Combustion Emission Measurements With Preheated Jet Fuel

2011 ◽  
Author(s):  
Qing-ping Zheng ◽  
Sangsig Yun ◽  
Dan Titirica ◽  
Sam Sampath ◽  
Ibrahim Yimer
Keyword(s):  
Temperature Effect ◽  
Experimental Tests ◽  
Jet Fuel ◽  
Operating Conditions ◽  
Cycle Performance ◽  
Fuel Temperature ◽  
Test Rig ◽  
Temperature Regimes ◽  
Aero Engines ◽  
Set Up

Jet fuel thermal stability at high temperature is receiving increased attention recently as advanced aero engines are being pushed to high power, high pressure and temperature regimes for improved engine cycle performance and low emissions. This paper describes the rig experimental tests to assess the high fuel temperature effect on combustor emissions. A special test rig facility has been designed and set up for emission measurements with preheated fuel. The purpose of the tests is to evaluate the combustor emission characteristics under nominal and elevated fuel temperatures. The scope of the project is two fold: (1) to design, procure and establish a dedicated hot fuel deoxygenation, fuel preheat facility that can reach temperature up to 600 °F (589 K); (2) to measure combustion emissions, mainly NOx, CO and UHC, at normal and elevated fuel temperature under representative engine operating conditions. The test rig has run for extended duration and proved reliable over the whole test campaign. Measured emission results show that fuel temperature effect on NOx, CO, UHC emissions are marginal, possibly due to the low emission capability of the sector combustor that is less sensitive to fuel inlet condition changes than other combustor designs. These results indicate a manageable risk for engine development with elevated fuel temperature from the emission viewpoint.

A Low-Speed Compressor Test Rig for Flutter Investigations

2019 ◽  
Vol 141 (5) ◽  
Author(s):  
Leonie Malzacher ◽  
Silvio Geist ◽  
Valentina Motta ◽  
Dieter Peitsch ◽  
Holger Hennings
Keyword(s):  
Experimental Tests ◽  
Test Facility ◽  
Test Rig ◽  
Compressor Blades ◽  
Low Speed ◽  
Surface Pressure Distribution ◽  
Wide Range ◽  
Oil Flow ◽  
Aero Engines ◽  
Set Up

A test facility for aeroeolastic investigations has been set up at the chair of Aero Engines at the Technische Universität Berlin. The test rig provides data for tool and code validation, and is used for basic aeroelastic experiments. It is a low-speed wind tunnel, which allows free and controlled flutter testing. The test section contains a linear cascade with eleven compressor blades. Nine of them are elastically suspended. The paper presents a detailed description of the test facility results to evaluate the overall flow quality alongside an aeroelastic model to predict the flutter velocity and critical interblade phase angles (IBPAs). Furthermore, chordwise pressure distributions, measured with traveling wave (TW) mode experimental tests, are presented. These measurements have been carried out for a wide range of IBPAs and have been compared to numerical results. Hot-wire anemometry has been applied to examine the inlet flow for several Mach numbers and Reynolds numbers. The results show small turbulence intensities. The blade surface pressure distribution and the flow field of the blade's suction and pressure sides have been obtained by oil flow visualization.

scholarly journals Studies of Jet Thermal Stability in a Flowing System

1992 ◽  
Author(s):  
S. P. Heneghan ◽  
C. R. Martel ◽  
T. F. Williams ◽  
D. R. Ballal
Keyword(s):  
Thermal Stability ◽  
Oxygen Consumption ◽  
Jet Fuel ◽  
Total Carbon ◽  
Threshold Temperature ◽  
Jet Fuels ◽  
Test Duration ◽  
Fuel Temperature ◽  
Test Rig ◽  
Carbon Deposits

