scholarly journals Emissions and Performance of Catalysts for Gas Turbine Catalytic Combustors

1977 ◽  
Author(s):  
D. N. Anderson
Keyword(s):  
Gas Turbine ◽  
Combustion Efficiency ◽  
Temperature Pattern ◽  
Turbine Engine ◽  
Reference Velocity ◽  
Test Conditions ◽  
Exit Temperature ◽  
And Performance ◽  
Catalytic Combustor ◽  
Emissions And Performance

Three noble-metal monolithic catalysts were tested in a 12-cm-dia combustion test rig to obtain emissions and performance data at conditions simulating the operation of a catalytic combustor for an automotive gas turbine engine. Tests with one of the catalysts at 800 K inlet mixture temperature, 3 × 105 Pa (3 atm) pressure, and a reference velocity (catalyst bed inlet velocity) of 10 m/sec demonstrated greater than 99 percent combustion efficiency for reaction temperatures higher than 1300 K. With a reference velocity of 25 m/sec the reaction temperature required to achieve the same combustion efficiency increased to 1380 K. The exit temperature pattern factors for all three catalysts were below 0.1 when adiabatic reaction temperatures were higher than 1400 K. The highest pressure drop was 4.5 percent at 25 m/sec reference velocity. Nitrogen oxides emissions were less than 0.1 g NO2/kg fuel for all test conditions.

scholarly journals Swirl-Can Combustor Performance to Near-Stoichiometric Fuel-Air Ratio

1976 ◽  
Author(s):  
L. A. Diehl ◽  
J. A. Biaglow
Keyword(s):  
Air Temperature ◽  
Combustion Efficiency ◽  
Oxides Of Nitrogen ◽  
Module Design ◽  
Air Temperatures ◽  
Nitrogen Emission ◽  
Unburned Hydrocarbons ◽  
Exit Temperature ◽  
And Performance ◽  
Emissions And Performance

Emissions and performance characteristics were determined for two full-annulus swirl-can modular combustors operated to near-stoichiometric fuel air ratios. The purposes of the tests were to obtain stoichiometric data at inlet-air temperatures up to 894 K and to determine the effect of module number by investigating 120 and 72 module swirl-can combustors. The maximum average exit temperature obtained with the 120-module swirl-can combustor was 2465 K with a combustion efficiency of 95 percent at an inlet-air temperature of 894 K. The 72-module swirl-can combustor reached a maximum average exit temperature of 2306 K with a combustion efficiency of 92 percent at an inlet-air temperature of 894 K. At a constant inlet air temperature, maximum oxides of nitrogen emission index values occurred at a fuel-air ratio of 0.037 for the 72-module design and 0.044 for the 120-module design. The combustor average exit temperature and combustion efficiency were calculated from emissions measurements. The measured emissions included carbon monoxide, unburned hydrocarbons, oxides of nitrogen, and smoke.

scholarly journals Full Annular Rig Development of the FT8 Gas Turbine Combustor

1990 ◽  
Author(s):  
T. G. Fox ◽  
B. C. Schlein
Keyword(s):  
Gas Turbine ◽  
Liquid Fuel ◽  
Water Injection ◽  
Gas Turbine Combustor ◽  
Exit Temperature ◽  
Reduce Emissions ◽  
Engine Testing ◽  
And Performance ◽  
Industrial Gas Turbine ◽  
Emissions And Performance

The results of developmental testing in a high pressure, full annular combustion section af the FT8 industrial gas turbine are presented. Base power conditions were simulated at approximately 60% of burner pressure. All aspects of combustion performance with liquid fuel were investigated, including starting, blowout, exit temperature signature, emissions, smoke and liner wall temperature. Configurational changes were made to improve liner cooling, reduce emissions, adjust pressure loss and modify exit temperature profile. The effects of water injection on emissions and performance were evaluated in the final test run. Satisfactory performance in all areas was demonstrated with further refinements to be carried out during developmental engine testing.

