Ongoing Development of a Low Emission Industrial Gas Turbine Combustion Chamber

1980 ◽  
Vol 102 (3) ◽  
pp. 549-554
Author(s):  
V. M. Sood ◽  
J. R. Shekleton
Keyword(s):  
Gas Turbine ◽  
Narrow Range ◽  
Small Scale ◽  
Engine Fuel ◽  
Combustion System ◽  
Emission Standards ◽  
Primary Zone ◽  
Premix Combustion ◽  
Fuel Staging ◽  
Industrial Gas Turbine

Experiments were performed in laboratory-and full-scale combustors to test the feasibility of meeting proposed EPA emission standards. It was found that by uniformly mixing gaseous fuel and primary zone air prior to combustion and burning fuel leanly (equivalence ratio <1.0), it was possible to meet the proposed emission standards in an industrial gas turbine. The characteristic narrow range of flame stability obtained with lean premix combustion necessitated the use of fuel staging or variable geometry to handle the operational range of the engine. Fuel staging was selected for its relative simplicity. Consequently, EPA proposed emission standards were met only over a narrow range covering the engine operation at and near the design point. Experiments on small scale models of various sizes operated with gaseous and liquid fuels showed that, contrary to expectation, NOx production from a lean premix combustion system is independent of the system pressure in the pressure range investigated (1 atm to 16 atm). The desirability of high combustor inlet temperature and pressure for premixing was indicated. Despite the complexities of premixing fuel and air, such a combustion system, in addition to meeting the proposed emission standards, offers advantages such as easing of combustor wall cooling problems, improved combustor exit temperature distribution, and freedom from exhaust and primary zone smoke.

scholarly journals Mars™ SoLoNOx Combustion System CFD Modeling

1995 ◽  
Author(s):  
Matthew E. Thomas ◽  
Mark J. Ostrander ◽  
Andy D. Leonard ◽  
Mel Noble ◽  
Colin Etheridge
Keyword(s):  
Gas Turbine ◽  
System Development ◽  
Cfd Modeling ◽  
Cfd Analysis ◽  
Combustion System ◽  
Design Environment ◽  
Turbine Engine ◽  
Combustion Modeling ◽  
Premix Combustion ◽  
Industrial Gas Turbine

CFD analysis methods were successfully implemented and verified with ongoing industrial gas turbine engine lean premix combustion system development. Selected aspects of diffusion and lean premix combustion modeling, predictions, observations and validated CFD results associated with the Solar Turbines Mars™ SoLoNOx combustor are presented. CO and NOx emission formation modeling details applicable to parametric CFD analysis in an industrial design environment are discussed. This effort culminated in identifying phenomena and methods of potentially further reducing NOx and CO emissions while improving engine operability in the Mars™ SoLoNOx combustion system. A potential explanation for the abrupt rise in CO formation observed in many gas turbine lean premix combustion systems is presented.

Combustor Development and Engine Demonstration of Micro-Mix Hydrogen Combustion Applied to M1A-17 Gas Turbine

2021 ◽  
Author(s):  
Atsushi Horikawa ◽  
Kunio Okada ◽  
Masato Yamaguchi ◽  
Shigeki Aoki ◽  
Manfred Wirsum ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Electrical Power ◽  
Hydrogen Combustion ◽  
Hydrogen Gas ◽  
Air Pollution Control ◽  
Production Of Hydrogen ◽  
Fuel Staging ◽  
Power Generation Plant ◽  
Electrical Power Output ◽  
Industrial Gas Turbine

Abstract Kawasaki Heavy Industries, LTD. (KHI) has research and development projects for a future hydrogen society. These projects comprise the complete hydrogen cycle, including the production of hydrogen gas, the refinement and liquefaction for transportation and storage, and finally the utilization in a gas turbine for electricity and heat supply. Within the development of the hydrogen gas turbine, the key technology is stable and low NOx hydrogen combustion, namely the Dry Low NOx (DLN) hydrogen combustion. KHI, Aachen University of Applied Science, and B&B-AGEMA have investigated the possibility of low NOx micro-mix hydrogen combustion and its application to an industrial gas turbine combustor. From 2014 to 2018, KHI developed a DLN hydrogen combustor for a 2MW class industrial gas turbine with the micro-mix technology. Thereby, the ignition performance, the flame stability for equivalent rotational speed, and higher load conditions were investigated. NOx emission values were kept about half of the Air Pollution Control Law in Japan: 84ppm (O2-15%). Hereby, the elementary combustor development was completed. From May 2020, KHI started the engine demonstration operation by using an M1A-17 gas turbine with a co-generation system located in the hydrogen-fueled power generation plant in Kobe City, Japan. During the first engine demonstration tests, adjustments of engine starting and load control with fuel staging were investigated. On 21st May, the electrical power output reached 1,635 kW, which corresponds to 100% load (ambient temperature 20 °C), and thereby NOx emissions of 65 ppm (O2-15, 60 RH%) were verified. Here, for the first time, a DLN hydrogen-fueled gas turbine successfully generated power and heat.

