Evaluation of performance properties of two combustor turbofan engine

Jakubowski, Robert

doi:10.17531/ein.2015.4.13

Cited by 10 publications

(6 citation statements)

References 18 publications

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“…For flow tests, based on the literature review 31 , 33 and certification guidelines 2 , the conditions of motor power were selected for cruising speed at sea level ( m above sea level). The data obtained on temperatures and pressures were summarized in Table 1 .…”

Section: The Object Of Studymentioning

confidence: 99%

Analysis of the effects of simplifications on the state of loads in a centrifugal compressor

Bednarz

Sęp

Bartłomowicz

et al. 2022

Sci Rep

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This study aims to quantify and assess qualitatively the impact of modeling simplifications used to represent inertial and aerodynamic loads on the stresses and structural deformations of a centrifugal compressor in operation. The research object is the compressor of the high-pressure line of the DGEN 380 bypass turbine engine. Based on the virtual dynamometer WESTT CS/BV, the gas-dynamic parameters at the entrance to the centrifugal compressor and after the stage are determined. These values were used as initial parameters for numerical flow analysis. As part of the numerical strength analyses, a series of several load configurations were carried out: spin only, spin and inlet pressure normally applied on the working surface of the rotor blade, spin and outlet pressure normally applied on the working surface of the rotor blade, and one-way fluid–structure interaction analysis taking into account the aerodynamic loads with and without spinning. Based on the simulations, the level of similarity of a given load configuration with the last analysis, adopted as the reference, was determined. It was observed that in terms of the stress state, the rotational analysis taking into account the pressure on both sides of the blade gives satisfactory results, but the strain values are overestimated. The results obtained and the method of evaluation of compressor results can be used in research in the area of aviation, automotive, and refrigeration industries.

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Section: The Object Of Studymentioning

confidence: 99%

Analysis of the effects of simplifications on the state of loads in a centrifugal compressor

Bednarz

Sęp

Bartłomowicz

et al. 2022

Sci Rep

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“…The adopted engine operating parameters correspond to the demand for the thrust required for flight of the aircraft with its known aerodynamic characteristics, mass, flight velocity, and altitude. 34 The details of methodology and selection of engine operating parameters are presented in earlier authors’ articles in the series 22-28 and Ref. 35…”

Section: Introductionmentioning

confidence: 99%

Determination of the flight trajectory in terms of emission and fuel consumption minimization

Pawlak

Kuźniar

Majka

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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The present-day world is characterized by the intense development of air transport. However, along with it, significant problems appear. Among these problems, the most important are those relating to safety and negative impact of air transport on the environment. Air transport efficiency and profitability issues, although not critical, must also be taken into account because they decide about the intensity of development of this branch of transport. There are currently two large programs in Europe oriented at improving safety, environmental, and efficiency indicators. These are SESAR 2020 and Clean Sky 2, being a continuation of previous ones. One of the ways to reduce negative impact of air transport on the environment and improve its efficiency is to reduce fuel consumption and pollutants emissions resulting from fuel combustion. To find solutions with the abovementioned features, it is necessary to have sufficiently accurate models to estimate the amount of fuel consumed and the amount of pollutants emitted. Developing a sufficiently accurate model to determine fuel consumption and pollutants emission was performed. Due to the specificity of the missions carried out by passenger aircraft, the focus was on the cruise stage when aircraft flies at a constant altitude with a constant air speed. The result of the analysis was the development of methodology for fuel consumption and emission of main pollutants in cruise conditions. Specific fuel consumption is calculated for the thrust required for horizontal flight at cruising altitude. Emission indexes for CO, NOx, HC, and CO2 for the cruise have been determined based on known indexes for the landing and take-off cycle phase, after applying appropriate corrections. An illustration of the application of the developed methodology was the optimization of a medium-sized transport aircraft trajectory on a selected connection to determine a trajectory characterized by a minimum emission value taking into account weather conditions.

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“…Compressor blades are used as critical elements of the aircraft engine. This naming is connected to geometry, work conditions, and potential failures [5]. The blades from the first stage of the compressor are thin in comparison to the rest of the geometrical parameters [4].…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Material Data to the Numerical Strain-Life Analysis of the Compressor Blade Subjected to Resonance Vibrations

Bednarz¹

2020

Adv. Sci. Technol. Res. J.

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This paper presents the impact of selecting the fatigue material model on the numerically determined fatigue life of a compressor blade. In the work, the first stage compressor blade of the PZL-10W turbine engine was used. The research object contained a geometric notch with a known location and shape. In numerical studies, 8 fatigue estimation methods were used in the ε-N analysis (based on the Manson-Coffin-Basquin model). At the same time, three methods for estimating material constants associated with the cyclic hardening were employed. On the basis of the selected models, 24 sets of fatigue parameters were obtained, which were used in numerical studies. The numerical tests were carried out under resonant conditions with amplitudes of 1.5 and 1.8 mm. The numerical tests were confirmed by the experimental fatigue tests. As a result of the above-mentioned tests, the impact of selecting the material fatigue model and hardening model on the obtained results was determined and they were referred to the initiation of the crack with the length a = 0.2 mm (achieved during experimental studies). The obtained results will constitute the basis for further fatigue tests.

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Evaluation of performance properties of two combustor turbofan engine

Cited by 10 publications

References 18 publications

Analysis of the effects of simplifications on the state of loads in a centrifugal compressor

Analysis of the effects of simplifications on the state of loads in a centrifugal compressor

Determination of the flight trajectory in terms of emission and fuel consumption minimization

Evaluation of Material Data to the Numerical Strain-Life Analysis of the Compressor Blade Subjected to Resonance Vibrations

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