Full Annular Rig Development of the FT8 Gas Turbine Combustor

1992 ◽  
Vol 114 (1) ◽  
pp. 27-32 ◽  
Author(s):  
T. G. Fox ◽  
B. C. Schlein
Keyword(s):  
Gas Turbine ◽  
Liquid Fuel ◽  
Water Injection ◽  
Gas Turbine Combustor ◽  
Exit Temperature ◽  
Reduce Emissions ◽  
Engine Testing ◽  
And Performance ◽  
Industrial Gas Turbine ◽  
Emissions And Performance

The results of developmental testing in a high-pressure, full annular combustion section of the FT8 industrial gas turbine are presented. Base power conditions were simulated at approximately 60 percent of burner pressure. All aspects of combustion performance with liquid fuel were investigated, including starting, blowout, exit temperature signature, emissions, smoke, and liner wall temperature. Configurational change were made to improve liner cooling, reduce emissions, adjust pressure loss, and modify exit temperature profile. The effects of water injection on emissions and performance were evaluated in the final test run. Satisfactory performance in all areas was demonstrated with further refinements to be carried out during developmental engine testing.

scholarly journals Some Aspects on Increasing Gas Turbine Combustor Exit Temperature

1980 ◽  
Author(s):  
B. G. A. Sjöblom
Keyword(s):  
Gas Turbine ◽  
Combustion Efficiency ◽  
Inlet Temperature ◽  
Temperature Pattern ◽  
Gas Turbine Combustor ◽  
Turbine Inlet Temperature ◽  
Air Mixing ◽  
Power Setting ◽  
Exit Temperature ◽  
Cycle Efficiency

A high turbine inlet temperature promotes the gas turbine overall cycle efficiency. Problems arising in the combustion system when increasing the temperature are discussed. A high exit temperature aircraft gas turbine combustor was designed by deleting the dilution air in a double recirculation zone combustor. Rig test were carried out and comparisions were made with a reference combustor of conventional design. It was found that the overall fuel-air ratio could be increased from 0.0182 to 0.0315 without imparing the emission characteristics or the combustion efficiency at any power setting. The exit temperature pattern factor was improved by providing a proper fuel and air mixing.

Thermo-mechanical fatigue crack growth behaviour of Ti-6246

2021 ◽  
Author(s):  
◽  
Jennie Palmer
Keyword(s):  
Fatigue Crack ◽  
Fatigue Crack Growth ◽  
Gas Turbine ◽  
Crack Growth ◽  
Growth Rates ◽  
Turbine Engine ◽  
Mechanical Fatigue ◽  
Test Conditions ◽  
Materials Used ◽  
Crack Growth Rates

Within the gas turbine engine, the high transient thermal stresses developed due to variations in power requirements during a typical flight cycle give rise to the phenomenon of thermo-mechanical fatigue (TMF). Associated with higher operating temperatures, the study of TMF within the gas turbine engine has mainly been focused on materials used in the latter turbine sections. However, the increasing temperatures to improve operating efficiency have led to the requirements for an understanding of the TMF behaviour in materials used for the later stages of the compressor. As such, fatigue crack growth rates are required to be evaluated under non-isothermal conditions along with the development of a detailed understanding of related failure mechanisms. In the current study a bespoke TMF crack growth (TMFCG) test set up has been developed and validated to investigate the TMFCG behaviour of the titanium alloy, Ti-6246. The study has explored the effects of phasing between mechanical loading and temperature, as well as the effects of maximum cycle temperature. Results show in-phase (IP) test conditions to have faster crack growth rates than out-of-phase (OP) test conditions, due to increased temperature at peak stress and therefore increased time-dependent crack growth. Fractography evidences subtle differences in fracture mechanisms and the microstructural analysis along the crack path has aided the characterisation of damage mechanisms in IP and OP test conditions.

