Development of an Aeroderivative Gas Turbine Dry Low Emissions Combustion System

1994 ◽  
Vol 116 (3) ◽  
pp. 542-546 ◽  
Author(s):  
G. Leonard ◽  
J. Stegmaier
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
System Component ◽  
Test Results ◽  
Combustion System ◽  
Fuel Delivery ◽  
Component Test ◽  
Engine Combustion ◽  
Annular Combustor ◽  
New System

This paper gives the development status of GE’s new aeroderivative premixed combustion system. This system consists of a new fuel staged annular combustor, compressor rear frame, first-stage turbine nozzle, electronic staging controller, and fuel delivery system. Component test results along with a description of the combustion system are presented. This new system will reduce NOx emissions by 90 percent relative to the original aircraft engine combustion system while maintaining low emissions of CO and UHCs. Tests of a LM6000 gas turbine equipped with the new system are planned for early 1994.

Development of an Aeroderivative Gas Turbine Dry Low Emissions Combustion System

1993 ◽  
Author(s):  
Gary Leonard ◽  
James Stegmaier
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
System Component ◽  
Test Results ◽  
Combustion System ◽  
Fuel Delivery ◽  
Component Test ◽  
Engine Combustion ◽  
Annular Combustor ◽  
New System

This paper gives the development status of GE’s new aeroderivative premixed combustion system. This system consists of a new fuel staged annular combustor, compressor rear frame, first stage turbine nozzle, electronic staging controller, and fuel delivery system. Component test results along with a description of the combustion system are presented. This new system will reduce NOx emissions by 90% relative to the original aircraft engine combustion system while maintaining low emissions of CO and UHCs. Tests of a LM6000 gas turbine equipped with the new system are planned for early 1994.

Full Scale Testing of a Low Swirl Fuel Injector Concept for Ultra-Low NOx Gas Turbine Combustion Systems

2006 ◽  
Author(s):  
Waseem Nazeer ◽  
Kenneth Smith ◽  
Patrick Sheppard ◽  
Robert Cheng ◽  
David Littlejohn
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Flame Temperature ◽  
Pressure Oscillation ◽  
Test Results ◽  
Combustion System ◽  
Fuel Injector ◽  
Annular Combustor ◽  
Swirl Injector ◽  
Gas Turbine Combustion

The continued development of a low swirl injector for ultra-low NOx gas turbine applications is described. An injector prototype for natural gas operation has been designed, fabricated and tested. The target application is an annular gas turbine combustion system requiring twelve injectors. High pressure rig test results for a single injector prototype are presented. On natural gas, ultra-low NOx emissions were achieved along with low CO. A turndown of approximately 100°F in flame temperature was possible before CO emissions increased significantly. Subsequently, a set of injectors was evaluated at atmospheric pressure using a production annular combustor. Rig testing again demonstrated the ultra-low NOx capability of the injectors on natural gas. An engine test of the injectors will be required to establish the transient performance of the combustion system and to assess any combustor pressure oscillation issues.

scholarly journals Use of Pyrolysis-Derived Fuel in a Gas Turbine Engine

1983 ◽  
Author(s):  
J. M. Kasper ◽  
G. B. Jasas ◽  
R. L. Trauth
Keyword(s):  
Gas Turbine ◽  
Forest Products ◽  
Test Results ◽  
Fuel Injector ◽  
Gas Turbine Combustor ◽  
Turbine Engine ◽  
Engine Combustion ◽  
Annular Combustor ◽  
Mean Size ◽  
Pyrolytic Oil

Combustion of a pyrolytically derived oil has been demonstrated in a J69-T-29 gas turbine combustor rig. The fuel was derived from agricultural and forest products/wastes through a pyrolysis conversion process which yields the oil and a residual char. The char was ground to a mean size of 25 microns and mixed with the oil and JP-4 in additional combustor rig tests. Analysis of the oil and char showed that both have hydrogen/carbon ratios less than 1.0 for the combustible components. The oil has a water content of 29%, a room temperature viscosity of 250 cS, and a pH of 2.9. The combustion system of the J69 consists of an annular combustor and a centrifugal fuel injector rotating at shaft speed. The centrifugal fuel injector can use slurry fuels without clogging and provides good atomization with viscous fuels. The combustor rig was operated at pressures and temperatures lower than those of the engine, and JP-4 was used as a baseline fuel. Test results indicate that use of pyrolytic oil will result in engine combustion efficiencies of over 99%. The pyrolytic oil may also be used as a supplement to JP-4. Additional development will be necessary to use the pyrolytic char as a gas turbine fuel.

