Design Procedures and a Developed Computer Code for Single Annular Combustor Preliminary Design

Mohammad, Bassam; Jeng, San‐Mou

doi:10.2514/6.2009-5208

Cited by 11 publications

(20 citation statements)

References 6 publications

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“…Mellor (2) has provided a list of empirical and semi-empirical tools for designing conventional combustors. In addition B. S. Mohammad (8) has introduced his preliminary design procedure of a conventional single annular combustor.…”

Section: Design Procedures and Resultsmentioning

confidence: 99%

“…Generally the design of a combustor (8)(9) is examined from inlet to outlet. This permits the inlet diffuser, combustion chamber flow-path, combustor primary zone, dilution zone and liner cooling methods to be designed individually.…”

Section: Design Procedures and Resultsmentioning

confidence: 99%

“…For cooling considerations the ratio of the dome cooling flow rate to the combustor air flow rate is assumed as 14%. Cooling ratios ranges between 10-15% for a typical combustor (8) . Meanwhile the remaining air flow can be used as liner cooling air and dilution air.…”

Section: Casing and Linermentioning

confidence: 99%

“…Mohammad and Jeng (8) have proposed a design procedure for the preliminary design of a single annular combustor and its performance. In one of the studies recently published by our group members (9) , the design procedure of a reverse flow combustor for a helicopter engine with high temperature rise has been presented.…”

Section: Introductionmentioning

confidence: 99%

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

Khandelwal

Karakurt

Sethi

et al. 2013

Aeronaut. j. (1968)

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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.

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Section: Design Procedures and Resultsmentioning

confidence: 99%

Section: Design Procedures and Resultsmentioning

confidence: 99%

Section: Casing and Linermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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

Khandelwal

Karakurt

Sethi

et al. 2013

Aeronaut. j. (1968)

View full text Add to dashboard Cite

show abstract

“…There are multi-rows inclined multi-holes, the first-row primary dilution holes and the second-row secondary dilution holes in the liner. The combustor in the experiment of the present paper is designed [15][16][17][18] at design point's fuel-air ratio of 0.033 and it is a small mass flow rate combustor. The combustion chamber has the following characteristics:…”

Section: Methodsmentioning

confidence: 99%

Effect of dilution holes on the performance of a triple swirler combustor

Ding

Zhao

et al. 2014

Chinese Journal of Aeronautics

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A triple swirler combustor is considered to be a promising solution for future high temperature rise combustors.The present paper aims to study dilution holes including primary dilution holes and secondary dilution holes on the performance of a triple swirler combustor. Experimental investigations are conducted at different inlet airflow velocities (40-70 m/s) and combustor overall fuel-air ratio with fixed inlet airflow temperature (473 K) and atmospheric pressure. The experimental results show that the ignition is very difficult with specific performance of high ignition fuel-air ratio when the primary dilution holes are located 0.6H (where H is the liner dome height)downstream the dome, while the other four cases have almost the same ignition performance. The position of primary dilution holes has an effect on lean blowout stability and has a large influence on combustion efficiency.The combustion efficiency is the highest when the primary dilution holes are placed 0.9H downstream the dome among the five different locations. For the secondary dilution holes, the pattern factor of Design A is better than that of Design B.

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Effect of steam addition on gas turbine combustor design and performance

Xue

Sethi

et al. 2016

Applied Thermal Engineering

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Adding steam influences the combustion process inside the combustor, which should be taken into account during combustor design. The design of combustor has long been the most challenging process. This study integrated the gas turbine performance with the combustor design, and formulated a detailed procedure for single annular combustors with steam addition consideration in particular. To accomplish this, a computer code has been developed based on the design procedures. The design model could provide the combustor geometry and the combustor performance. The inlet parameters for combustor design are obtained and validated through the calculation of gas turbine engine performance provided by our own home code. The model predictions are compared with operational and configuration data from two real engines and show reasonably good accuracy. The influence of steam addition on combustor design is investigated and results showed the variation of geometrical size is highest for components where intense combustion takes place while the design is almost kept the same for components where only pure flow exists. After conforming the feasibility of the combustor design code, we investigated the effects of steam addition on combustor performance. It revealed that steam injection is an effective way to reduce the temperature in the burner while other performance like the total pressure loss would be slightly deteriorated.

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Design Procedures and a Developed Computer Code for Single Annular Combustor Preliminary Design

Cited by 11 publications

References 6 publications

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

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

Effect of dilution holes on the performance of a triple swirler combustor

Effect of steam addition on gas turbine combustor design and performance

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