Performance of a Dry Low-NOx Gas Turbine Combustor Designed With a New Fuel Supply Concept

2002 ◽  
Vol 124 (4) ◽  
pp. 771-775 ◽  
Author(s):  
T. Wakabayashi ◽  
S. Ito ◽  
S. Koga ◽  
M. Ippommatsu ◽  
K. Moriya ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Equivalence Ratio ◽  
Gas Turbine Combustor ◽  
Lean Premixed Combustion ◽  
Fuel Distribution ◽  
Fuel Supply ◽  
Stable Combustion ◽  
Fuel Jet ◽  
Combustion Region ◽  
Pressurized Combustion

This paper describes the performance of a dry low-NOx gas turbine combustor designed with a new fuel supply concept. This concept uses automatic fuel distribution achieved by an interaction between the fuel jet and the airflow. At high loads, most of the fuel is supplied to the lean premixed combustion region for low-NOx, while at low loads, it is supplied to the pilot combustion region for stable combustion. A numerical simulation was carried out to estimate the equivalence ratio in the fuel supply unit. Next, through the pressurized combustion experiments on the combustor with this fuel supply unit using natural gas as fuel, it was confirmed that NOx emissions were reduced and stable combustion was achieved over a wide equivalence ratio range.

Performance of a Dry Low-NOx Gas Turbine Combustor Designed With a New Fuel Supply Concept

2001 ◽  
Author(s):  
Tsutomu Wakabayashi ◽  
Seiichi Ito ◽  
Shonosuke Koga ◽  
Masamichi Ippommatsu ◽  
Koji Moriya ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Equivalence Ratio ◽  
Gas Turbine Combustor ◽  
Lean Premixed Combustion ◽  
Fuel Distribution ◽  
Fuel Supply ◽  
Stable Combustion ◽  
Fuel Jet ◽  
Combustion Region ◽  
Pressurized Combustion

This paper describes the performance of a dry low-NOx gas turbine combustor designed with a new fuel supply concept. This concept uses automatic fuel distribution achieved by an interaction between the fuel jet and the airflow. At high loads, most of the fuel is supplied to the lean premixed combustion region for low-NOx, while at low loads, it is supplied to the pilot combustion region for stable combustion. A numerical simulation was carried out to estimate the equivalence ratio in the fuel supply unit. Next, through the pressurized combustion experiments on the combustor with this fuel supply unit using natural gas as fuel, it was confirmed that NOx emissions were reduced and stable combustion was achieved over a wide equivalence ratio range.

Performance of a Dry Low NOx Gas Turbine Combustor With an Improved Innovative Fuel Supply Concept

2004 ◽  
Author(s):  
Tsutomu Wakabayashi ◽  
Koji Moriya ◽  
Shonosuke Koga ◽  
Kazuo Shimodaira ◽  
Yoji Kurosawa ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Pressure Loss ◽  
Combustion Efficiency ◽  
Gaseous Fuel ◽  
Gas Turbine Combustor ◽  
Fuel Distribution ◽  
Fuel Supply ◽  
Fuel Jet ◽  
Pressurized Combustion ◽  
Combustion Tests

This paper describes the combustion performance of a dry low-NOx gas turbine combustor designed with an innovative fuel supply concept using gaseous fuel. This concept uses spontaneous fuel distribution achieved by an interaction between the gaseous fuel jet and the airflow. Previously, we proved that fuel distribution based on the innovative fuel supply concept actually occurred according to the load by means of pressurized combustion tests using a prototype combustor. However, NOx was not low enough at high loads, and combustion efficiency was not high at medium and low loads. Further, the pressure loss of the combustor was high. Therefore, the prototype combustor was improved from the viewpoint of NOx, combustion efficiency and combustor pressure loss. This paper describes the detailed structure of the improved combustors and the results of the pressurized combustion experiments.

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.

The Influence of Film Cooling on Emissions for a Low NOx Radial Swirler Gas Turbine Combustor

2001 ◽  
Author(s):  
G. E. Andrews ◽  
M. N. Kim
Keyword(s):  
Mach Number ◽  
Gas Turbine ◽  
Flow Rate ◽  
Film Cooling ◽  
Equivalence Ratio ◽  
Air Flow ◽  
Gas Turbine Combustor ◽  
Cooling Flow ◽  
Full Coverage ◽  
Primary Zone

An experimental investigation was undertaken of the influence on emissions of full coverage discrete hole film cooling of a lean low NOx radial swirler natural gas combustor. The combustor used radial swirler vane passage fuel injection on the centre of the vane passage inlet. The test configuration was similar to that used in the Alstom Power Tornado and related family of low NOx gas turbines. The test conditions were simulated at atmospheric pressure at the flow condition of lean low NOx gas turbine primary zones. The tests were carried out at an isothermal flow Mach number of 0.03, which represents 60% of industrial gas turbine combustor airflow through the swirl primary zone. The effusion film cooling used was Rolls-Royce Transply, which has efficient internal cooling of the wall as well as full coverage discrete hole film cooling. Film cooling levels of 0, 16 and 40% of the primary zone airflow were investigated for a fixed total primary zone air flow and reference Mach number of 0.03. The results showed that there was a major increase in the NOx emissions for 740K inlet temperature and 0.45 overall equivalence ratio from 6ppm at zero film cooling air flow to 32ppm at 40% coolant flow rate. CO emissions increased from 25ppm to 75ppm for the same increase in film cooling flow rate. It was shown that the main effect was the creation of a richer inner swirler combustion with a surrounding film cooling flow that did not mix well with the central swirling combustion. The increase in NOx and CO could be predicted on the basis of the central swirl flow equivalence ratio.