Development of Dry Low-NOx Combustor for 300 kW Class Gas Turbine Applied to Co-Generation Systems

2001 ◽  
Author(s):  
Yoichiro Ohkubo ◽  
Osamu Azegami ◽  
Hiroshi Sato ◽  
Yoshinori Idota ◽  
Shinichiro Higuchi
Keyword(s):  
Gas Turbine ◽  
Output Power ◽  
Combustion Efficiency ◽  
Gas Generator ◽  
Turbine Engine ◽  
Partial Load ◽  
Wide Range ◽  
Compressor Inlet ◽  
Endurance Testing ◽  
Turbine Speed

A 300 kWe class gas turbine which has a two-shaft and simple-cycle has been developed to apply to co-generation systems. The gas turbine engine is operated in the range of about 30% partial load to 100% load. The gas turbine combustor requires a wide range of stable operations and low NOx characteristics. A double staged lean premixed combustor, which has a primary combustion duct made of Si3N4 ceramics, was developed to meet NOx regulations of less than 80 ppm (corrected at 0% oxygen). The gas turbine with the combustor has demonstrated superior low-emission performance of around 40 ppm (corrected at 0% oxygen) of NOx, and more than 99.5% of combustion efficiency between 30% and 100% of engine load. Endurance testing has demonstrated stable high combustion performance over 3,000 hours in spite of a wide compressor inlet air temperature (CIT) range of 5 to 35 degree C.. While increasing the gas generator turbine speed, the flow rate of primary fuel was controlled to hold a constant equivalence ratio of around 0.5 in the CIT range of more than 15 C. The output power was also decreased while increasing the CIT, in order to keep a constant temperature at the turbine inlet. The NOx decreases in the CIT range of more than 15 C. On the other hand, the NOx increases in the CIT range of less than 15 C when the output power was kept a constant maximum power. As a result, NOx emission has a peak value of about 40 ppm at 15 C.

Development of a Dual-Fuel Gas Turbine Engine of Liquid and Low-Calorific Gas

2005 ◽  
Author(s):  
Masamichi Koyama ◽  
Hiroshi Fujiwara
Keyword(s):  
Gas Turbine ◽  
Sewage Treatment ◽  
Energy Resource ◽  
Biomass Energy ◽  
Dual Fuel ◽  
Fuel Gas ◽  
Turbine Engine ◽  
Reference Velocity ◽  
Continuous Use ◽  
Wasted Energy

We developed a dual-fuel single can combustor for the Niigata Gas Turbine (NGT2BC), which was developed as a continuous-duty gas turbine capable of burning both kerosene and digester gas. The output of the NGT2BC is 920 kW for continuous use with digester gas and 1375 kW for emergency use with liquid fuel. Digester gas, obtained from sludge processing at sewage treatment plants, is a biomass energy resource whose use reduces CO2 emissions and take advantage of an otherwise wasted energy source. Design features for good combustion with digester gas include optimized the good matching of gas injection and swirl air and reduced reference velocity. The optimal combination of these parameters was determined through CFD analysis and atmospheric rig testing.

scholarly journals Evaluation of a Catalytic Combustor in a Gas Turbine-Generator Unit

1990 ◽  
Author(s):  
Shinichi Kajita ◽  
Yasutaroh Tanaka ◽  
Junichi Kitajima
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Development Program ◽  
Combustion Efficiency ◽  
Turbine Generator ◽  
Operation Test ◽  
Generator Unit ◽  
Catalytic Combustor ◽  
Generator Output ◽  
Very High

As a final step of the Catalytic Combustor Development Program, a catalytic combustor developed was tested in a 150-kW gas turbine-generator unit. A digital control system was developed to improve its controllability for a transient operation, and a 200-hr continuous operation test was performed to asses the durability of the catalyst. During the test, an excellent performance of the control system was verified, and a very high combustion efficiency of more than 99% and a ultra-low NOx level of less than 5.6 ppm (at 15% O2) were achieved at a 150-kW generator output. In addition, the combustion efficiency has been maintained at over 98% for 200 hours of operation. However, the catalyst exposed to 200 hours of operation showed signs of deactivation.

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