A Study on Design and Test for Combustor and Fuel Nozzles of a Small Aircraft Gas Turbine

1997 ◽  
Author(s):  
C. D. Kong ◽  
S. K. Kim
Keyword(s):  
Gas Turbine ◽  
Optimal Combination ◽  
Flame Stability ◽  
Design Requirement ◽  
Flammability Limit ◽  
Fuel Nozzle ◽  
Design Requirements ◽  
Firing Tests ◽  
Hot Test ◽  
Small Aircraft

A combustor and a fuel nozzle for a small aircraft gas turbine were designed and appropriateness for design requirements were evaluated and confirmed through the cold and hot test. For the purpose of studying the flame stability of a pilot atomizer under ignition, firing tests were carried out at the various fuel supply pressures. As the results of the experiment and design revision, the optimal combination of the fuel nozzle which is suitable to the design requirement was obtained without the fuel splash phenomena and unstable flame. The combustor was designed and evaluated with detailed investigations and experiments for design requirements. As the results of the hot test, it was confirmed that the combustor in this study had proper profile and pattern factors, flammability limit, total pressure loss and combustor efficiency within design requirements.

scholarly journals Flame Ionization Sensor Integrated Into a Gas Turbine Fuel Nozzle

2005 ◽  
Vol 127 (1) ◽  
pp. 42-48 ◽  
Author(s):  
Kelly Benson ◽  
Jimmy D. Thornton ◽  
Douglas L. Straub ◽  
E. David Huckaby ◽  
Geo. A. Richards
Keyword(s):  
Gas Turbine ◽  
Low Cost ◽  
Stability Margin ◽  
Thermodynamic Efficiency ◽  
Flame Stability ◽  
Fuel Quality ◽  
Widespread Application ◽  
Combustion Dynamics ◽  
Flame Ionization ◽  
Fuel Nozzle

Recent advances in lean premix gas turbine combustion have focused primarily on increasing thermodynamic efficiency, reducing emissions, and minimizing combustion dynamics. The practical limitation on increasing efficiency at lower emissions is the onset of combustion instability, which is known to occur near the lean flammability limit. In a laboratory environment there are many sensors available that provide the combustion engineer with adequate information about flame stability, but those sensors are generally too expensive or unreliable for widespread application in the field. As a consequence, engines must be commissioned in the field with adequate stability margin such that normally expected component wear, fuel quality, and environmental conditions will not cause the turbine to experience unstable combustion. Woodward Industrial Controls, in cooperation with the National Energy Technology Laboratory, is developing a novel combustion sensor that is integrated into the fuel nozzle such that low cost and long life are achieved. The sensor monitors flame ionization, which is indicative of air–fuel ratio and most importantly flame stability.

Design and Performance of Low Heating Value Fuel Gas Turbine Combustors

1996 ◽  
Author(s):  
Robert A. Battista ◽  
Alan S. Feitelberg ◽  
Michael A. Lacey
Keyword(s):  
Gas Turbine ◽  
Coal Gasification ◽  
Combined Cycle ◽  
Flame Stability ◽  
Load Range ◽  
Fuel Gas ◽  
Heating Value ◽  
Gas Turbine Combustors ◽  
Fuel Nozzle ◽  
Combustor Liner

General Electric Company is developing and testing low heating value fuel gas turbine combustors for use in integrated gasification combined cycle power generation systems. This paper presents the results of a series of combustion tests conducted at the pilot scale coal gasification and high temperature desulfurization system located at GE Corporate Research and Development in Schenectady, New York. Tests were performed in a modified GE MS6000 combustor liner operating at a pressure of 10 bar and over a wide load range (combustor exit temperatures from 760 to 1400°C). The primary objective of these tests was to compare and contrast the performance (emissions, flame stability, and combustor liner temperatures) of six different low heating value fuel nozzle designs, representing three distinct nozzle concepts. With 2200 to 4600 ppmv NH3 in the fuel, the conversion of fuel NH3 to NOx was roughly independent of fuel nozzle type, and ranged from about 70% at low combustor exit temperatures to about 20% at high combustor exit temperatures. For all of the fuel nozzles, CO emissions were typically less than 5 ppmv (on a dry, 15% O2 basis) at combustor exit temperatures greater than 980°C. Significant differences in CO emissions were observed at lower combustor exit temperatures. Some differences in liner temperatures and flame stability were also observed with the different nozzles. In general, nozzles which produced lower CO emissions and greater flame stability had higher fuel swirl angles and resulted in higher combustor liner temperatures. The nozzle with the best overall performance (consisting of concentric axial air and fuel swirlers and an air cooled mixing cup) has been selected for use at a commercial site.

