Economic and environmental impact assessments of hybridized aircraft engines with hydrogen and other fuels

Seyam, Shaimaa; Dinçer, İbrahim; Agelin‐Chaab, Martin

doi:10.1016/j.ijhydene.2022.01.171

Cited by 15 publications

(9 citation statements)

References 18 publications

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“…A drawback of the works [2][3][4][5] is the determination of enthalpy only as a function of temperature, which does not allow for a correct representation of the equivalent chemical reaction path and does not account for the thermal dissociation of combustion products. In [6], a study of a hybrid aircraft engine was conducted using three approaches: exergetic, exergoeconomic, and exergo-ecological analysis. Five alternative fuel types with different concentrations were selected for the study.…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

“…In [7], six chemical nonequilibrium models are compared under various conditions encountered in real rocket engines. Unlike [2][3][4][5], the works [6,7] consider thermal dissociation of combustion products but do not accurately describe the equivalent chemical reaction path.…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

“…Thus, a common drawback of the mathematical models presented in [2][3][4][5][6][7] is the lack of analysis of the equivalent chemical reaction path at pressure other than standard one. Specifically, the absence of two additional isothermal processes: transitioning from actual pressure to standard one and reversing from standard pressure to actual one.…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

“…To account for the influence of pressure and thermal dissociation, two approaches can be employed: solving a system of chemical kinetics equations with a large number of equations [6,7], or utilizing experimental values of enthalpies or specific isobaric heat capacity с р as functions of temperature Т and pressure p [8]. Additionally, by adopting the second approach to determine the enthalpy of combustion products, we obtain a correctly formulated equivalent chemical reaction path.…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

See 3 more Smart Citations

Working process model development of the gas turbine engine combustor fueling on methanol

Shevchenko,

Ambrozhevich,

Fesenko

2024

EEJET

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The use of methanol as a fuel for aircraft and stationary gas turbine engines (GTE) is a priority direction in engine building. It is well known that when modeling the GTE performances using first-level mathematical models, there is an error in calculating specific fuel consumption, which is caused by the simplified description of the GTE combustor working process. The object of the study is the working process in the GTE combustor fueling on methanol. The peculiarity of the developed mathematical model of the working process of the GTE combustor is the use of enthalpy dependencies on temperature, pressure, and mixture composition. Enthalpy dependencies in this form implicitly account for the effect of thermal dissociation and allow for the correct formulation of the equivalent combustion reaction path. For two components (H2O and CO2), accounting for pressure leads to the fact that at standard temperature and partial pressures exceeding the saturation pressure, these components exist in a liquid state. This situation, with a constant enthalpy increment in the equivalent process of heating the combustion products from the standard temperature to the temperature at the end of adiabatic heat supply, decreases this temperature. Clarification of the temperature at the combustor outlet leads to changes in all calculated combustor performances, including the combustor fuel air ratio. The calculation results of the fuel air ratio are compared with known experimental data of the General Electric CF6-80A engine combustor (USA). The average calculation error of the fuel air ratio does not exceed 4 %. The developed model can be implemented in existing and developing mathematical models of gas turbine engines for temperatures at the end of the combustion process below 2,600 K

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Section: Literature Review and Problem Statementmentioning

confidence: 99%

Section: Literature Review and Problem Statementmentioning

confidence: 99%

Section: Literature Review and Problem Statementmentioning

confidence: 99%

Section: Literature Review and Problem Statementmentioning

confidence: 99%

See 2 more Smart Citations

Working process model development of the gas turbine engine combustor fueling on methanol

Shevchenko,

Ambrozhevich,

Fesenko

2024

EEJET

View full text Add to dashboard Cite

show abstract

“…Researchers focused on aircraft design with fuel cells and hydrogen [27], hybridized aircraft engines [28] [29], hydrogen infrastructure [30] and so on. Due to the abundant wind energy resources close to the airport [31], deployment of wind turbine systems in wind farms can generate sufficient renewable energy [32].…”

Section: Introductionmentioning

confidence: 99%

Low-carbon transition in smart city with sustainable airport energy ecosystems and hydrogen-based renewable-grid-storage-flexibility

Zhou

2022

Energy Reviews

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Hydrogen As An Alternative Aviation Fuel—A Review

Kumar,

Suryan,

Manju

2024

Energy, Environment, and Sustainability

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Economic and environmental impact assessments of hybridized aircraft engines with hydrogen and other fuels

Cited by 15 publications

References 18 publications

Working process model development of the gas turbine engine combustor fueling on methanol

Working process model development of the gas turbine engine combustor fueling on methanol

Low-carbon transition in smart city with sustainable airport energy ecosystems and hydrogen-based renewable-grid-storage-flexibility

Hydrogen As An Alternative Aviation Fuel—A Review

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