A flowing, single-pass heat exchanger test rig, with a fuel capacity of 189 litres, has been developed to evaluate jet fuel thermal stability. This so called, “Phoenix Rig” is capable of supplying jet fuel to a 2.15 mm I.D. tube at a pressure up to 3.45 MPa, fuel temperature up to 900K, and a fuel-tube Reynolds number in the range 300–11,000. Using this test rig, fuel thermal stability (carbon deposition rate), dissolved oxygen consumption, and methane production were measured for three baseline jet fuels and three fuels blended with additives. Such measurement were performed under oxygen-saturation or oxygen-starved conditions. Tests with all of the blended fuel samples showed a noticeable improvement in fuel thermal stability. Both block temperature and test duration increased the total carbon deposits in a nonlinear fashion. Interestingly, those fuels that need a higher threshold temperature to force the consumption of oxygen exhibited greater carbon deposits than those that consume oxygen at a lower temperature. These observations suggested a complicated relationship between the formation of carbon deposits and the temperature-driven consumption of oxygen. A simple analysis, based on a bi-molecular reaction rate, correctly accounted for the shape of the oxygen consumption curve for various fuels. This analysis yielded estimates of global bulk parameters of oxygen consumption. The test rig yielded quantitative results which will be very useful in evaluating fuel additives, understanding the chemistry of deposit formation, and eventually developing a global chemistry model.

scholarly journals Experimental investigations and analysis on churning losses of splash lubricated spiral bevel gears

2017 ◽  
Vol 18 (4) ◽  
pp. 412 ◽  
Author(s):  
S. Laruelle ◽  
C. Fossier ◽  
C. Changenet ◽  
F. Ville ◽  
S. Koechlin
Keyword(s):  
Experimental Tests ◽  
Operating Conditions ◽  
Experimental Investigations ◽  
Spiral Bevel Gear ◽  
Power Losses ◽  
Test Rig ◽  
Specific Test ◽  
Spiral Bevel Gears ◽  
Bevel Gears ◽  
Spiral Bevel

Churning losses are a complex phenomenon which generates significant power losses when considering splash lubrication of gear units. However, only few works deal with bevel gears dipped lubrication losses. The objective of this study is to provide a wide variety of experimental tests on churning losses, especially getting interested in geometry of spiral bevel gears influence. A specific test rig was used in order to study a single spiral bevel gear partially immersed in an oil bath. Experiments have been conducted for several operating conditions in terms of speeds, lubricants, temperatures and gear geometries to study their impact on splash lubrication power losses. These experimental results are compared with the predictions from various literature sources. As the results did not agree well with the predictions for all operating conditions, an extended equation derived from previous works is introduced to estimate churning losses of bevel gears.

Studies of Jet Fuel Thermal Stability in a Flowing System

1993 ◽  
Vol 115 (3) ◽  
pp. 480-485 ◽  
Author(s):  
S. P. Heneghan ◽  
C. R. Martel ◽  
T. F. Williams ◽  
D. R. Ballal
Keyword(s):  
Thermal Stability ◽  
Oxygen Consumption ◽  
Bimolecular Reaction ◽  
Jet Fuel ◽  
Total Carbon ◽  
Threshold Temperature ◽  
Test Duration ◽  
Fuel Temperature ◽  
Test Rig ◽  
Carbon Deposits

A flowing, single-pass heat exchanger test rig, with a fuel capacity of 189 liters, has been developed to evaluate jet fuel thermal stability. This “Phoenix Rig” is capable of supplying jet fuel to a 2.15 mm i.d. tube at a pressure up to 3.45 MPa, fuel temperature up to 900 K, and a fuel-tube Reynolds number in the range 300–11,000. Using this test rig, fuel thermal stability (carbon deposition rate), dissolved oxygen consumption, and methane production were measured for three baseline jet fuels and three fuels blended with additives. Such measurement were performed under oxygen-saturation or oxygen-starved conditions. Tests with all of the blended fuel samples showed a noticeable improvement in fuel thermal stability. Both block temperature and test duration increased the total carbon deposits in a nonlinear fashion. Interestingly, those fuels that need a higher threshold temperature to force the consumption of oxygen exhibited greater carbon deposits than those that consume oxygen at a lower temperature. These observations suggested a complicated relationship between the formation of carbon deposits and the temperature-driven consumption of oxygen. A simple analysis, based on a bimolecular reaction rate, correctly accounted for the shape of the oxygen consumption curve for various fuels. This analysis yielded estimates of global bulk parameters of oxygen consumption. The test rig yielded quantitative results, which will be very useful in evaluating fuels additives, understanding the chemistry of deposit formation, and eventually developing a global chemistry model.