Development, Fabrication, and Testing of a Prototype Water-Cooled Gas Turbine Nozzle

1983 ◽  
Vol 105 (1) ◽  
pp. 114-119 ◽  
Author(s):  
M. F. Collins ◽  
M. C. Muth ◽  
W. F. Schilling
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Small Scale ◽  
General Electric ◽  
Process Technology ◽  
Aqueous Corrosion ◽  
Post Test ◽  
Efficient Heat Transfer ◽  
Gas Turbine Nozzle ◽  
Industrial Gas Turbine

The design and development of a water-cooled high temperature gas turbine has been under active investigation by the General Electric Gas Turbine Division for the past 15 years. The transition from testing small scale, laboratory-size experimental hardware to full scale industrial gas turbine components was initiated in 1975 by General Electric and extended further under the U.S. Department of Energy’s High Temperature Turbine Technology (HTTT) program. A key element in this transition was the identification of a composite (hybrid) design for the first stage nozzles. This design permits efficient heat transfer to the water-cooling passageways, thus lowering effective strains and increasing part life. This paper describes the metallurgical considerations and process technology required for such hardware. A review of the materials selection criteria utilized for the nozzle is presented, along with the results of several materials development programs aimed at determining metallurgical compatibility of the component materials, diffusion bonding behavior and both hot corrosion and aqueous corrosion performance of key materials. A brief description of the actual cascade testing of the part is given, along with results of a post-test metallurgical analysis of the tested hardware.

Coal-Water Slurry Testing of an Industrial Gas Turbine

1992 ◽  
Author(s):  
R. A. Wenglarz ◽  
C. Wilkes ◽  
R. C. Bourke ◽  
H. C. Mongia
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Water Injection ◽  
Department Of Energy ◽  
Combustion System ◽  
Hot Gas ◽  
Water Slurry ◽  
Coal Water Slurry ◽  
Burning Coal ◽  
Industrial Gas Turbine

This paper describes the first test of an industrial gas turbine and low emissions combustion system on coal-water-slurry fuel. The engine and combustion system have been developed over the past five years as part of the Heat Engines program sponsored by the Morgantown Energy Technology Center of the U.S. Department of Energy (DOE). The engine is a modified Allison 501-K industrial gas turbine designed to produce 3.5 MW of electrical power when burning natural gas or distillate fuel. Full load power output increases to approximately 4.9 MW when burning coal-water slurry as a result of additional turbine mass flow rate. The engine has been modified to accept an external staged combustion system developed specifically for burning coal and low quality ash-bearing fuels. Combustion staging permits the control of NOx from fuel-bound nitrogen while simultaneously controlling CO emissions. Water injection freezes molten ash in the quench zone located between the rich and lean zones. The dry ash is removed from the hot gas stream by two parallel cyclone separators. This paper describes the engine and combustor system modifications required for running on coal and presents the emissions and turbine performance data from the coal-water slurry testing. Included is a discussion of hot gas path ash deposition and planned future work that will support the commercialization of coal-fired gas turbines.

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.

Acoustic Resonances of an Industrial Gas Turbine Combustion System

2000 ◽  
Author(s):  
S. Hubbard ◽  
A. P. Dowling
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Acoustic Waves ◽  
Low Frequency ◽  
Operating Conditions ◽  
Combustion System ◽  
Resonant Frequencies ◽  
Bulk Mode ◽  
Acoustic Resonances ◽  
Industrial Gas Turbine

A theory is developed to describe low frequency acoustic waves in the complicated diffuser/combustor geometry of a typical industrial gas turbine. This is applied to the RB211-DLE geometry to give predictions for the frequencies of the acoustic resonances at a range of operating conditions. The main resonant frequencies are to be found around 605 Hz (associated with the plenum) and around 461 Hz and 823 Hz (associated with the combustion chamber), as well as one at around 22 Hz (a bulk mode associated with the system as a whole).

