Combustion Efficiency Measurement in a Direct-Connected Scramjet Test Facility by Using Multiplexed Diode Lasers

2009 ◽  
Author(s):  
Fei Li ◽  
Xilong Yu ◽  
Lihong Chen ◽  
Xinyu Chang
Keyword(s):  
Diode Lasers ◽  
Combustion Efficiency ◽  
Efficiency Measurement ◽  
Test Facility

Experimental Study of Combustion on a Micro Gas Turbine Combustor

2008 ◽  
Author(s):  
Feng-Shan Wang ◽  
Wen-Jun Kong ◽  
Bao-Rui Wang
Keyword(s):  
Gas Turbine ◽  
Pressure Loss ◽  
Loss Factor ◽  
Total Pressure ◽  
Combustion Efficiency ◽  
Total Pressure Loss ◽  
Test Facility ◽  
Inlet Temperature ◽  
Micro Gas Turbine ◽  
Oil Fuel

A research program is in development in China as a demonstrator of combined cooling, heating and power system (CCHP). In this program, a micro gas turbine with net electrical output around 100kW is designed and developed. The combustor is designed for natural gas operation and oil fuel operation, respectively. In this paper, a prototype can combustor for the oil fuel was studied by the experiments. In this paper, the combustor was tested using the ambient pressure combustor test facility. The sensors were equipped to measure the combustion performance; the exhaust gas was sampled and analyzed by a gas analyzer device. From the tests and experiments, combustion efficiency, pattern factor at the exit, the surface temperature profile of the outer liner wall, the total pressure loss factor of the combustion chamber with and without burning, and the pollutants emission fraction at the combustor exit were obtained. It is also found that with increasing of the inlet temperature, the combustion efficiency and the total pressure loss factor increased, while the exit pattern factor coefficient reduced. The emissions of CO and unburned hydrogen carbon (UHC) significantly reduced, but the emission of NOx significantly increased.

Preliminary Study on Combustion of Biodiesel for Power Generation

2006 ◽  
Author(s):  
Ee Sann Tan ◽  
Kumaran Palanisamy ◽  
Ibrahim Hussein ◽  
Farid Nasir Ani
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Fossil Fuel ◽  
Alternative Fuel ◽  
Waste Cooking Oil ◽  
Combustion Efficiency ◽  
Test Facility ◽  
Animal Fats ◽  
Cooking Oil ◽  
Crude Oil Prices

In the recent wake of escalating crude oil prices due to depletion of fossil fuel, biodiesel has generated a significant interest as an alternative fuel for the future. The use of biodiesel to fuel microturbines or gas turbine application is envisaged to solve problems of diminishing supplies of fossil fuel reserves and environmental concerns. This paper examines the combustion of biodiesel derived from Malaysian Waste Cooking Oil (WCO) in a combustion test facility to study the feasibility of using the designated fuel at five various volumetric ratios for gas turbine application. Biodiesel was produced from waste cooking oil in Malaysia, mainly from palm oil sources and animal fats. The oil burner was able to fire the five blends of fuel without any modification or pretreatment. The combustion performance of Malaysian WCO biodiesel and distillate blends was examined with respect to the combustion efficiency. The results indicated biodiesel combustion required less air for stoichiometric combustion due to presence of oxygen in the fuel. Indeed biodiesel stand as a potential alternative fuel for power generation application with the best efficiency at blended ratio of 20% biodiesel and 80% distillate.

Combustion Test Results of an Uncooled Combustor With Ceramic Matrix Composite Liner

2001 ◽  
Author(s):  
Yasufumi Suzuki ◽  
Toyoichi Satoh ◽  
Manabu Kawano ◽  
Naofumi Akikawa ◽  
Yoshihiro Matsuda
Keyword(s):  
Matrix Composite ◽  
Reverse Flow ◽  
Ceramic Matrix Composite ◽  
Three Dimensional ◽  
Ceramic Matrix ◽  
High Heat ◽  
Combustion Efficiency ◽  
Test Facility ◽  
Annular Combustor ◽  
Release Ratio

A reverse-flow annular combustor with its casing diameter of 400 mm was developed using an uncooled liner made of three-dimensional-woven ceramic-matrix composite. The combustor was tested using the TRDI high-pressure combustor test facility at the combustor maximum inlet and exit temperature of 723K and 1623K respectively. Although both the material and combustion characteristics were evaluated in the test, this report focused on the combustion performance. As the results of the test, the high combustion efficiency and high heat release ratio of 99.9% and 1032 W/m3/Pa were obtained at the design point. The latter figure is approximately twice as high as that of existing reverse–flow annular combustors. Pattern factor was sufficiently low and was less than 0.1. Surface temperatures of the liner wall were confirmed to be higher than the limit of the combustor made of existing heat-resistant metallic materials.