scholarly journals Effect of Inlet Conditions on Lean Premixed Gas Turbine Combustor Performance

1998 ◽  
Author(s):  
Suresh R. Vilayanur ◽  
Nell T. Davis ◽  
Scott Samuelsen
Keyword(s):  
Equivalence Ratio ◽  
Statistical Approach ◽  
Recirculation Zone ◽  
Cfd Modeling ◽  
Gas Turbine Combustor ◽  
Fuel Distribution ◽  
Multiple Parameters ◽  
Significant Parameter ◽  
Concentration Peak ◽  
Inlet Conditions

To address the complex effect of inlet parameters on combustor performance, a statistically based technique is applied to a model, premixed natural gas fired combustor. In this way, multiple parameters are simultaneously investigated for their contribution to combustion performance. Atmospheric tests are performed at conditions otherwise representative of industrial combustors: 670 K. inlet preheat and an equivalence ratio of 0.47. Experimental results, in combination with CFD modeling, reveal that (1) the statistical approach is an effective tool by which parameters that dominate performance can be identified, (2) the principal statistically significant parameter linked to NOx production is the inlet fuel distribution, (3) the principal statistically significant parameter linked to CO production is swirl solidity, and (4) an inlet fuel distribution that features a concentration peak in line with the shear layer of the recirculation zone yields NOx levels comparable to a well premixed case.

scholarly journals Experimental Evaluation of a Low Emissions, Variable Geometry, Small Gas Turbine Combustor

1990 ◽  
Author(s):  
K. O. Smith ◽  
M. H. Samii ◽  
H. K. Mak
Keyword(s):  
Gas Turbine ◽  
Experimental Evaluation ◽  
Premixed Combustion ◽  
Nox Emissions ◽  
Variable Geometry ◽  
Test Results ◽  
Gas Turbine Combustor ◽  
Lean Premixed Combustion ◽  
Primary Zone ◽  
Lean Premixed

The results of an on-engine evaluation of an ultra-low NOx, natural gas-fired combustor for a 200 kW gas turbine are presented. The combustor evaluated used lean-premixed combustion to reduce NOx emissions and variable geometry to extend the range over which low emissions were obtained. Test results showed that ultra-low NOx emissions could be achieved from full load down to approximately 50% load through the combination of lean-premixed combustion and variable primary zone airflow.

CFD Analysis of Fuel Distribution in Concentric Swirling Flows in a Reverse Flow Gas Turbine Combustor

2006 ◽  
Author(s):  
K. Sudhakar Reddy ◽  
D. N. Reddy ◽  
C. M. Vara Prasad
Keyword(s):  
Gas Turbine ◽  
Reverse Flow ◽  
Distribution Patterns ◽  
Swirling Flows ◽  
Cfd Analysis ◽  
Fuel Injector ◽  
Gas Turbine Combustor ◽  
Fuel Distribution ◽  
Wide Range ◽  
Injection Pressures

This paper presents the results of numerical investigations of a turbulent, swirling and recirculating flow without combustion inside a reverse flow gas turbine combustor. In order to establish the characteristics of fuel distribution patterns of the fuel spray injected into swirling flows, flow fields are analyzed inside the swirl combustor for varying amount of swirl strength using a commercial CFD code fluent 6.1.22. Three Dimensional computations are performed to study the influence of the various parameters like injection pressure, flow Reynolds number and Swirl Strength on the fuel distribution patterns. The model predictions are compared against the experimental results, and its applicability over a wide range of flow conditions was investigated. It was observed from the CFD analysis, that the fuel decay along the axis is faster with low injection pressures compared to higher injection pressures. With higher Reynolds numbers the fuel patterns are spreading longer in the axial direction. The higher momentum of the air impedes the radial mixing and increases the constraint on the jet spread. The results reveal that an increase in swirl enhances the mixing rate of the fuel and air and causes recirculation to be more pronounced and to occur away form the fuel injector. The CFD predictions are compared with the experimental data from the phototransistor probe measurements, and good agreement has been achieved.

Infrared Image Processing for Operating Point Control of Gas Turbine Combustor

2004 ◽  
Author(s):  
Mahesh Subramanya ◽  
Srikanth Natarajan ◽  
Ahsan R. Choudhuri
Keyword(s):  
Image Processing ◽  
Gas Turbine ◽  
Equivalence Ratio ◽  
Infrared Image ◽  
Gas Turbine Combustor ◽  
Gray Scale ◽  
Infrared Image Processing ◽  
Intensity Class ◽  
Point Control ◽  
Interrogation Technique

The paper presents a technique to estimate the combustor equivalence ratio based on broadband infrared flame images. A static zonal interrogation technique was developed to separate flame images from the combustor background. Histogram characteristics of gray scale images were used to correlate the image properties with flame equivalence ratios. Two histogram properties i.e. average number of pixels at 100 to 200 intensity-class and number of pixels at 150 intensity-classes were used to develop the correlation.

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