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.

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

1996 ◽  
Vol 118 (1) ◽  
pp. 38-45 ◽  
Author(s):  
T. S. Snyder ◽  
T. J. Rosfjord ◽  
J. B. McVey ◽  
A. S. Hu ◽  
B. C. Schlein
Keyword(s):  
Gas Turbine ◽  
Residence Time ◽  
Fuel Injection ◽  
Pressure Ratio ◽  
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 base-load 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 demonstrated. NOx sensitivities to 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 time was observed and was associated with the increased role of the thermal NOx production mechanism at elevated flame temperatures.

Ignition Characteristics on the Annular Combustor With Rotating Fuel Injection System

2004 ◽  
Author(s):  
Kang Yeop Lee ◽  
Seong Man Choi ◽  
Yeoung-Min Han ◽  
Jeong-Bae Park
Keyword(s):  
Fuel Injection ◽  
Combustion Efficiency ◽  
Injection System ◽  
Test Facility ◽  
Ignition Process ◽  
Fuel Injection System ◽  
Shaft Speed ◽  
Annular Combustor ◽  
Ignition Characteristics ◽  
Ignition And Combustion

An experimental study was performed to investigate the ignition characteristics on the annular combustor with rotating fuel injection system. The combustor was tested in KARI (Korea Aerospace Research Institute) combustor test facility. As the results of the test, equivalence ratio of lean ignition limit is 0.15 at 7,300 rpm and 0.08 at 10,400 rpm respectively. Combustion efficiency is gradually increased from 99.1% to 99.62% with increasing shaft speed from 15,000 rpm to 30,000 rpm. Over than 30,000 rpm, the combustion efficiency is not changed and kept constant. From the ignition and combustion test, ignition process of this annular combustor is mainly governed by the shaft speed. To understand the relationship between the spray characteristics and shaft speed, droplet size was measured by using PDPA system. In this spray test, Sauter mean diameter (SMD) largely depends on the shaft speed. SMD is changed from 73 μm to 42 μm with increasing the shaft speed from 5,000 rpm to 20,000 rpm.

Development of a Dual-Fuel Injection System for Lean Premixed Industrial Gas Turbines

1996 ◽  
Author(s):  
Luke H. Cowell ◽  
Amjad Rajput ◽  
Douglas C. Rawlins
Keyword(s):  
Natural Gas ◽  
Gas Turbines ◽  
Liquid Fuel ◽  
Fuel Injection ◽  
Premixed Combustion ◽  
Injection System ◽  
Fuel Injection System ◽  
Load Range ◽  
Lean Premixed Combustion ◽  
Lean Premixed

A fuel injection system for industrial gas turbine engines capable of using natural gas and liquid fuel in dry, lean premixed combustion is under development to significantly reduce NOx and CO emissions. The program has resulted in a design capable of operating on DF#2 over the 80 to 100% engine load range meeting the current TA LUFT regulations of 96 ppm (dry, @ 15% O2) NOx and 78 ppm CO. When operating on natural gas the design meets the guaranteed levels of 25 ppm NOx and 50 ppm CO. The design approach is to apply lean premixed combustion technology to liquid fuel. Both injector designs introduce the majority of the diesel fuel via airblast alomization into a premixing passage where fuel vaporization and air-fuel premixing occur. Secondary fuel injection occurs through a pilot fuel passage which operates in a partially premixed mode. Development is completed through injector modeling, flow visualization, combustion rig testing, and engine testing. The prototype design tested in development engine environments has operated with NOx emissions below 65 ppm and 20 ppm CO at full load. This paper includes a detailed discussion of the injector design and qualification testing completed on this development hardware.

Effect of transverse fuel injection system on combustion efficiency in scramjet combustor

Energy ◽  
2021 ◽  
Vol 218 ◽  
pp. 119511
Author(s):  
Kumari Ambe Verma ◽  
Krishna Murari Pandey ◽  
Mukul Ray ◽  
Kaushal Kumar Sharma
Keyword(s):  
Fuel Injection ◽  
Combustion Efficiency ◽  
Injection System ◽  
Fuel Injection System ◽  
Scramjet Combustor

Improvement of Gas Turbine Injection Systems by Combined Experimental/Numerical Approach

2002 ◽  
Author(s):  
G. Riccio ◽  
P. Adami ◽  
F. Martelli ◽  
D. Cecchini ◽  
L. Carrai
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Fuel Injection ◽  
Numerical Approach ◽  
Combustion Stability ◽  
Pollutant Emissions ◽  
Injection System ◽  
Flame Stability ◽  
Fuel Injection System ◽  
Joint Application

An aerodynamic study for the premixing device of an industrial turbine gas combustor is discussed. The present work is based on a joint application of numerical CFD and experimental investigation tools in order to verify and optimize the combustor gaseous fuel injection system. The objective is the retrofit of an old generation gas turbine combustion chamber that is carried out considering new targets of NOx emission keeping the same CO and combustion stability performances. CFD has been used to compare different premixing duct configurations for improved mixing features. Experimental test has been carried out in order to assess the pollutant emissions, flame stability and pattern factor characteristics of the full combustion chamber retrofitted with the modified injection system.

