New Modular Test Rig for Unsteady Performance Assessment of Automotive Turbocharger Turbines

2017 ◽  
Author(s):  
Paul Lyttek ◽  
Harald Roclawski ◽  
Martin Böhle ◽  
Marc Gugau
Keyword(s):  
Gas Flow ◽  
Measurement Techniques ◽  
Basic Research ◽  
Standard Test ◽  
Operating Conditions ◽  
Test Facility ◽  
Exhaust Gas ◽  
Special Device ◽  
Test Rig ◽  
Inflow Conditions

Standard test rigs for basic research on turbochargers usually do not provide the capability of periodically changing, instantaneous process values, which are characteristic for the real application of these turbines. The challenge of testing the performance potential of turbocharger turbines under pulsating inflow conditions is mainly originated by the complex compatibility of two main issues that need to be implemented at a test facility: Firstly, a special device is required that reproducibly provides real engine-like exhaust gas pulsations with some variability representing different engine operating conditions. Secondly, appropriate real time measurement techniques for all significant transient values are required to measure both, instantaneous turbine inflow conditions and turbine power output. This paper presents a new developed test rig that enables a preferably high overlap between the above mentioned supply of approximately real engine exhaust gas conditions and the fundamental and scientifically based attempt of unsteady gas flow examinations.

Simplified Method for Fuel Quality Prediction

2005 ◽  
Author(s):  
Aravind Sivaraman ◽  
Sridhar Ranganathan ◽  
Shashank Tangirala ◽  
G. Lakshmi Narayana Rao
Keyword(s):  
Diesel Engine ◽  
Standard Test ◽  
Operating Conditions ◽  
Exhaust Gas ◽  
Test Rig ◽  
Single Cylinder ◽  
Fuel Ratio ◽  
Test Conditions ◽  
Quality Rating

The objective of this work is to compare the quality of various diesel fuels using a normal engine and carrying out the test under the actual operating conditions of the engine, unlike the conventional test methods that uses standard test conditions. The standard test conditions involve the running of the diesel engine test rig at a speed of around 800 rpm, which is not the condition when the fuel is actually being used, as the operational speed of commercial engines is around 1500–2000 rpm. Also the non-engine based quality rating methods are not economically liable and are inaccurate as they depend too much on the chemical nature of the fuel. So, the objective of this work is to develop a generalized quality rating procedure with less number of parameters, with a simpler and cheaper method compared to other available methods. A single cylinder diesel engine was used to study the ignition quality of various reference fuels of known Cetane numbers. A relatively simple and compact setup was used, by modifying the existing test rig. The inlet manifold was incorporated with an airflow control valve so that the quantity of air let into the cylinder can be varied. The exhaust gas manifold was modified to enable easier observation of the exhaust gas. The single cylinder diesel engine was made to run at two distinct conditions, namely, the normal and white-puff / critical condition, with the reference fuels of known cetane numbers. The quantity of air available for the fuel to combust is the only difference between the two conditions. The air-fuel ratio of each fuel under both the conditions was continuously monitored. A correlation was developed between the critical air-fuel ratios and the corresponding Cetane numbers. From this correlation, a test fuel can be rated easily by finding the air-fuel ratio, by running it in the same engine at an identical load, at an instant when the “white puff” is observed.

Experimental Inverstigations On the Pressure Fluctuations in the Sealing Gap of Dry Gas Seals with Embedded Pressure Sensors

2021 ◽  
Author(s):  
Jingjing Luo ◽  
Dieter Brillert
Keyword(s):  
High Speed ◽  
Gas Flow ◽  
Static Pressure ◽  
Pressure Sensors ◽  
Operating Conditions ◽  
Test Facility ◽  
Experimental Investigations ◽  
Mechanical Seals ◽  
Process Gas ◽  
Sealing Gap

Abstract Dry gas lubricated non-contacting mechanical seals (DGS), most commonly found in centrifugal compressors, prevent the process gas flow into the atmosphere. Especially when high speed is combined with high pressure, DGS is the preferred choice over other sealing alternatives. In order to investigate the flow field in the sealing gap and to facilitate the numerical prediction of the seal performance, a dedicated test facility is developed to carry out the measurement of key parameters in the gas film. Gas in the sealing film varies according to the seal inlet pressure, and the thickness of gas film depends on this fluctuated pressure. In this paper, the test facility, measurement methods and the first results of static pressure measurements in the sealing gap of the DGS obtained in the described test facility are presented. An industry DGS with three-dimensional grooves on the surface of the rotating ring, where experimental investigations take place, is used. The static pressure in the gas film is measured, up to 20 bar and 8,100 rpm, by several high frequency ultraminiature pressure transducers embedded into the stationary ring. The experimental results are discussed and compared with the numerical model programmed in MATLAB, the characteristic and magnitude of which have a good agreement with the numerical simulations. It suggests the feasibility of measuring pressure profiles of the standard industry DGS under pressurized dynamic operating conditions without altering the key components of the seal and thereby affecting the seal performance.