scholarly journals Investigations on Oil Flow Rates Projected on the Casing Walls by Splashed Lubricated Gears

2012 ◽  
Vol 2012 ◽  
pp. 1-7 ◽  
Author(s):  
G. Leprince ◽  
C. Changenet ◽  
F. Ville ◽  
P. Velex
Keyword(s):  
Spur Gear ◽  
Operating Conditions ◽  
Test Rig ◽  
Variable Size ◽  
Flow Measurements ◽  
Flow Rates ◽  
Lubricant Flow ◽  
Wide Range ◽  
Oil Flow ◽  
Set Up

In order to investigate the oil projected by gears rotating in an oil bath, a test rig has been set up in which the quantity of lubricant splashed at several locations on the casing walls can be measured. An oblong-shaped window of variable size is connected to a tank for flow measurements, and the system can be placed at several locations. A series of formulae have been deduced using dimensional analysis which can predict the lubricant flow rate generated by one spur gear or one disk at various places on the casing. These results have been experimentally validated over a wide range of operating conditions (rotational speed, geometry, immersion depth, etc.).

Rolling Bearings Monitoring and Damage Detection Methodology

2006 ◽  
Vol 3-4 ◽  
pp. 293-302 ◽  
Author(s):  
Cristiana Delprete ◽  
Mario Milanesio ◽  
Carlo Rosso
Keyword(s):  
Early Detection ◽  
Damage Detection ◽  
Experimental Tests ◽  
Operating Conditions ◽  
Test Rig ◽  
Rolling Bearings

Aim of the research was the development of an effective and functional methodology able to monitoring and precociously diagnosing rolling bearings damage during operating conditions. Several experimental tests have been carried on a dedicated test rig. The monitoring methodology has been revealed effective in an early detection of rolling bearings damage, also with the contemporary presence of vibrations from unbalances, plays and misalignments.

Measurement of Thermal Contact Conductance of a Heat Shield for Gas Turbine Combustors in a Realistic Test Rig Set-Up

2012 ◽  
Author(s):  
B. Facchini ◽  
F. Simonetti ◽  
L. Tarchi ◽  
R. Abram ◽  
M. Maritano
Keyword(s):  
Gas Turbine ◽  
Thermal Contact ◽  
Operating Conditions ◽  
Heat Shield ◽  
Ceramic Fiber ◽  
Thermal Contact Conductance ◽  
Test Rig ◽  
Contact Conductance ◽  
Experimental Campaign ◽  
Set Up

This paper presents the results of the experimental campaign on the measurement of thermal contact conductance (TCC) in a realistic test rig replicating the contact between the ceramic heat shield and the liner for an ANSALDO Energia s.p.a. heavy-duty gas turbine. The designed test rig is made up of a single sector consisting of a combustor ceramic brick and a liner sector with a non-rigid ceramic fiber textile insulating layer in between, to better replicate the operating conditions of the combustor components. The experimental campaign was carried out with a steady-state technique applying an uniform thermal load on the heat shield surface. The effect of brick-holders, that in the actual combustor anchor the bricks on the liner walls, was replicated with static loads. The liner sector was tested without the brick-holder grooves first and afterwards their effect was assessed in the same test conditions; the test campaign also aimed at measuring the load cycling effect on TCC. Validation of the measured TCC was then performed with a finite element code to compare the predicted temperature profiles with the measured ones.

scholarly journals Hardware in the Loop Test-Rig for Identification and Control Application on High Speed Pantographs

2004 ◽  
Vol 11 (3-4) ◽  
pp. 445-456 ◽  
Author(s):  
A. Collina ◽  
A. Facchinetti ◽  
F. Fossati ◽  
F. Resta
Keyword(s):  
High Speed ◽  
Real Life ◽  
Operating Conditions ◽  
Hardware In The Loop ◽  
Test Rig ◽  
Dynamical Interaction ◽  
Contact Wire ◽  
The Real ◽  
Current Collection ◽  
Set Up