Emission and Performance of a Lean-Premixed Gas Fuel Injection System for Aeroderivative Gas Turbine Engines

1994 ◽  
Author(s):  
Timothy S. Snyder ◽  
Thomas J. Rosfjord ◽  
John B. McVey ◽  
Aaron S. Hu ◽  
Barry C. Schlein
Keyword(s):  
Gas Turbine ◽  
Fuel Injection ◽  
Pressure Ratio ◽  
Combustion Efficiency ◽  
Injection System ◽  
Test Facility ◽  
Fuel Injection System ◽  
Moderate Pressure ◽  
Single Digit ◽  
Lean Premixed

A dry-low-NOx, high-airflow-capacity fuel injection system for a lean-premixed combustor has been developed for a moderate pressure ratio (20:1) aeroderivative gas turbine engine. Engine requirements for combustor pressure drop, emissions, and operability have been met. Combustion performance was evaluated at high power conditions in a high-pressure, single-nozzle test facility which operates at full baseload conditions. Single digit NOx levels and high combustion efficiency were achieved A wide operability range with no signs of flashback, autoignition, or thermal problems was demonsuated. NOx sensitivities 10 pressure and residence time were found to be small at flame temperatures below 1850 K (2870 F). Above 1850 K some NOx sensitivity to pressure and residence Lime was observed and was associated with the increased role of the thermal NOx production mechanism at elevated flame temperatures.

How to handle the Hydrogen enriched Natural Gas blends in combustion efficiency measurement procedure of conventional and condensing boilers

Energy ◽  
2017 ◽  
Vol 123 ◽  
pp. 615-636 ◽  
Author(s):  
Gianluigi Lo Basso ◽  
Benedetto Nastasi ◽  
Davide Astiaso Garcia ◽  
Fabrizio Cumo
Keyword(s):  
Natural Gas ◽  
Measurement Procedure ◽  
Combustion Efficiency ◽  
Efficiency Measurement

The Development of a Neural Network Based System for the Optimal Control of Chain-Grate Stoker-Fired Boilers

2000 ◽  
Author(s):  
A. Z. S. Chong ◽  
S. J. Wilcox ◽  
J. Ward
Keyword(s):  
Neural Network ◽  
Steady State ◽  
Pilot Scale ◽  
Combustion Efficiency ◽  
Fine Tuning ◽  
Pollutant Emissions ◽  
Test Facility ◽  
Test Results ◽  
Load Following ◽  
Online Implementation

Abstract A novel Neural Network Based Controller (NNBC) was developed following a comprehensive set of experiments carried out on a pilot-scale stoker test facility at CRE Group Ltd., U.K. The NNBC mimicked the actions of an expert boiler operator, by providing ‘near optimum’ settings of coal feed and air flow, as well as ‘staging’ these parameters during load following conditions, before fine tuning the combustion air under quasi-steady-state conditions. Test results from the online implementation of the NNBC have demonstrated that improved transient and steady-state combustion conditions were attained. The prototype NNBC thus provides both stoker manufacturers and users with a means of reducing pollutant emissions, as well as improving the combustion efficiency of this type of coal firing equipment.

Combustion Test Results of an Uncooled Combustor With Ceramic Matrix Composite Liner

2002 ◽  
Vol 125 (1) ◽  
pp. 28-33 ◽  
Author(s):  
Y. Suzuki ◽  
T. Satoh ◽  
M. Kawano ◽  
N. Akikawa ◽  
Y. Matsuda
Keyword(s):  
Matrix Composite ◽  
Reverse Flow ◽  
Ceramic Matrix Composite ◽  
Three Dimensional ◽  
Ceramic Matrix ◽  
High Heat ◽  
Combustion Efficiency ◽  
Test Facility ◽  
Annular Combustor ◽  
Release Ratio

A reverse-flow annular combustor with its casing diameter of 400 mm was developed using an uncooled liner made of a three-dimensional woven ceramic matrix composite. The combustor was tested using the TRDI high-pressure combustor test facility at the combustor maximum inlet and exit temperature of 723 K and 1623 K, respectively. Although both the material and combustion characteristics were evaluated in the test, this report focused on the combustion performance. As the results of the test, the high combustion efficiency and high heat release ratio of 99.9% and 1032 W/m3/Pa were obtained at the design point. The latter figure is approximately twice as high as that of existing reverse-flow annular combustors. Pattern factor was sufficiently low and was less than 0.1. Surface temperatures of the liner wall were confirmed to be higher than the limit of the combustor made of existing heat-resistant metallic materials.