scholarly journals Temperature impact on dusty and cleaned photovoltaic module exposed in sub-Saharan outdoor conditions

2018 ◽  
Vol 9 ◽  
pp. 8 ◽  
Author(s):  
N'detigma Kata ◽  
Y. Moussa Soro ◽  
Djicknoum Diouf ◽  
Arouna Darga ◽  
A. Seidou Maiga
Keyword(s):  
Standard Test ◽  
Operating Conditions ◽  
Solar Irradiation ◽  
Test Facility ◽  
Photovoltaic Module ◽  
Significant Drop ◽  
Single Junction ◽  
Irradiation Level ◽  
Sub Saharan ◽  
Module Performance

In this work, impacts of temperature and dust cleaning on photovoltaic module performance operating in sub-Saharan's climate are investigated. Two single junction technologies, monocrystalline and polycrystalline silicon, and one micromorph (amorphous/micrystalline) thin film silicon tandem technology are considered. We have recorded at the same time under real operating conditions, the module temperature and the current versus voltage characteristics of each module, and the local solar irradiation. All the measurements were performed with the outdoor monitoring and test facility located at Ouagadougou in Burkina Faso. The results show the drop of generated power of dusty modules for the same irradiation level. Between April and June (where temperatures are higher) a significant drop of output power is observed, despite a daily cleaning. Furthermore, performance losses are observed for all technologies compared to that under standard test conditions. However, the micromorph silicon tandem technology with low temperature sensitivity present the less losses in performance compared to the monocrystalline and the polycrystalline single junction modules, even if the modules are not cleaned.

Design of a New Experimental Rig for Thermal Cyclic Testing of Combustor Liner Tiles

2008 ◽  
Author(s):  
C. Mende ◽  
O. Liedtke ◽  
A. Schulz ◽  
H.-J. Bauer
Keyword(s):  
Low Cycle Fatigue ◽  
Operating Conditions ◽  
Quality Data ◽  
Test Facility ◽  
Test Rig ◽  
Design Data ◽  
High Quality Data ◽  
Damage Models ◽  
Combustor Liner ◽  
Experimental Rig

This paper describes the design and operation of a new test rig, which allows the simulation of real engine operating conditions leading to Low-Cycle Fatigue of combustor liner tiles. The experimental setup will provide high-quality data for the development of damage models. At first the design data of the test rig will be derived from the relevant damage mechanisms in Combustor Liner Tiles (CLT). Then the construction of the test rig and its integration into an existing high temperature high pressure test facility will be elucidated. Finally experimental data of a typical simulated thermal cycle is shown.

scholarly journals Design and Testing of a 10KW Steam Turbine for Steam Turbochargers

1985 ◽  
Author(s):  
M. Rautenberg ◽  
M. Malobabic ◽  
A. Mobarak ◽  
M. Abdel Kader
Keyword(s):  
Waste Heat ◽  
Rankine Cycle ◽  
Operating Conditions ◽  
Experimental Investigations ◽  
Exhaust Gas ◽  
Test Rig ◽  
Pelton Turbine ◽  
Partial Admission ◽  
Turbine Design ◽  
Design And Testing

A Clausius-Rankine-cycle has been proposed to recover waste heat from a piston engine. This waste heat is then used to supercharge the cylinders by means of a steam turbocharger. The advantage of using this steam turbocharger system is to avoid the losses due to the engine back pressure which accompany the use of the conventional exhaust gas turbocharger. The mass flow rate of turbines for steam turbochargers in the range from 1 to 10 kW is about 0.03 to 0.08 kg/s. This implies a special turbine design, characterised by partial admission and supersonic flow, which unfortunately leads to low turbine efficiencies. A small Pelton turbine for steam has been designed and produced. The turbine is connected to the radial compressor of a conventional exhaust gas turbocharger which works, in this case, as a brake to dissipate the generated turbine power. A special test rig has been built to carry out the experimental investigations on the proposed Pelton turbine. The test rig is supplied with superheated steam from the University’s power plant. Two different rotors for this Pelton turbine have been tested under the same operating conditions (rotor 2 see Fig. 1). Some experimental test results of a special Pelton turbine are presented and discussed in this report.