Design and Testing of an Ultra-Low NOx Gas Turbine Combustor

1986 ◽  
Author(s):  
Kenneth O. Smith ◽  
Leonard C. Angello ◽  
F. Richard Kurzynske
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Catalytic Reduction ◽  
Water Injection ◽  
Nox Emissions ◽  
Combustion System ◽  
Gas Turbine Combustor ◽  
Program Goal ◽  
Primary Zone ◽  
Design And Testing

The design and initial rig testing of an ultra-low NOx gas turbine combustor primary zone are described. A lean premixed, swirl-stabilized combustor was evaluated over a range of pressures up to 10.7 × 105 Pa (10.6 atm) using natural gas. The program goal of reducing NOx emissions to 10 ppm (at 15% O2) with coincident low CO emissions was achieved at all combustor pressure levels. Appropriate combustor loading for ultra-low NOx operation was determined through emissions sampling within the primary zone. The work described represents a first step in developing an advanced gas turbine combustion system that can yield ultra-low NOx levels without the need for water injection and selective catalytic reduction.

Small-scale specimen testing for fatigue life assessment of service-exposed industrial gas turbine blades

2016 ◽  
Vol 92 ◽  
pp. 262-271 ◽  
Author(s):  
D. Holländer ◽  
D. Kulawinski ◽  
A. Weidner ◽  
M. Thiele ◽  
H. Biermann ◽  
...  
Keyword(s):  
Fatigue Life ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Life Assessment ◽  
Small Scale ◽  
Gas Turbine Blades ◽  
Fatigue Life Assessment ◽  
Industrial Gas Turbine

Description of a 9000 HP Single Shaft Gas Turbine

1960 ◽  
Author(s):  
O. C. Schoeppner
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Turbine Rotor ◽  
Decisive Factor ◽  
Combustion System ◽  
Test Program ◽  
Important Place ◽  
Prime Movers ◽  
Industrial Gas Turbine

Low first cost and little need for maintenance assure the industrial gas turbine an important place for many applications where the lower thermal efficiency as compared with other prime movers is not a decisive factor. The simplicity of the gas turbine finds its best expression in the compact integrated single shaft design featuring a single compressor-turbine rotor supported in two bearings, the whole including the combustion system being contained in a common casing structure. The recognized need for simplicity together with reliability has been the main consideration in the design of the unit presented in the following description. At present, an intensive test program is under way and it is expected that the new Clark gas turbine will soon be ready for installation.

Retrofittable Dry Low Emissions Combustor for 501-K Industrial Gas Turbine Engines

1994 ◽  
Author(s):  
Mohan K. Razdan ◽  
Jacob T. McLeroy ◽  
William E. Weaver
Keyword(s):  
High Pressure ◽  
Turbine Engines ◽  
Bench Test ◽  
Gas Turbine Engines ◽  
Test Results ◽  
Mixing Performance ◽  
Premix Combustion ◽  
Fuel Staging ◽  
Air Mixing ◽  
Industrial Gas Turbine

This paper describes progress in the development of a 25 ppm NOx combustor that requires no diluent injection or post-combustion treatment The combustor will be retrofittable in all existing Allison Model 501-K series industrial engines. The approach undertaken is based on lean-premix combustion design incorporating an efficient fuel and air pre-mixing, fuel staging, and advanced wall cooling. Extensive use has been made of Computational Combustor Dynamics (CCD) codes in the design of the low NOx combustor. Experimental work in support of the present effort includes atmospheric bench scale testing and high pressure rig testing. The bench tests have been performed to evaluate several candidate designs, to gain better understanding of general lean pre-mixed combustor behavior, and to verify model predictions. The bench test results have indicated good fuel/air mixing performance of the lean premixing domes. The high pressure simulated engine rig tests of the dry lean pre-mixed low emissions combustors using natural gas have demonstrated NOx levels less than 15 ppm vd (15% O2 corrected), well below the program goals.

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