scholarly journals Characteristic Time Correlations of Pollutant Emissions From an Annular Gas Turbine Combustor

1979 ◽  
Author(s):  
A. M. Mellor ◽  
R. M. Washam
Keyword(s):  
Gas Turbine ◽  
Characteristic Time ◽  
Pollutant Emissions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Time Model ◽  
Gaseous Pollutant ◽  
Modeling Approach ◽  
Time Correlations

The continuing development of a characteristic time model for gaseous pollutant emissions from conventional gas turbine engines is described. The now engine studied here is the Pratt and Whitney JT9D, and it is shown that universal correlations can be obtained by comparison with previous results. Current limitations of the modeling approach are detailed.

scholarly journals Development of 300 kW Class Ceramic Gas Turbine (CGT302)

1995 ◽  
Author(s):  
Kozi Nishio ◽  
Junzo Fujioka ◽  
Tetsuo Tatsumi ◽  
Isashi Takehara
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Pollutant Emissions ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Iso Standard ◽  
Current State ◽  
Ceramic Components

With the aim of achieving higher efficiency, lower pollutant emissions, and multi-fuel capability for small to medium-sized gas turbine engines for use in co-generation systems, a ceramic gas turbine (CGT) research and development program is being promoted by the Japanese Ministry of International Trade and Industry (MITI) as a part of its “New Sunshine Project”. Kawasaki Heavy Industries (KHI) is participating in this program and developing a regenerative two-shaft CGT (CGT302). In 1993, KHI conducted the first test run of an engine with full ceramic components. At present, the CGT302 achieves 28.8% thermal efficiency at a turbine inlet temperature (TIT) of 1117°C under ISO standard conditions and an actual TIT of 1250°C has been confirmed at the rated speed of the basic CGT. This paper consists of the current state of development of the CGT302 and how ceramic components are applied.

A New Gas Turbine Combustor Alloy

1984 ◽  
Author(s):  
D. L. Klarstrom ◽  
H. M. Tawancy ◽  
D. E. Fluck ◽  
M. F. Rothman
Keyword(s):  
Solid Solution ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Nickel Base Superalloy ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
High Temperature Alloys ◽  
Oxidation Properties ◽  
Nickel Base ◽  
Base Superalloy

A wrought, nickel-base superalloy based on the Ni-Cr-W system has been developed for applications in the hot section of gas turbine engines. The new alloy is solid solution strengthened and very thermally stable. It particularly resists the formation of detrimental intermetallic compounds and contains little or no cobalt. Various mechanical and oxidation properties of the new alloy were measured, and the microstructural features were characterized. These were compared with those for other solid solution strengthened, high-temperature alloys. A number of advantages of the new alloy are defined.

Prediction of CO Emission Index for Aviation Gas Turbine Combustor Using Flamelet Generated Manifold Combustion Model

2021 ◽  
Author(s):  
Saurabh Patwardhan ◽  
Pravin Nakod ◽  
Stefano Orsino ◽  
Rakesh Yadav ◽  
Fang Xu ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Liquid Fuel ◽  
Operating Conditions ◽  
Turbine Engines ◽  
Combustion Model ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Flamelet Generated Manifold ◽  
Emission Index ◽  
Co Emission