Experimental Investigation of the Flow in the Pipe Diffuser of a Centrifugal Compressor Stage Under Selected Parameter Variations

2009 ◽  
Author(s):  
Uwe Zachau ◽  
Reinhard Niehuis ◽  
Herwart Hoenen ◽  
David C. Wisler
Keyword(s):  
Centrifugal Compressor ◽  
Measurement Techniques ◽  
Operating Conditions ◽  
Tip Clearance ◽  
Test Facility ◽  
Experimental Investigations ◽  
Pressure Side ◽  
Compressor Stage ◽  
Diffuser Flow ◽  
Parameter Variations

On a centrifugal compressor test facility various experimental investigations have been carried out contributing a valuable gain in knowledge on the fundamental flow physics within passage type diffusers. An extensive measurement series using various steady, unsteady and laser optical measurement techniques has been performed to detect the unsteady, highly three dimensional diffuser flow under various realistic operating conditions. Zachau et al. [1] presented the test facility and the results gathered under nominal conditions. As a follow-up the results of investigated parameter variations are now presented, covering bleed variations, impeller tip clearance and impeller-diffuser misalignment studies. The data is compared to the benchmark created from the nominal baseline data sets and evaluated with respect to the compressor stage performance. Zachau et al. [1] found that under nominal conditions the flow in the pipe diffuser separates on the pressure side in the first half of the pipe. In the last 30% of the pipe hardly any deceleration of the flow takes place. From this, special attention is given to the investigated parameter variations regarding a first proposal for a diffuser design change, which consists in shortening the diffuser. The results for each parameter variation are evaluated in detail in direct comparison to the nominal baseline configuration underlining the conclusion made earlier that the diffuser flow always separates on the pressure side with negligible deceleration in the last third of the diffusing pipe.

Coal Ash Deposition on Nozzle Guide Vanes: Part I—Experimental Characteristics of Four Coal Ash Types

2011 ◽  
Author(s):  
J. Webb ◽  
B. Casaday ◽  
B. Barker ◽  
J. P. Bons ◽  
A. D. Gledhill ◽  
...  
Keyword(s):  
Film Cooling ◽  
Gas Flow ◽  
Guide Vane ◽  
Ambient Pressure ◽  
Coal Ash ◽  
Leading Edge ◽  
Operating Conditions ◽  
Test Facility ◽  
Gas Temperature ◽  
Nozzle Guide

An accelerated deposition test facility was operated with three different coal ash species to study the effect of ash composition on deposition rate and spatial distribution. The facility seeds a combusting (natural gas) flow with 10–20 micron mass mean diameter coal ash particulate. The particulate-laden combustor exhaust is accelerated through a rectangular-to-annular transition duct and expands to ambient pressure through a nozzle guide vane annular sector. For the present study, the annular cascade consisted of two CFM56 aero-engine vane doublets; comprising three full passages and two half passages of flow. The inlet Mach number (0.1) and gas temperature (1100°C) are representative of operating turbines. Ash samples were tested from the three major coal ranks: lignite, subbituminous, and bituminous. Investigations over a range of inlet gas temperatures from 900°C to 1120°C showed that deposition increased with temperature, though the threshold for deposition varied with ash type. Deposition levels varied with coal rank, with lignite producing the largest deposits at the lowest temperature. Regions of heightened deposition were noted; the leading edge and pressure surface being particularly implicated. Scanning electron microscopy was used to identify deposit structure. For a limited subset of tests, film cooling was employed at nominal design operating conditions but provided minimal protection in cases of severe deposition.

The 2-Stage Axial Turbine Test Facility “LISA”

2001 ◽  
Author(s):  
M. Sell ◽  
J. Schlienger ◽  
A. Pfau ◽  
M. Treiber ◽  
R. S. Abhari
Keyword(s):  
Unsteady Flow ◽  
Mass Flow ◽  
Measurement Techniques ◽  
Operating Conditions ◽  
Test Facility ◽  
Two Stage ◽  
Axial Turbine ◽  
Aerodynamic Pressure ◽  
Second Stage ◽  
The Impact

