Development of a Compact Gas Turbine Combuster to Give Extended Life and Acceptable Exhaust Emissions

1979 ◽  
Vol 101 (3) ◽  
pp. 349-357 ◽  
Author(s):  
D. McKnight
Keyword(s):  
Gas Turbine ◽  
Industrial Application ◽  
Engine Performance ◽  
Development Effort ◽  
Gas Turbine Combustor ◽  
Development History ◽  
Low Emission ◽  
Percent Increase ◽  
Two Factors ◽  
History Of

The paper describes the development history of the Olympus gas turbine combustor from the time that it was first applied to an industrial application in the early 1960s. The design improvements made — • to permit a change in fuel (from kerosene to diesel and/or natural gas), • a 60 percent increase in engine performance, and • to reduce emission levels — are detailed, and the in-service problems associated with these changes are also discussed. The emphasis is placed upon improvements in combustor life and capability to produce smoke levels well below the visible threshold, and significant success is shown to have been achieved in these two factors. The final sections of the paper are concerned with the latest on-going development effort, which is primarily to produce a low emission combustor that can be retrofitted into today’s engines.

Numerical simulation of a low-emission gas turbine combustor using KIVA-II

1992 ◽  
Vol 15 (8) ◽  
pp. 865-881 ◽  
Author(s):  
S. L. Yang ◽  
R. Chen ◽  
M. C. Cline ◽  
H. L. Nguyen ◽  
G. J. Micklow
Keyword(s):  
Numerical Simulation ◽  
Gas Turbine ◽  
Gas Turbine Combustor ◽  
Low Emission

Preliminary design and performance analysis of a low emission aero-derived gas turbine combustor

2013 ◽  
Vol 117 (1198) ◽  
pp. 1249-1271 ◽  
Author(s):  
B. Khandelwal ◽  
A. Karakurt ◽  
V. Sethi ◽  
R. Singh ◽  
Z. Quan
Keyword(s):  
Gas Turbine ◽  
Combustion Efficiency ◽  
Operating Conditions ◽  
Gas Turbine Combustor ◽  
Detailed Method ◽  
Low Emission ◽  
Heat Shields ◽  
Lean Fuel ◽  
Reduce Emissions ◽  
And Performance

Abstract Modern gas turbine combustor design is a complex task which includes both experimental and empirical knowledge. Numerous parameters have to be considered for combustor designs which include combustor size, combustion efficiency, emissions and so on. Several empirical correlations and experienced approaches have been developed and summarised in literature for designing conventional combustors. A large number of advanced technologies have been successfully employed to reduce emissions significantly in the last few decades. There is no literature in the public domain for providing detailed design methodologies of triple annular combustors. The objective of this study is to provide a detailed method designing a triple annular dry low emission industrial combustor and evaluate its performance, based on the operating conditions of an industrial engine. The design methodology employs semi-empirical and empirical models for designing different components of gas turbine combustors. Meanwhile, advanced DLE methods such as lean fuel combustion, premixed methods, staged combustion, triple annular, multi-passage diffusers, machined cooling rings, DACRS and heat shields are employed to cut down emissions. The design process is shown step by step for design and performance evaluation of the combustor. The performance of this combustor is predicted, it shows that NO x emissions could be reduced by 60%-90% as compared with conventional single annular combustors.

scholarly journals Gas Turbine Applications for Railcar in Japan

1974 ◽  
Author(s):  
S. Takita
Keyword(s):  
Gas Turbine ◽  
Industrial Application ◽  
High Speed ◽  
Rolling Stock ◽  
Prime Mover ◽  
History Of Development ◽  
History Of

In 1967, IHI engaged in developing a gas turbine for high speed railcars as an industrial application of the aero gas turbine CT58. Since then, IM100-1R and IM100-2R engines, derived from CT58’s, have been tested on the bench and on experimental railcars by the Japanese Rolling Stock Manufacturers association (JRSMA) and the Japan National Railway (JNR). In this paper, a brief history of development tests for gas turbine railcars, problems and improvements in applications of the IM100-1R and -2R for prime mover of the railcar are described.

scholarly journals Investigations of a Gas Turbine Low-Emission Combustor Operating on the Synthesis Gas

2017 ◽  
Vol 2017 ◽  
pp. 1-14 ◽  
Author(s):  
Serhiy Serbin ◽  
Nataliia Goncharova
Keyword(s):  
Power Generation ◽  
Nitrogen Oxides ◽  
Gas Turbine ◽  
Synthesis Gas ◽  
Geometry Optimization ◽  
Gas Turbine Combustor ◽  
Lean Burn ◽  
Operation Modes ◽  
Low Emission ◽  
Combustion Technology

Investigations of the working processes in a gas turbine low-emission combustor operating on the synthesis gas, in which the principle of RQL (Rich-Burn, Quick-Mix, and Lean-Burn) combustion technology is realized, have been performed. Selected concept of a gas turbine combustor can provide higher performance and lower emission of nitrogen oxides and demonstrates satisfactory major key parameters. Obtained results and recommendations can be used for the gas turbine combustor operation modes modeling, geometry optimization, and prospective power generation units design and engineering.

scholarly journals The GE Rich-Quench-Lean Gas Turbine Combustor

1998 ◽  
Vol 120 (3) ◽  
pp. 502-508 ◽  
Author(s):  
A. S. Feitelberg ◽  
M. A. Lacey
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Coal Gasification ◽  
Perforated Plate ◽  
Combined Cycle ◽  
Development Effort ◽  
Nox Emissions ◽  
Gas Turbine Combustor ◽  
Chemical Kinetic Model ◽  
The Rich

