals Experimental Research on Passive Residual Heat Removal System of Chinese Advanced PWR

2014 ◽  
Vol 2014 ◽  
pp. 1-8 ◽  
Author(s):  
Zhuo Wenbin ◽  
Huang Yanping ◽  
Xiao Zejun ◽  
Peng Chuanxin ◽  
Lu Sansan
Keyword(s):  
Steady State ◽  
Scaling Laws ◽  
Heat Removal ◽  
Experimental Results ◽  
Test Facility ◽  
Semiempirical Model ◽  
Pressurized Water ◽  
Heat Removal System ◽  
Removal System ◽  
Residual Heat

Passive residual heat removal system (PRHRS) for the secondary loop is one of the important features for Chinese advance pressurized water reactor (CAPWR). To prove the safety characteristics of CAPWR, serials of experiments have been done on special designed PRHRS test facility in the former stage. The test facility was built up following the scaling laws to preserve the similarity to CAPWR. A total of more than 300 tests have been performed on the test facility, including 90% steady state cases and 10% transient cases. A semiempirical model was generated for passive heat removal functions based on the experimental results of steady state cases. The dynamic capability characteristics and reliability of passive safety system for CAPWR were evidently proved by transient cases. A new simulation code, MISAP2.0, has been developed and calibrated by experimental results. It will be applied in future design evaluation and optimization works.

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