A Study on Performance Comparison of Integrated Aerodynamic-Ramp-Injector/ Gas-Portfire Flame Holder with Cavity

2013 ◽  
Vol 390 ◽  
pp. 8-11
Author(s):  
Bao Xi Wei ◽  
Qiang Gang ◽  
Yan Zhang ◽  
Rong Jian Liu ◽  
Liang Tian ◽  
...  
Keyword(s):  
Experimental Study ◽  
Mach Number ◽  
Supersonic Flow ◽  
Specific Impulse ◽  
Combustion Efficiency ◽  
Performance Comparison ◽  
Test Facility ◽  
Flame Holder ◽  
Scramjet Combustor ◽  
Total Temperature

Experimental study of an integrated aerodynamic-ramp-injector /gas-portfire (aero-ramp/G-P) has been conducted in a hydrogen-fueled scramjet combustor. The aero-ramp injectors consisted of four flush-walled holes, arranged to induce vorticular motion and enhance mixing. For comparison, a recessed cavity with four low downstream-angled circular injector holes was also examined. The combustor models were investigated experimentally using the scramjet direct connected test facility at the Beihang University. The facility can deliver a continuous supersonic flow of Mach number 2 with a total temperature of 1200K. The hot experimental results showed that the combustion efficiency and air specific impulse of aero-ramp/G-P are 85% and 35s while the corresponding values of cavity are 92% and 34s. These results justify the feasibility of aero-ramp/G-P flame holder.

Turbine Efficiency Measurement System for the QinetiQ Turbine Test Facility

2009 ◽  
Vol 132 (1) ◽  
Author(s):  
Paul F. Beard ◽  
Thomas Povey ◽  
Kamaljit S. Chana
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Measurement System ◽  
Efficiency Measurement ◽  
Test Facility ◽  
Torque Measurement ◽  
Measurement Systems ◽  
Turbine Efficiency ◽  
Turbine Inlet

A turbine efficiency measurement system has been developed and installed on the turbine test facility (TTF) at QinetiQ Farnborough. The TTF is an engine-scale short-duration (0.5s run time) rotating transonic facility, which can operate as either single stage (HP vane and rotor) or 112 stage (HP stage with IP or LP vane). The current MT1 HP stage is highly loaded and unshrouded and is therefore relevant to current design trends. Implementation of the efficiency measurement system forms part of the EU Turbine Aero-Thermal External Flows (TATEF II) program. The following aspects of the efficiency measurement system are discussed in this paper: mass-flow rate measurement, power measurement by direct torque measurement, turbine inlet and exit area traverse measurement systems, computation of efficiency by mass weighting, and uncertainty analysis of the experimentally determined turbine efficiency. The calibration of the mass-flow rate and torque measurement systems are also discussed. Emphasis was placed on the need for a low efficiency precision uncertainty, so that changes in efficiency associated with turbine inlet temperature distortion and swirl can be resolved with good accuracy. Measurements with inlet flow distortion form part of the TATEF II program and will be the subject of forthcoming publications.

Hydrogen-Enhanced Gasoline Stratified Combustion in SI-DI Engines

2008 ◽  
Vol 130 (2) ◽  
Author(s):  
Enrico Conte ◽  
Konstantinos Boulouchos
Keyword(s):  
Direct Injection ◽  
Combustion Efficiency ◽  
Gasoline Direct Injection ◽  
Test Facility ◽  
Experimental Investigations ◽  
Pure Hydrogen ◽  
Hc Emissions ◽  
Homogeneous Background ◽  
Stratified Combustion ◽  
Reformer Gas

Experimental investigations were carried out to assess the use of hydrogen in a gasoline direct injection (GDI) engine. Injection of small amounts of hydrogen (up to 27% on energy basis) in the intake port creates a reactive homogeneous background for the direct injection of gasoline in the cylinder. In this way, it is possible to operate the engine with high exhaust gas recirculation (EGR) rates and, in certain conditions, to delay the ignition timing as compared to standard GDI operation, in order to reduce NOx and HC emissions to very low levels and possibly soot emissions. The results confirmed that high EGR rates can be achieved and NOx and HC emissions reduced, showed significant advantage in terms of combustion efficiency and gave unexpected results relative to the delaying of ignition, which only partly confirmed the expected behavior. A realistic application would make use of hydrogen-containing reformer gas produced on board the vehicle, but safety restrictions did not allow using carbon monoxide in the test facility. Thus, pure hydrogen was used for a best-case investigation. The expected difference in the use of the two gases is briefly discussed.

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