scholarly journals Flame Ionization Sensor Integrated Into Gas Turbine Fuel Nozzle

2003 ◽  
Author(s):  
Kelly Benson ◽  
Jimmy D. Thornton ◽  
Douglas L. Straub ◽  
E. David Huckaby ◽  
Geo. A. Richards
Keyword(s):  
Gas Turbine ◽  
Low Cost ◽  
Stability Margin ◽  
Thermodynamic Efficiency ◽  
Flame Stability ◽  
Fuel Quality ◽  
Widespread Application ◽  
Combustion Dynamics ◽  
Flame Ionization ◽  
Fuel Nozzle

Recent advances in lean premix gas turbine combustion have focused primarily on increasing thermodynamic efficiency, reducing emissions, and minimizing combustion dynamics. The practical limitation on increasing efficiency at lower emissions is the onset of combustion instability, which is known to occur near the lean flammability limit. In a laboratory environment there are many sensors available which provide the combustion engineer with adequate information about flame stability, but those sensors are generally too expensive or unreliable for widespread application in the field. As a consequence, engines must be commissioned in the field with adequate stability margin such that normally expected component wear, fuel quality, and environmental conditions will not cause the turbine to experience unstable combustion. Woodward, in cooperation with NETL, is developing a novel combustion sensor which is integrated into the fuel nozzle such that low cost and long life are achieved. The sensor monitors flame ionization, which is indicative of air-fuel ratio, and most importantly flame stability.

A Numerical Study on the Reactivity of Biogas/Reformed-Gas/Air and Methane/Reformed-Gas/Air Mixtures at Gas Turbine Relevant Conditions

2016 ◽  
Author(s):  
Pablo Diaz Gomez Maqueo ◽  
Philippe Versailles ◽  
Gilles Bourque ◽  
Jeffrey M. Bergthorson
Keyword(s):  
Gas Turbine ◽  
Laminar Flame ◽  
Numerical Study ◽  
Flame Temperature ◽  
Flame Speed ◽  
Flame Stability ◽  
Laminar Flame Speed ◽  
Fuel Reforming ◽  
Numerical Work ◽  
Chemical Effects

This study investigates the increase in methane and biogas flame reactivity enabled by the addition of syngas produced through fuel reforming. To isolate thermodynamic and chemical effects on the reactivity of the mixture, the burner simulations are performed with a constant adiabatic flame temperature of 1800 K. Compositions and temperatures are calculated with the chemical equilibrium solver of CANTERA® and the reactivity of the mixture is quantified using the adiabatic, freely-propagating premixed flame, and perfectly-stirred reactors of the CHEMKIN-Pro® software package. The results show that the produced syngas has a content of up to 30 % H2 with a temperature up to 950 K. When added to the fuel, it increases the laminar flame speed while maintaining a burning temperature of 1800 K. Even when cooled to 300 K, the laminar flame speed increases up to 30 % from the baseline of pure biogas. Hence, a system can be developed that controls and improves biogas flame stability under low reactivity conditions by varying the fraction of added syngas to the mixture. This motivates future experimental work on reforming technologies coupled with gas turbine exhausts to validate this numerical work.

Development of a gas turbine fuel nozzle for DME and a design method thereof

Fuel ◽  
2012 ◽  
Vol 102 ◽  
pp. 823-830 ◽  
Author(s):  
Min Chul Lee ◽  
Youngbin Yoon
Keyword(s):  
Gas Turbine ◽  
Design Method ◽  
Fuel Nozzle

The Field Measure of Special Strata Freezing Temperature in West Area

2012 ◽  
Vol 170-173 ◽  
pp. 1207-1210
Author(s):  
Jun Hao Chen ◽  
Rui Zhang
Keyword(s):  
Engineering Design ◽  
Freezing Temperature ◽  
Design Requirement ◽  
Shaft Sinking ◽  
Design Requirements ◽  
Security Information ◽  
Frozen Wall ◽  
The Difference ◽  
Circle Tube ◽  
Field Measure