Development of a Low-Emission Combustor for a 100-kW Automotive Ceramic Gas Turbine (III)

1996 ◽  
Author(s):  
Masafumi Sasaki ◽  
Hirotaka Kumakura ◽  
Daishi Suzuki ◽  
Hiroyuki Ichikawa ◽  
Youichiro Ohkubo ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Gas Turbine ◽  
Air Distribution ◽  
Performance Tests ◽  
Test Results ◽  
Combustion System ◽  
Stable Combustion ◽  
Lean Combustion ◽  
Low Emission ◽  
Combustion Region

A low emission combustor, which uses a prevaporization-premixing lean combustion system for the 100 kW automotive ceramic gas turbine (CGT), has been subjected to performance tests. Now a second combustor prototype (PPL-2), which incorporates improvements intended to overcome a flashback problem observed in an initial combustor prototype (PPL-1), is tested. The PPL-2 has been designed and built, so that it will substantially expand the stable combustion range. The improvement is accomplished by increasing the air distribution ratio in the lean combustion region to avoid flashback, providing a uniform flow velocity through the throat area and also by diluting the boundary layer so as to suppress flashback. Test results of the PPL-2 combustor show that it expands the flashback limit without affecting the blow out limit and is able to cover the stable combustion range need for the 100kW CGT.

Managing Gas Turbine Combustion System Fuel Manifold Distress Through Ultrasonic Inspections and Calibrated Fracture Analyses

2017 ◽  
Author(s):  
Scott Keller ◽  
Afzal Pasha Mohammed ◽  
Khalid Oumejjoud
Keyword(s):  
Gas Turbine ◽  
Residual Life ◽  
Ultrasonic Inspection ◽  
Combustion System ◽  
Fuel Delivery ◽  
The Common ◽  
Support Housing ◽  
Industrial Gas Turbine ◽  
Lifecycle Management ◽  
Ray Methods

One of the common issues within the industrial gas turbine fleet is the susceptibility of a can-annular combustors’ fuel manifold cover (support housings) to develop embedded cracks. These cracks, located in the assembly joint of cover plates that create internal passages for fuel delivery to the combustion system, have enough of a driving force to propagate to the surface of the component. Once a crack propagates to the surface, gas has the potential to leak into the enclosure, posing a potential fire and safety risk. Furthermore, cracked fuel manifold covers are prone to increased NOx levels and excessive dynamics. Consequently, operators have the potential for a forced outage due to the failure of the fuel manifold. Currently, the existing solution is to replace the support housings with new or refurbished housings, with prior analyses requiring near perfect fusion. An ultrasonic inspection procedure has been developed to inspect a combustor’s fuel manifold cover for embedded cracks, which are not currently detectable with FPI or X-ray methods. Through this method, the amount of fusion in the assembly joint is readily obtained, including the ability to understand if the crack is partial-thickness or through-thickness. Parametric fracture analyses, utilizing experimental material test data calibrated to service-exposed components, are conducted to predict the residual life. Coupled with the engine operating data, including the use of cold- or heated-fuels, a recommendation for the remaining useful operation of the support housings can be provided. Ultimately, by completing the ultrasonic inspection and analysis on the support housing/fuel manifold, both the risk of an unplanned outage in the future and the lifecycle management cost to the operator is reduced.

Combustion System Performance and Field Test Results of the MS7001F Gas Turbine

1993 ◽  
Vol 115 (3) ◽  
pp. 537-546 ◽  
Author(s):  
J. P. Claeys ◽  
K. M. Elward ◽  
W. J. Mick ◽  
R. A. Symonds
Keyword(s):  
Gas Turbine ◽  
Field Test ◽  
System Performance ◽  
Mechanical Performance ◽  
Steam Injection ◽  
Test Results ◽  
Combustion System ◽  
Dynamic Activity ◽  
Unburned Hydrocarbons ◽  
Nox Control

This paper presents the results of the combustion system test of the MS7001F installed at the Virginia Power Chesterfield station. Tests of water and steam injection for NOx control were performed. Results of emissions, combustor dynamics, and combustor hardware performance are presented. Emissions test results include NOx, CO, unburned hydrocarbons, VOC, and formaldehyde levels. Combustor dynamic activity over a range of diluent injection ratios, and the performance of an actively cooled transition duct are also discussed. Combustion system mechanical performance is described following the first combustion system inspection.

scholarly journals Field Experience of the Sequential Combustion System for the GT24/GT26 Gas Turbine Family

1998 ◽  
Author(s):  
Franz Joos ◽  
Philipp Brunner ◽  
Marcel Stalder ◽  
Stefan Tschirren
Keyword(s):  
Gas Turbine ◽  
Research Work ◽  
Basic Research ◽  
Test Facility ◽  
Test Results ◽  
Combustion System ◽  
System A ◽  
Commercial Operation ◽  
Near Future

The first units of the Sequential Combustion System gas turbine family are in commercial operation. The first gas turbine GT24 (60Hz, 165MW-class) started the commercial operation, while the first GT26 (50Hz, 265MW-class) demonstrates its performance at the GT test facility. More engines are presently in the commissioning phase or will be in the near future. These turbines are designed to offer increased output at high GT efficiency. To acheive this, the sequential combustion system, a reheat process with two combustors, has been developed. Whereas the first combustor is based on the proven EV-combustor technology, extensive research and development efforts have been carried out in developing the lean premixed self-igniting second combustor (SEV). This paper is a follow-up of the ASME paper 96-GT-315, which described the basic research work concerning the lean premixing SEV-burners with self-ignition. The present paper reports the experience gained during commissioning of the first engines. The performance of the two combustors, as well as the measured emissions, are discussed and compared with the expected values and rig test results. Finally, the potential of the sequential combustion system to reach low NOx levels is demonstrated by unveiling the results of the extensive testing program during the commissioning phase.