Abstract Carbon monoxide (CO) has been identified as one of the regulated pollutants and gas turbine manufacturers target to reduce the CO emission from their gas turbine engines. CO forms primarily when carbonous fuels are not burnt completely, or products of combustion are quenched before completing the combustion. Numerical simulations are effective tools that allow a better understanding of the mechanisms of CO formation in gas turbine engines and are useful in evaluating the effect of different parameters like swirl, fuel atomization, mixing etc. on the overall CO emission for different engine conditions like idle, cruise, approach and take off. In this paper, a thorough assessment of flamelet generated manifold (FGM) combustion model is carried out to predict the qualitative variation and magnitude of CO emission index with the different configurations of a Honeywell test combustor operating with liquid fuel under idle condition, which is the more critical engine condition for CO emission. The different designs of the test combustor are configured in such a way that they yield different levels of CO and hence are ideal to test the accuracy of the combustion model. Large eddy simulation (LES) method is used for capturing the turbulence accurately along with the FGM combustion model that is computationally economical compared to the detailed/reduced chemistry modeling using finite rate combustion model. Liquid fuel spray breakup is modeled using stochastic secondary droplet (SSD) model. Four different configurations of the aviation gas turbine combustor are studied in this work referring to earlier work by Xu et al. [1]. It is shown that the FGM model can predict CO trends accurately. The other global parameters like exit temperature, NOx emissions, pattern factor also show reasonable agreement with the test data. The sensitivity of the CO prediction to the liquid fuel droplet breakup model parameters is also studied in this work. Although the trend of CO variation is captured for different values of breakup parameters, the absolute magnitude of CO emission index differs significantly with the change in the values of breakup parameters suggesting that the spray has a larger impact on the quantitative prediction of CO emission. An accurate prediction of CO trends at idle conditions using FGM model extends the applicability of FGM model to predict different engine operating conditions for different performance criteria accurately.

Modeling of Particle Wall Interaction and Film Transport Using Eulerian Wall Film Model

2014 ◽  
Author(s):  
Rahul Ingle ◽  
Ravi Yadav ◽  
Hemant Punekar ◽  
Jing Cao
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Blades ◽  
Continuous Phase ◽  
Pollutant Emissions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Secondary Atomization ◽  
Wall Film ◽  
Wall Interaction

The growing awareness of pollutant emissions from gas turbines has made it very important to study fuel atomization system, the spray wall interaction and hydrodynamic of film formed on engine walls. A precise fuel spray spatial distribution and efficient fuel air mixing plays important role in improving combustion performance. Cross-flow injection and film atomization technique has been studied extensively for gas turbine engines to achieve efficient combustion. Air blast atomizer is one of these kind of systems used in gas turbine engines which involves shear driven prefilmer secondary atomization. In addition to gas turbine combustor shear driven liquid wall film can be seen in IC engines, rocket nozzles, heat exchangers and also on steam turbine blades. In our work we have used Eulerian Wall Film (EWF) [1] model to simulate the experiment performed by Arienti et al. [2]. In the Arienti’s experiment liquid jet is injected from a nozzle from the top of the chamber. Droplets shed from the jet surface due to primary and later secondary atomization in the presence of high shearing cross flowing air. Further liquid fuel particles hit the wall to form film, film moves subjected to shear from the gas phase. Liquid film can reatomizes due to subgrid processes like stripping, splashing and film breakup. In current study we have validated Arienti et al. [2] experimental data by modeling complex & coupled physics of spray, film and continuous phase and by accounting complex subgrid processes.

Aldehydes Emissions Measurement and OFP Assessment of Biodiesel and its Blends With Kerosene Using a Low NOx Gas Turbine Combustor

2011 ◽  
Author(s):  
Hu Li ◽  
Mohamed A. Altaher ◽  
Gordon E. Andrews
Keyword(s):  
Gas Turbine ◽  
Alternative Fuels ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Animal Fats ◽  
Lack Of Information ◽  
Ozone Formation Potential ◽  
Potential Benefits ◽  
Biodiesel Fuels

There is more interest of using biodiesel fuels derived from vegetable oil or animal fats as alternative fuels for both diesel and gas turbine engines. This is mainly due to the potential benefits on CO2 reductions and renewable. Regulated emissions of biodiesel and its blends are widely studied in diesel engines and some gas turbine engines. However, there is a knowledge gap of lack of information about non-regulated pollutants such as carbonyl compounds (aldehydes etc). This paper assessed aldehydes emissions under atmospheric pressure and 600K using a radial swirler industrial low NOx gas turbine combustor. A comparison was made between B100 (100% WME), B20 (80% Kerosene: 20% WME) and pure Kerosene. A FTIR was used to determine aldehydes including formaldehyde, acetaldehyde and acrolein. OFP (Ozone Formation Potential) of formaldehyde emissions were assessed for these three fuels. The results showed that formaldehyde was the most prevalent aldehyde species for B100, B20 and kerosene, accounted for up to 50%. The aldehydes decreased as equivalence ratio increased due to the increased flame temperatures. A strong correlation between aldehydes emissions and flame temperatures was observed.