A new round of upsurge of mine well construction were set off in the west area, but there are many problems, this article through the field measure of special strata freezing temperature in Bo-jiang-hai-zi coal mine airshaft, use the freezing shaft sinking security information network visualization platform that developed by Anhui University of Science and Technology, analysis several different strata, obtain the overall temperatre decline rate, and compare the difference between in-site shaft well temperature and the calculation value at different position, and difference is very small, it shows that the platform can good response the actual situation. Through calculation, the frozen wall thickness, average of frozen wall temperature, shaft well temperature are meet the engineering design requirement, so propose that in west area at the freezing method mine well construction, the main purpose is waterproof, and use single circle tube freezing can satisfy engineering design requirements.

scholarly journals Design and Experimental Investigation on Gas Oxygen/Kerosene Ejector Rocket for RBCC Application

2018 ◽  
Vol 36 (3) ◽  
pp. 558-564
Author(s):  
Xianggeng Wei ◽  
Fei Qin ◽  
Lei Shi ◽  
Baoqing Zhang ◽  
Guoqiang He
Keyword(s):  
Working Conditions ◽  
Rocket Engine ◽  
Combined Cycle ◽  
Engine Test ◽  
The Core ◽  
Technical Requirements ◽  
Core Components ◽  
Design Requirements ◽  
Working Parameters ◽  
Firing Tests

The ejector rocket is one of the core components of the rocket based combined cycle propulsion system, and must be capable of variable working conditions. In order to meet technical requirements for RBCC application, the variable duty operating ejector rocket using the gas Oxygen/Kerosene was designed based on the gas pressurized propellant feed systems. Hot firing tests of four different working conditions had been completed. Experimental results show that the designed ejector rocket engine was stable and reliable, and the working parameters met the design requirements, and the working conditions were adjusted quickly. It lays a foundation for the study of the RBCC engine test and the engine technology of large adjustment ratio.

The Design Requirement for an Unattended Engine Room Steam Propulsion Plant

1972 ◽  
Vol 9 (02) ◽  
pp. 205-215
Author(s):  
william G. Bullock ◽  
Frank D. Yonika
Keyword(s):  
Preliminary Design ◽  
Design Requirement ◽  
Detailed Design ◽  
Ship Construction ◽  
Engine Room ◽  
Base Reference ◽  
Design Requirements ◽  
Reference Document

This paper is a summary of a report prepared by the Office of Ship Construction to provide a base reference document from which a detailed design for an automated steam propulsion plant will be developed for unattended engine room operation. As the design details are developed, it may be anticipated that some of the concepts and preliminary design requirements discussed herein may be modified and/or changed to reflect these developments. It should also be noted that the concepts and opinions expressed herein are those of the authors and do not necessarily reflect those of the Maritime Administration.

OPTIMUM DESIGN OF CANTILEVERED MICROPROBES FOR INSPECTING LCD PANELS AND MEASUREMENT OF CONTACTING FORCES

2010 ◽  
Vol 24 (15n16) ◽  
pp. 2429-2434 ◽  
Author(s):  
CHEOL KIM ◽  
KWANG-JOONG KIM
Keyword(s):  
Shape Optimization ◽  
Optimum Design ◽  
Measuring Equipment ◽  
Optimization Technique ◽  
Experimental Results ◽  
Design Requirement ◽  
Fine Pitch ◽  
Mems Fabrication ◽  
Topology And Shape Optimization ◽  
Design Requirements

Fine pitch microprobe arrays are microneedle-like probes for inspecting the pixels of LCD panels or IC. They are usually made of multi-layers of metallic, nonmetallic, or combination of the two. The design requirement for a contacting force is less than 2 gf and a deflection should be less than 100 µm. Many microprobe shapes satisfying the design requirements are possible. A cantilever-type microprobe having many needles was chosen and optimized in this study. Several candidate shapes were chosen using topology and shape optimization technique subjected to design requirements. Then, the microprobe arrays were fabricated using the process applied for MEMS fabrication and they were made of BeNi , BeCu , or Si . The contact probing forces and deflections were measured for checking the results from optimum design by newly developed measuring equipment in our laboratory. Numerical and experimental results were compared and both showed a good correlation.

Numerical Study of a Single Hydrogen/Air Gas Turbine Fuel Nozzle

2003 ◽  
Author(s):  
Tsan-Hsing Shih ◽  
Timothy Smith ◽  
Cecil Marek ◽  
Anthony Iannetti ◽  
Andrew Norris ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Numerical Study ◽  
Fuel Nozzle
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