Numerical investigation of a GTM-140 turbojet
engine

Suchocki, Tomasz; Lampart, Piotr; Klonowicz, Piotr

doi:10.1515/eng-2015-0053

Cited by 9 publications

(13 citation statements)

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“…To resolve the major flow properties, the tetrahedral cell system is often created. It was previously proven that this meshing solution is successful in case of gas microturbines combustors [3][4][5][6][7]. This kind of element permits to fill a complex geometry, while keeping correct values of quality parameters (skewness, orthogonality and aspect ratio).…”

Section: Computational Domain Grid Systemmentioning

confidence: 99%

“…In case of combustion in furnace problem, radiation is not only the dominant energy transport mechanism but also one of the most complex problems. A Discrete Ordinates method [4,14] was used to evaluate the radiative heat transfer. In a typical combustion chamber, H 2 O and CO 2 are the main gaseous absorbers and emitters of radiant energy.…”

Section: Mathematical Modelmentioning

confidence: 99%

“…The work [4] describes a numerical simulation of the combustion chamber of the gas microturbine GTM-140. The authors used the RANS k-epsilon turbulence model, the non-premixed combustion model and the Discrete Ordinates radiation model.…”

Section: Introductionmentioning

confidence: 99%

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Numerical investigation of the internal flue gas recirculation system applied to methane powered gas microturbine combustor

Fąfara¹,

Modliński²

2021

Combustion Engines

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The gas microturbines gain significance in various industry sectors. One of their most crucial advantages is the capability of utilizing variety of fuels. At the same time, the emissions regulations become increasingly strict. This is why there is a need to look for a new technological solution to limit the emissions of selected substances, like carbon monoxide (CO) and nitrogen oxides (NOx). The internal recirculation of the flue gases is well known to limit the temperature peak and for the homogenization of the temperature field gradient in different combustion chambers. This paper presents a numerical investigation of a novel internal flue gas recirculation system applied to gas microturbine combustors. The ability to perform an internal exhaust gases recirculation by adding a combustor internal pipe system was verified numerically. This paper exposed the numerical investigation methods and obtained results. The study presents the concept and results performed on three cases of internal exhaust gases recirculation systems applied to a reference combustor. The work permitted to demonstrate numerically that it is possible to perform an autonomous exhaust gases recirculation inside gas microturbine combustor at a maximum global rate of 0.51%, and that the recirculation system has an impact on the combustion processes without specially modifying the combustor work parameters.

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Section: Computational Domain Grid Systemmentioning

confidence: 99%

Section: Mathematical Modelmentioning

confidence: 99%

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Numerical investigation of the internal flue gas recirculation system applied to methane powered gas microturbine combustor

Fąfara¹,

Modliński²

2021

Combustion Engines

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“…In [8] a steady-state mathematical modelling of the microturbojet Jetpol GTM120 was developed, and a comparison with laboratory test stand experimental data was carried out. In [9] a three-dimensional numerical simulation of combustion in Jetpol GTM140 miniature turbine engine was developed. Few works have been performed regarding the creation of a transient microturbine engine model and its validation with flight data.…”

Section: Introductionmentioning

confidence: 99%

Model-based dynamic performance simulation of a microturbine

Erario

Giorgi

Przysowa

2022

IOP Conf. Ser.: Mater. Sci. Eng.

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Microturbines can be used not only in models and education but also to propel UAVs. However, their wider adoption is limited by their relatively low efficiency and durability. Validated simulation models are required to monitor their performance, improve their lifetime, and design engine control systems. The aim of this study is to develop a numerical model of a micro gas turbine for engine performance predictions and prognostics. To build a reliable zero-dimensional model, the available compressor and turbine maps were scaled to available test bench data with the least-squares method, to meet the performance of the engine achieved during bench and flight tests. A steady-state aeroengine model was then developed and compared with experimental operating points. Selected flight data were then used as input for the transient engine model. The EGT temperature and the fuel flow were chosen as the two key parameters to validate the model, comparing the numerical predicted values with the correspondent experimental ones. The observed difference between the model and flight data was lower than 3% for both EGT and fuel flow.

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“…Over the years CFD techniques have proven useful in designing different component parts of a gas turbine [6,7], including the combustion chamber [8][9][10][11][12][13][14][15][16]. However, the numerical simulation of the complex phenomena which take www.etasr.com Mangra: Design and Numerical Analysis of a Micro Gas Turbine Combustion Chamber place inside the combustion chamber is still problematic.…”

Section: Introductionmentioning

confidence: 99%

Design and Numerical Analysis of a Micro Gas Turbine Combustion Chamber

Mangra

2020

Eng. Technol. Appl. Sci. Res.

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The interest in micro gas turbines has been steadily increasing. As a result, attention has been focused on obtaining optimal configurations for micro gas turbines depending on the applications in which they are used. This paper presents the CFD modeling results regarding an annular type combustion chamber, part of an 800N micro gas turbine, predestined to equip a small scale multifunctional airplane. Two configurations have been taken into consideration and 3D RANS numerical simulations have been conducted with the use of the commercial software ANSYS CFX. The liquid fuel droplets were modeled by the particle transport model, which tracks the particles in a Lagrangian way. An initial fuel droplet diameter of 500µm has been imposed. The numerical results obtained are encouraging. The flame was developed in the central area of the fire tube, its walls thus not being subjected to high temperatures. Also, the maximum temperatures were obtained in the primary zone of the fire tube. The temperature then decreased in the fire tube's secondary zone and dilution zone. The numerical results will be validated by conducting combustion tests on a testing rig which will be developed inside the institute's Combustion Chamber Laboratory.

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Numerical investigation of a GTM-140 turbojet engine

Cited by 9 publications

References 0 publications

Numerical investigation of the internal flue gas recirculation system applied to methane powered gas microturbine combustor

Numerical investigation of the internal flue gas recirculation system applied to methane powered gas microturbine combustor

Model-based dynamic performance simulation of a microturbine

Design and Numerical Analysis of a Micro Gas Turbine Combustion Chamber

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