This paper describes the design and construction of a new two stage axial turbine test facility, christened “Lisa”. The research objective of the rig is to study the impact (relevance) of unsteady flow phenomena upon the aerodynamic performance, this being achieved through the use of systematic studies of parametric changes in the stage geometry and operating point. Noteworthy in the design of the rig is the use of a twin shaft arrangement to decouple the stages. The inner shaft carries the load from the first stage whilst the outer is used with an integral torque-meter to measure the loading upon the second stage alone. This gives an accurate measurement of the loading upon the aerodynamically representative second stage, which possesses the correct stage inlet conditions in comparison to the full two stage machine which has an unrealistic axial inlet flow at the first stator. A calibrated Venturi nozzle measures the mass flow at an accuracy of below 1%, from which stage efficiencies can be derived. The rig is arranged in a closed loop system. The turbine has a vertical arrangement and is connected through a gear box to a generator system that works as a brake to maintain the desired operating speed. The turbine exit is open to ambient pressure. The rig runs at a low pressure ratio of 1.5. The maximum Mach number at stator exit is 0.3 at an inlet pressure of 1.5 bar. The maximum mass flow is 14 kg/sec. Nominal rotor design speed is 3000 RPM. The tip to hub blade ratio is 1.29, and the nominal axial chord is 50 mm. The rig is designed to accommodate a broad range of measurement techniques, but with a strong emphasis upon unsteady flow methods, for example fast response aerodynamic pressure probes for time-resolved flow measurements. The first section of this paper describes the overall test facility hardware. This is followed by a detailed focus on the torque measurement device including stage efficiency measurements at operating conditions in Lisa. Discussion of measurement techniques completes the paper.

Coal Ash Deposition on Nozzle Guide Vanes—Part I: Experimental Characteristics of Four Coal Ash Types

2012 ◽  
Vol 135 (2) ◽  
Author(s):  
J. Webb ◽  
B. Casaday ◽  
B. Barker ◽  
J. P. Bons ◽  
A. D. Gledhill ◽  
...  
Keyword(s):  
Film Cooling ◽  
Gas Flow ◽  
Guide Vane ◽  
Ambient Pressure ◽  
Coal Ash ◽  
Leading Edge ◽  
Operating Conditions ◽  
Test Facility ◽  
Gas Temperature ◽  
Nozzle Guide

An accelerated deposition test facility was operated with four different coal ash species to study the effect of ash composition on deposition rate and spatial distribution. The facility seeds a combusting (natural gas) flow with 10–20 micron mass mean diameter coal ash particulate. The particulate-laden combustor exhaust is accelerated through a rectangular-to-annular transition duct and expands to ambient pressure through a nozzle guide vane annular sector. For the present study, the annular cascade consisted of two CFM56 aero-engine vane doublets, comprising three full passages and two half passages of flow. The inlet Mach number (0.1) and gas temperature (1100 °C) are representative of operating turbines. Ash samples were tested from the three major coal ranks: lignite, subbituminous, and bituminous. Investigations over a range of inlet gas temperatures from 900 °C to 1120 °C showed that deposition increased with temperature, though the threshold for deposition varied with ash type. Deposition levels varied with coal rank, with lignite producing the largest deposits at the lowest temperature. Regions of heightened deposition were noted; the leading edge and pressure surface being particularly implicated. Scanning electron microscopy was used to identify deposit structure. For a limited subset of tests, film cooling was employed at nominal design operating conditions but provided minimal protection in cases of severe deposition.

A New Test Facility for Investigating the Interaction Between Swirl Flow and Wall Cooling Films in Combustors

2009 ◽  
Author(s):  
B. Wurm ◽  
A. Schulz ◽  
H.-J. Bauer
Keyword(s):  
Gas Turbines ◽  
Static Pressure ◽  
Thermal Analyses ◽  
Thermal Studies ◽  
Swirl Flow ◽  
Operating Conditions ◽  
Test Facility ◽  
Wall Region ◽  
Test Rig ◽  
Combustor Liner

Swirl stabilization of flames is typically used in combustors of aero engines and gas turbines for power generation. In the near wall region of the combustor liner, the swirling flow interacts in a very particular way with wall cooling films. This interaction and its effect on the local wall cooling performance gave reason to design and commission a new atmospheric test rig for detailed aerodynamic and thermal studies. The new test rig includes three burners in a planar arrangement. Special emphasis was placed on the simulation of realistic operating conditions as Reynolds number and temperature ratio. The liner cooling and the formation of a starter cooling film can be independently controlled. The rectangular flow channel is equipped with large windows to allow for laser optical diagnostics like PIV and 3-component LDA. The thermal analyses are based on highly resolved temperature mappings of the cooled surface utilizing infrared thermography. First experimental results are presented in terms of static pressure distributions on the combustor liner and PIV contour plots of the swirl flow. The static pressure pattern corresponds well to the up wash and downwash regions of the swirl flow.

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