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Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine

Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review

Authors

  • Panagiotis Ignatidis
  • Viet d. Nghiem
  • Jan Goeing
  • Marcel Oettinger
  • Henrik Von der haar *,
  • Joerg r. Seume
  • Friedrich Dinkelacker

Research Organisations

External Research Organisations

  • Technische Universität Braunschweig

Details

Original languageEnglish
Title of host publicationProceedings of Global Power and Propulsion Society
Publication statusPublished - 18 Sept 2022
EventGPPS Technical Conference 2022 (GPPS Chania22) - Chania, Greece
Duration: 12 Sept 2022 → 14 Sept 2022
https://gpps.global/gpps-chania22/

Publication series

NameProceedings of Global Power and Propulsion Society
ISSN (electronic)2504-4400

Abstract

Malfunctions in the combustion chamber of aircraft engines influence downstream turbines. If individual burners vary in their performance, cold or hot streaks can enter and propagate through the turbine section and alter the temperature distribution in the exhaust of the engine. Analysing the variances in the temperature distribution of the exhaust jet provides information on the failure modes of the combustor. This can be used to identify damage to the aircraft engine, accelerate the inspection process and reduce maintenance cost. To investigate the influence of combustor failure on the temperature distribution, CFD simulations of a defined defect are carried out in this paper for a real size gasturbine engine. For this purpose, the total failure of one fuel nozzle in the combustion chamber, which results in a cold gas streak entering the turbine, is simulated. The cold streak is analysed by performing a turbine simulation for which the combustor exit profile is used on as an inlet condition. The simulations were performed using two different techniques. A frozen-rotor approach was used for the steady-state method to estimate the geometric influence on the mixing. The influence of the blade rotation is considered via unsteady simulation. The disturbance width and propagation were determined for both methods. The mixing and dispersion processes are found to be strong in the high pressure part of the turbine and are strongly influenced by the engine rotational speed.

Cite this

Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine. / Ignatidis, Panagiotis; Nghiem, Viet d.; Goeing, Jan et al.
Proceedings of Global Power and Propulsion Society. 2022. (Proceedings of Global Power and Propulsion Society).

Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review

Ignatidis, P, Nghiem, VD, Goeing, J, Oettinger, M, Von der haar *, H, Friedrichs, J, Seume, JR & Dinkelacker, F 2022, Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine. in Proceedings of Global Power and Propulsion Society. Proceedings of Global Power and Propulsion Society, GPPS Technical Conference 2022 (GPPS Chania22), Chania, Greece, 12 Sept 2022. https://doi.org/10.33737/gpps22-tc-103
Ignatidis, P., Nghiem, V. D., Goeing, J., Oettinger, M., Von der haar *, H., Friedrichs, J., Seume, J. R., & Dinkelacker, F. (2022). Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine. In Proceedings of Global Power and Propulsion Society (Proceedings of Global Power and Propulsion Society). https://doi.org/10.33737/gpps22-tc-103
Ignatidis P, Nghiem VD, Goeing J, Oettinger M, Von der haar *, H, Friedrichs J et al. Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine. In Proceedings of Global Power and Propulsion Society. 2022. (Proceedings of Global Power and Propulsion Society). doi: 10.33737/gpps22-tc-103
Ignatidis, Panagiotis ; Nghiem, Viet d. ; Goeing, Jan et al. / Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine. Proceedings of Global Power and Propulsion Society. 2022. (Proceedings of Global Power and Propulsion Society).
Download
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title = "Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine",
abstract = "Malfunctions in the combustion chamber of aircraft engines influence downstream turbines. If individual burners vary in their performance, cold or hot streaks can enter and propagate through the turbine section and alter the temperature distribution in the exhaust of the engine. Analysing the variances in the temperature distribution of the exhaust jet provides information on the failure modes of the combustor. This can be used to identify damage to the aircraft engine, accelerate the inspection process and reduce maintenance cost. To investigate the influence of combustor failure on the temperature distribution, CFD simulations of a defined defect are carried out in this paper for a real size gasturbine engine. For this purpose, the total failure of one fuel nozzle in the combustion chamber, which results in a cold gas streak entering the turbine, is simulated. The cold streak is analysed by performing a turbine simulation for which the combustor exit profile is used on as an inlet condition. The simulations were performed using two different techniques. A frozen-rotor approach was used for the steady-state method to estimate the geometric influence on the mixing. The influence of the blade rotation is considered via unsteady simulation. The disturbance width and propagation were determined for both methods. The mixing and dispersion processes are found to be strong in the high pressure part of the turbine and are strongly influenced by the engine rotational speed.",
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Download

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AU - Ignatidis, Panagiotis

AU - Nghiem, Viet d.

AU - Goeing, Jan

AU - Oettinger, Marcel

AU - Von der haar ,, Henrik

AU - Friedrichs, Jens

AU - Seume, Joerg r.

AU - Dinkelacker, Friedrich

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N2 - Malfunctions in the combustion chamber of aircraft engines influence downstream turbines. If individual burners vary in their performance, cold or hot streaks can enter and propagate through the turbine section and alter the temperature distribution in the exhaust of the engine. Analysing the variances in the temperature distribution of the exhaust jet provides information on the failure modes of the combustor. This can be used to identify damage to the aircraft engine, accelerate the inspection process and reduce maintenance cost. To investigate the influence of combustor failure on the temperature distribution, CFD simulations of a defined defect are carried out in this paper for a real size gasturbine engine. For this purpose, the total failure of one fuel nozzle in the combustion chamber, which results in a cold gas streak entering the turbine, is simulated. The cold streak is analysed by performing a turbine simulation for which the combustor exit profile is used on as an inlet condition. The simulations were performed using two different techniques. A frozen-rotor approach was used for the steady-state method to estimate the geometric influence on the mixing. The influence of the blade rotation is considered via unsteady simulation. The disturbance width and propagation were determined for both methods. The mixing and dispersion processes are found to be strong in the high pressure part of the turbine and are strongly influenced by the engine rotational speed.

AB - Malfunctions in the combustion chamber of aircraft engines influence downstream turbines. If individual burners vary in their performance, cold or hot streaks can enter and propagate through the turbine section and alter the temperature distribution in the exhaust of the engine. Analysing the variances in the temperature distribution of the exhaust jet provides information on the failure modes of the combustor. This can be used to identify damage to the aircraft engine, accelerate the inspection process and reduce maintenance cost. To investigate the influence of combustor failure on the temperature distribution, CFD simulations of a defined defect are carried out in this paper for a real size gasturbine engine. For this purpose, the total failure of one fuel nozzle in the combustion chamber, which results in a cold gas streak entering the turbine, is simulated. The cold streak is analysed by performing a turbine simulation for which the combustor exit profile is used on as an inlet condition. The simulations were performed using two different techniques. A frozen-rotor approach was used for the steady-state method to estimate the geometric influence on the mixing. The influence of the blade rotation is considered via unsteady simulation. The disturbance width and propagation were determined for both methods. The mixing and dispersion processes are found to be strong in the high pressure part of the turbine and are strongly influenced by the engine rotational speed.

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