Lean Blowout Research in a Generic Gas Turbine Combustor With High Optical Access

1993 ◽  
Author(s):  
G. J. Sturgess ◽  
D. Shouse
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Air Force ◽  
Operating Conditions ◽  
Test Facility ◽  
Turbine Engines ◽  
Flame Stability ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Lean Blowout

The U.S. Air Force is conducting a comprehensive research program aimed at improving the design and analysis capabilities for flame stability and lean blowout in the combustors of aircraft gas turbine engines. As part of this program, a simplified version of a generic gas turbine combustor is used. The intent is to provide an experimental data base against which lean blowout modeling might be evaluated and calibrated. The design features of the combustor and its instrumentation are highlighted, and the test facility is described. Lean blowout results for gaseous propane fuel are presented over a range of operating conditions at three different dome flow splits. Comparison of results with those of a simplified research combustor is also made. Lean blowout behavior is complex, so that simple phenomenological correlations of experimental data will not be general enough for use as design tools.

Design and Performance Analysis of a Gas Turbine Flameless Combustor Using CFD Simulations

2012 ◽  
Author(s):  
Y. Levy ◽  
F. C. Christo ◽  
I. Gaissinski ◽  
V. Erenburg ◽  
V. Sherbaum
Keyword(s):  
Gas Turbine ◽  
Combustion Regime ◽  
Operating Conditions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Cfd Simulations ◽  
Flow Configurations ◽  
And Performance ◽  
Zone Radius

This study investigates the performance and the conditions under which flameless oxidation can be achieved for a given annular adiabatic combustor. Numerical modelling of velocity, temperature and species fields are performed for different flow configurations of air and methane streams injected into a proposed design of a gas-turbine combustor. Parametric analysis was performed by systematically varying several parameters: radius of a recirculation zone, radius of the combustor, location of air and fuel ports, air and fuel velocities magnitudes and injection angles. The analysis was performed initially using a three-step global chemistry model to identify a design (geometry and operating conditions) that yield flameless combustion regime. The selected design was then modelled using a skeletal (46 reactions) and a detailed (309 reactions) chemical kinetics mechanism. The k–ε turbulence model was used in the most calculations. Overall, similar qualitative flow, temperature, and species patterns were predicted by both kinetics models; however the detailed mechanism provides quantitatively more realistic predictions. An optimal flow configuration was achieved with exhaust NOx emissions of < 7.5 ppm, CO < 35ppm, and a pressure-drop < 5%, hence meeting the design criteria for gas turbine engines. This study demonstrates the feasibility of achieving ultra-low NOx and CO emissions utilising a flameless oxidation regime.

A Physics-Based Modeling Approach for Performance Monitoring in Gas Turbine Engines

2015 ◽  
Vol 64 (1) ◽  
pp. 197-205 ◽  
Author(s):  
Houman Hanachi ◽  
Jie Liu ◽  
Avisekh Banerjee ◽  
Ying Chen ◽  
Ashok Koul
Keyword(s):  
Gas Turbine ◽  
Performance Monitoring ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Modeling Approach

Lean Blowout Research in a Generic Gas Turbine Combustor With High Optical Access

1997 ◽  
Vol 119 (1) ◽  
pp. 108-118 ◽  
Author(s):  
G. J. Sturgess ◽  
D. Shouse
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Air Force ◽  
Operating Conditions ◽  
Test Facility ◽  
Turbine Engines ◽  
Flame Stability ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Lean Blowout

The U. S. Air Force is conducting a comprehensive research program aimed at improving the design and analysis capabilities for flame stability and lean blowout in the combustors of aircraft gas turbine engines. As part of this program, a simplified version of a generic gas turbine combustor is used. The intent is to provide an experimental data base against which lean blowout modeling might be evaluated and calibrated. The design features of the combustor and its instrumentation are highlighted, and the test facility is described. Lean blowout results for gaseous propane fuel are presented over a range of operating conditions at three different dome flow splits. Comparison of results with those of a simplified research combustor is also made. Lean blowout behavior is complex, so that simple phenomenological correlations of experimental data will not be general enough for use as design tools.

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