The General Electric Company has developed and successfully tested a full-scale, F-class (2550°F combustor exit temperature), rich-quench-lean (RQL) gas turbine combustor, designated RQL2, for low heating value (LHV) fuel and integrated gasification combined cycle applications. Although the primary objective of this effort was to develop an RQL combustor with lower conversion of fuel bound nitrogen to NOx than a conventional gas turbine combustor, the RQL2 design can be readily adapted to natural gas and liquid fuel combustion. RQL2 is the culmination of a 5 year research and development effort that began with natural gas tests of a 2” diameter perforated plate combustor and included LHV fuel tests of RQL1, a reduced scale (6” diameter) gas turbine combustor. The RQL2 combustor includes a 14” diameter converging rich stage liner, an impingement cooled 7” diameter radially-stratified-quench stage, and a backward facing step at the entrance to a 10” diameter film cooled lean stage. The rich stage combustor liner has a novel double-walled structure with narrow circumferential cooling channels to maintain metal wall temperatures within design limits. Provisions were made to allow independent control of the air supplied to the rich and quench/lean stages. RQL2 has been fired for almost 100 hours with LHV fuel supplied by a pilot scale coal gasification and high temperature desulfurization system. At the optimum rich stage equivalence ration NOx emissions were about 50 ppmv (on a dry, 15 percent O2 basis), more than a factor of 3 lower than expected from a conventional diffusion flame combustor burning the same fuel. With 4600 ppmv NH3 in the LHV fuel, this corresponds to a conversion of NH3 to NOx of about 5 percent. As conditions were shifted away from the optimum, RQL2 NOx emissions gradually increased until they were comparable to a standard combustor. A chemical kinetic model of RQL2, constructed from a series of ideal chemical reactors, matched the measured NOx emissions fairly well. The CO emissions were between 5 and 30 ppmv (on a dry, 15 percent O2 basis) under all conditions.

Preliminary Study of Low Emission Gas Turbine Combustor With Airblast Fuel Atomizer

1976 ◽  
Vol 98 (1) ◽  
pp. 15-22
Author(s):  
K. Yamanaka ◽  
K. Nagato
Keyword(s):  
Gas Turbine ◽  
Fuel Injection ◽  
Tube Wall ◽  
Combustion Stability ◽  
Exhaust Emission ◽  
Fuel Injector ◽  
Gas Turbine Combustor ◽  
Low Emission ◽  
New Type ◽  
Preliminary Study

Recent papers describe that an airblast fuel atomizer is very effective for reducing emissions from a gas turbine and this type of fuel injector is being applied to practical engines. This paper deals with the new type of airblast fuel atomizer AFIT which comes from “Airblast Fuel Injection Tube” that makes fuel to break up into droplets by atomizing air at several small holes on the tube wall and fuel is well mixed with atomizing air instantly at the exits of holes. Regarding this AFIT, the fuel spray characteristics, combustion stability which is usually narrow for the combustor with an airblast fuel atomizer at lower engine speeds and exhaust emission levels are experimented and its effectiveness is discussed.

scholarly journals Developments in Air Cooling of Gas Turbine Vanes and Blades

1983 ◽  
Author(s):  
Darryl E. Metzger
Keyword(s):  
Gas Turbine ◽  
Research Work ◽  
Engine Performance ◽  
Detailed Knowledge ◽  
Air Cooling ◽  
Turbine Engine ◽  
Engine Cooling ◽  
History Of ◽  
Effective Use ◽  
Cooling Air

Over the history of gas turbine engine development, improvements in engine performance are closely tied to increases in the level of tolerable turbine inlet temperatures. The ability to operate at increasingly high temperatures has been the result of both improvements in materials capability and advances in the art of cooling the hot section components. For propulsion engines and their derivatives the cooling medium is air supplied from the compressor stages, requiring an expense of engine power. The hot section airfoils, particularly the first stage vanes and blades, consume a significant fraction of the total engine cooling air. Designers are continuously faced with the task of making more effective use of the coolant to improve either performance or durability or both. The design process requires detailed knowledge of heat transfer and flow friction characteristics for present and candidate future cooling schemes. Typical current cooling schemes and associated research work directed to future improved designs are discussed.

scholarly journals Theoretical Investigations of a Dual-Fuel Low-Emission Gas Turbine Combustor

2020 ◽  
Vol 0 (1) ◽  
pp. 27-33
Author(s):  
Badri Tengizovich Diasamidze ◽  
Sergii Volodimirovich Vilkul ◽  
Serhiy Ivanovich Serbin
Keyword(s):  
Gas Turbine ◽  
Dual Fuel ◽  
Gas Turbine Combustor ◽  
Low Emission ◽  
Theoretical Investigations

scholarly journals Performance Testing of a Low Emissions, Natural-Gas Fired, Small Gas Turbine Combustor

1989 ◽  
Author(s):  
K. O. Smith ◽  
G. W. Wade ◽  
M. H. Samii ◽  
H. K. Mak
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Performance Testing ◽  
Development Effort ◽  
Nox Emissions ◽  
Gas Turbine Combustor ◽  
Initial Development ◽  
Lean Premixed ◽  
Engine Testing

The initial development of a lean-premixed, natural gas-fired combustor for a 200 kw gas turbine is described. The development effort included both rig testing and on-engine testing of the combustor. The combustor demonstrated an ultra-low NOx emissions capability in both test environments.

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