Initial Operating Experience and Test Results of ABB’s Gas Turbine GT13E2

1995 ◽  
Author(s):  
M. Klohr ◽  
J. Schmidtke ◽  
S. Tschirren ◽  
P. Rihak
Keyword(s):  
Gas Turbine ◽  
Dynamic Pressure ◽  
Operating Experience ◽  
Combined Cycle ◽  
Test Facility ◽  
Vibration Velocity ◽  
Inlet Temperature ◽  
Test Results ◽  
Pressure System ◽  
Annular Combustor

On 20 October 1993, the first ABB GT13E2 gas turbine was put into operation. This 165 MW class gas turbine achieves 35,7% thermal efficiency in single cycle application and up to 54,3% (according ISO standard 3977, Annexe F) in a three pressure system. An optimised turbine and compressor design along with the increased turbine inlet temperature, lead to improved efficiency and electrical output. A new concept for the combustor aimed at meeting the increasing demands on gas turbine emissions. The GT13E2 is equipped with the new single annular combustor and 72 of the ABB EV double cone burners. The commissioning and testing of the first GT13E2 was carried out at the Kawasaki Gas Turbine Research Center (KGRC) in Sodegaura City near Tokyo, Japan. The gas turbine was assembled with various measurement systems to monitor static and dynamic pressure, gas and metal temperature, expansion, vibration, velocity and emissions. The facility will be used during a 15 year joint test program by ABB and Kawasaki Heavy Industries (KHI) to obtain a sound database of operating experience for further improvements of the GT13E2 gas turbine. Therefore, mid 1994 a second test phase was conducted and early 1995 a third test period is scheduled. In parallel, the 2nd and 3rd GT13E2’s were commissioned and tested at the Deeside Combined Cycle Power Plant near Chester, Great Britain. In November 1994, the 4th GT13E2 at Lage Weide was successfully commissioned. This paper describes the operating experience with the GT13E2 during the first commissioning and test phases at KGRC and Deeside. The design features, the test facility, the instrumentation, the commissioning and test results are presented and discussed.

Advanced Burner Development for the Vx4.3A Gas Turbines

2001 ◽  
Author(s):  
Holger Streb ◽  
Bernd Prade ◽  
Thomas Hahner ◽  
Stefan Hoffmann
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Field Evaluation ◽  
Test Facility ◽  
Nox Emissions ◽  
Exhaust Gas ◽  
Test Results ◽  
Exhaust Gas Emission ◽  
Annular Combustor ◽  
Base Load

The Vx4.3A gas turbine family has already been well received by the market. Nevertheless the market drives technology towards both increased turbine inlet temperatures and reduced emissions. The HR3 burner was originally developed for the V4.2 and Vx4.3 fleet featuring silo combustors in order to mitigate the risk of flashback and to improve the NOx- emissions (Prade, Streb, 1996). Due to its favourable performance characteristics in the Vx4.3 family the advanced HR3 burner was adapted to the Vx4.3A series with annular combustor. The paper reports upon the design, testing and field evaluation steps which were necessary to implement the burner for the 50 and 60 cycle gas turbines. With CFD calculations the flow field and the mixing of natural gas and combustion air have been optimised. A number of tests in the Siemens test facilities confirmed these predictions. The atmospheric 3 burner segment combustion test rig allows to test flame interaction, stability and exhaust gas emission simultaneously. In the Siemens Berlin Test Facility which provides a platform for full scale gas turbine testing 24 HR3-burners were implemented into a V84.3A gas turbine with a base load power output of 184 MW at ISO conditions for prototype testing before introducing this new burner generation into the bigger 50 cycle family V94.3A. Implementation of 24 scaled HR3 burners were installed in the V94.3A of Cottam Development Centre (Great Britain) and demonstrated an excellent performance. The gas turbine reached an ISO base load output of 265 MW with NOx emissions well below 25 ppmvd. Due to the very promising test results in Berlin and Cottam, this burner modification, which can be retrofitted to all VX4.3A gas turbines, was implemented nearly fleet wide.

Improved Vibration Monitoring on Aeroderivative Gas Generators With Internal Transducers

2001 ◽  
Author(s):  
Peyton Swan ◽  
Robert G. Betts
Keyword(s):  
Gas Turbine ◽  
Monitoring System ◽  
Vibration Monitoring ◽  
Internal Vibration ◽  
Test Results ◽  
Turbine Engine ◽  
Machinery Condition Monitoring ◽  
Gas Generators ◽  
Condition Monitoring System ◽  
New System

This paper discusses a research project undertaken by Bently Nevada Corporation and TransCanada PipeLines to develop an improved machinery condition monitoring system for the Rolls-Royce Avon gas turbine engine. The project centers on the installation of internal vibration and temperature transducers in and around the engine internal wheel case housing for the center bearing. The paper outlines the current industry-accepted vibration monitoring system, why there is a need to improve the system, the design of the internal transducer mounting arrangements, and test results of the new system.

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