scholarly journals Conical Grid Plate Flame Stabilizers for Combustor Primary Zones

1985 ◽  
Author(s):  
A. F. Ali ◽  
G. E. Andrews
Keyword(s):  
Residence Time ◽  
Fuel Injection ◽  
Combustion Efficiency ◽  
Shear Layers ◽  
Injection System ◽  
Fuel Injection System ◽  
Nox Emissions ◽  
Fuel Injector ◽  
Primary Zone ◽  
Grid Plate

Emission results are presented for a jet shear layer flame stabiliser design consisting of a 90° conical flame stabiliser with an array of holes and a central annular vaporiser fuel injection system. This design was tested with premixed propane and air and with direct propane injection into the vaporiser at two blockages and approach velocities. The results showed that an array of jet shear layers could be fuelled by a single fuel injector without incurring excessive NOx emissions. An increase in the primary zone residence time was found to result in an improved combustion efficiency, with no increase in NOx, provided that the stabiliser blockage was increased to maintain the pressure loss.

Application of Thermal Oxidation to a Recuperated Gas Turbine: The Path to PPB NOx Emissions

2013 ◽  
Author(s):  
Jeffrey Armstrong ◽  
Douglas Hamrin ◽  
Steve Lampe
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Fuel Injection ◽  
Landfill Gas ◽  
Premixed Combustion ◽  
Nox Emissions ◽  
Single Digit ◽  
Lean Premixed Combustion ◽  
Lean Premixed ◽  
Order Of Magnitude

Dry, low NOx emissions developments in the industrial gas turbine industry have focused on lean-premixed combustion to reduce NOx to single digit parts-per-million (ppmV) emissions. The reduction of thermal NOx is limited by the lowest lean-premix combustion temperatures. To overcome this limit, a thermal oxidizer is applied which can oxidize hydrocarbon fuels at temperatures below those of lean-premixed combustion in a Brayton cycle. This oxidation technique is explained in a combustion taxonomy model. This paper presents the historical development and demonstration of technology with two different recuperated gas turbines operating on landfill gas. A unique fuel-injection strategy was used to introduce the fuel into the inlet of the gas turbine’s air compressor. The technology demonstrated an order-of-magnitude reduction in the emissions of NOx to the parts-per-billion range.

Verification of Single Digit Emission Performance of a 24 MW Gas Turbine: SGT-600 3rd Generation DLE

2017 ◽  
Author(s):  
Arturo Manrique Carrera ◽  
Philipp Geipel ◽  
Anders Larsson ◽  
Rikard Magnusson
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Liquid Fuel ◽  
Fuel Injection ◽  
Injection System ◽  
Combustion System ◽  
Single Digit ◽  
2Nd Generation ◽  
Droplet Distribution ◽  
Industrial Gas Turbine

The SGT-600 3rd generation DLE is a 24 MW industrial gas turbine which was recently upgraded from the SGT-600 2nd generation DLE. The upgraded SGT-600 is an addition to the existing low emissions gas turbine portfolio within Siemens. The objectives of the engine upgrade focused on increasing the lifetime of the components, lowering emissions and improving liquid fuel operation. In order to accomplish these objectives the combustion system was fully replaced, an improved gas fuel distribution was implemented and the first stage of the turbine was replaced. Furthermore, the liquid fuel injection system was enhanced in terms of fuel droplet distribution. Both gas and liquid fuel operation were confirmed in Siemens industrial gas turbine test facility located in Finspong, Sweden. The upgraded combustion system originates from the SGT-700 gas turbine, a 33MW class engine, which consists of 18 “3rd generation DLE” burners that replaced the original “2nd generation DLE” ones that are normally incorporated in the SGT-600 DLE gas turbines. The first stage of the turbine has also been improved and less air is needed for cooling purposes. Moreover, an additional update on the compressor air bleed control was implemented. The liquid fuel burner hardware was optimized with new fuel injection lances manufactured by electron erosion techniques in order to improve the droplet distribution. The SGT-600 3rd generation DLE is capable to operate in single digit conditions both in NOx and CO from 100% to 70% load and it is possible to extend single digit operation on NOx down to 50% load. CO emissions are below 80ppm at 50% load which is in compliance with current European regulation. Concerning liquid fuel operation the SGT-600 3rd generation DLE does not use water injection for emission control and is capable to reach below 58ppm NOx at full load while keeping CO below 40ppm down to 75% load. The present work describes the main modifications performed during the engine upgrade and the results of the performed engine tests. Finally, it should be noted that the SGT-600 3rd generation DLE is an excellent example of the development/upgrade efforts within Siemens AG. The commercialization process of the SGT-600 3rd generation DLE has been initiated and three engines are already in commercial operation up to date, and two units will be installed in the near future.

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