Trains current collection for traction motors is obtained by means of a sliding contact between the overhead line (OHL) and the collector strips mounted on the pantograph head. The normal force by which the collector presses against the contact wire ensures the contact pressure for the electrical contact. As the train speed increases, the variation of contact force between pantograph and catenary increases, and the pantograph-OHL dynamic interaction becomes greater. This condition causes excessive mechanical wear and contact wire uplift (for high values of contact forces), and leads to high percentage of contact loss, arcing and electrically related wear.The topic of actively controlled pantograph is gaining more interest as a tool to increase the performance of the current collection at high speed. In the last few years, it appears possible to transfer the knowledge based on numerical experiments, to the real operating condition. An important step in this direction is the set up of a laboratory hardware in the loop test-rig in which the control strategies and the actuation can be tested, before tests performing in real life conditions, in order to demonstrate their actual feasibility. The present paper describes an hardware in the loop (HIL) test-rig developed by the authors, which allows to reproduce the dynamical interaction between overhead lines and pantograph in high speed railways. Using the described laboratory set-up, experimental investigation on the problems related with pantograph-OHL interaction can be performed, very similarly to the real life operating conditions, with the advantage of varying test parameters and conditions easily.

CFD Study of a Micro-Combustor Under Variable Operating Conditions

2017 ◽  
Author(s):  
Maria Cristina Cameretti ◽  
Roberta De Robbio ◽  
Raffaele Tuccillo
Keyword(s):  
Gas Turbine ◽  
Fossil Fuels ◽  
Experimental Tests ◽  
Operating Conditions ◽  
Combustion Stability ◽  
Combustion Model ◽  
Low Carbon ◽  
Kinetic Mechanisms ◽  
Micro Turbine ◽  
Set Up

New concepts for power generation are discussed as a response to CO2 emissions from the combustion of fossil fuels. These concepts include low-carbon fuels as well as new fuel supplies will be used, with (biogenic) low-caloric gases such as syngas with an amount of hydrogen, with a share of 50% and even higher. However, hydrogen mixtures have a higher reactivity than natural gas (NG) mixtures, burned mostly in today’s gas turbine combustors. The authors discuss in this paper the potential of a micro gas turbine (MGT) combustor when operated under unconventional conditions, both in terms of variation in the fuel supplied and concerning the part-load or off-design operation. In particular, the authors’ methodology relies on an advanced CFD approach that makes use of extended kinetic mechanisms coupled with the turbulent interaction of the reacting species. A preliminary set-up of the combustion model is based on data provided by experimental tests of the micro-turbine. In the paper, several computational examples are discussed, namely: - The comparison of combustion stability and efficiency and pollutant production with several fuels. - The analysis of the combustor response with reduced load. - The use of the pilot and main injectors for supplying different fuels.

scholarly journals Comprehensive Parameters Identification and Dynamic Model Validation of Interior-Mount Line-Start Permanent Magnet Synchronous Motors

Machines ◽  
2019 ◽  
Vol 7 (1) ◽  
pp. 4 ◽  
Author(s):  
Luqman S. Maraaba ◽  
Zakariya M. Al-Hamouz ◽  
Abdulaziz S. Milhem ◽  
Ssennoga Twaha
Keyword(s):  
Mathematical Model ◽  
Permanent Magnet ◽  
High Efficiency ◽  
Experimental Tests ◽  
Induction Machines ◽  
Test Methods ◽  
Operating Conditions ◽  
Test Method ◽  
Permanent Magnet Synchronous Motors ◽  
Synchronous Motors

The application of line-start permanent magnet synchronous motors (LSPMSMs) is rapidly spreading due to their advantages of high efficiency, high operational power factor, being self-starting, rendering them as highly needed in many applications in recent years. Although there have been standard methods for the identification of parameters of synchronous and induction machines, most of them do not apply to LSPMSMs. This paper presents a study and analysis of different parameter identification methods for interior mount LSPMSM. Experimental tests have been performed in the laboratory on a 1-hp interior mount LSPMSM. The measurements have been validated by investigating the performance of the machine under different operating conditions using a developed qd0 mathematical model and an experimental setup. The dynamic and steady-state performance analyses have been performed using the determined parameters. It is found that the experimental results are close to the mathematical model results, confirming the accuracy of the studied test methods. Therefore, the output of this study will help in selecting the proper test method for LSPMSM.

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