Temat: turbine engine - Prolib Integro

Skocz do pozycji: 1.

Tytuł:: Influence of inlet geometry on the efficiency of 1 MW steam turbine
Autorzy:: Koprowski, Arkadusz
Gotowski, Dominik
Rzadkowski, Romuald
Szczepanik, Ryszard
Tematy:: turbine engine
steam turbine
turbine inlet; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/950128.pdf Link otwiera się w nowym oknie
Opis:: The process of the design of the 1 MW steam turbine includes designing the stator and rotor blades, the steam turbine inlet and exit, the casing and the rotor. A turbine that operates at rotation speeds other than 3000 rpm requires a gearbox and generator with complex electronic software. This article analyses the efficiency of eight turbine variants, including seven inlet geometries and three stages of stator as well as an eight variant with one of the inlets, all three stages and an outlet. This article analyses the efficiency of 8 turbine variants, including four spiral inlet geometries and tree stages in a 1 MW steam turbine. In the article, inlets and 1st stator blades of various geometries were analysed to obtain maximal turbine efficiency. Changing the inlet spiral from one pipe to two pipes increased the turbine efficiency. The geometry of the blades and turbine inlets and outlet was carried out using Design Modeller. The blade mesh was prepared in TurboGrid and inlet in ANSYS Meshing.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Modelling the characteristics of axial compressor of variable flow passage geometry, working in the gas turbine engine system
Autorzy:: Wirkowski, P.
Tematy:: marine gas turbine engine; Pokaż więcej
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Powiązania:: https://bibliotekanauki.pl/articles/259564.pdf Link otwiera się w nowym oknie
Opis:: This paper concerns application of mathematical modelling methods to analyzing gas-dynamic processes in marine gas turbines. Influence of geometry changes in axial compressor flow passage on kinematical air flow characteristics, are presented. The elaborated mathematical model will make it possible to realize – in the future – simulative investigations of gas-dynamic processes taking place in a compressor fitted with controllable guide vanes.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Unstable operation of the turbine aircraft engine
Autorzy:: Kozakiewicz, A.
Kowalski, M.
Tematy:: turbine engine
engine dynamics
compressor stall; Pokaż więcej
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Powiązania:: https://bibliotekanauki.pl/articles/280192.pdf Link otwiera się w nowym oknie
Opis:: The article presents reasons for generating a non-uniform field of parameters in the compressor inlet of a turbine aircraft engine and its influence on the air jet kinematics at lowering fatigue strength of the compressor blade. Analysis of the engine torque in function of the engine operation time has been performed. Courses of the basic turbine engine operations parameters during compressor stall have been presented. The significant role of changes of the first torque derivative in relation to variation of the rotor acceleration in that assessment has been determined, which may be an important signal of the compressor surge occurring in the compressor. That parameter may be a signal for the control system to eliminate the negative phenomenon. The engine dynamics during the compressor surge has also been presented by developing the phase images of the engine operation basic parameters. The article includes analysis of dynamical changes in temperature of the combustion gases.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Report on the implementation of the POIG project „turbine engine with a detonation combustion chamber”
Autorzy:: Kalina, P.
Wolański, P.
Balicki, W.
Perkowski, W.
Rowiński, A.
Tematy:: combustion
rotating detonation
turbine engine; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/241703.pdf Link otwiera się w nowym oknie
Opis:: This article contains a description of the work carried out under the UDA-POIG 01.03.01-14-071/09-10 project titled “A turbine engine with a detonation chamber”. The work carried out during the project involved 14 construction, research and calculation tasks. Various research stands designed to analyse the process of mixture formation, initiation of detonation and research of rotating detonation in combustion chambers were constructed. Test stand for examining a turboshaft engine with detonation combustion chamber was built. Those test stands allowed powering the combustion chambers and the engine with both liquid and gaseous fuels, simultaneously or separately. At the same time, REFLOPS software, which could calculate the propagation of a detonation wave was created, and used in the design of further versions of combustion chambers. Data from the experiments was used to verify the calculations and models created in the mentioned software. GTD-350 engine was used as the base; the structure of which (combustion chamber situated outside the turbine-compressor unit) facilitated modifying the shape of the detonation combustion chamber. During the research, great emphasis was placed on the safety of researchers. Working with hydrogen in high temperatures and JET-A1 fuel, which was additionally heated, and the usage of the oxy-acetylene detonators forced extreme caution, and full compliance with developed procedures. The project was divided into 14 tasks that were often conducted simultaneously in a 20-person team implementing the project. The work was completed by performing comparative studies between conventional engine with deflagration combustion chamber, and modified engine with a detonation combustion chamber. During the completion of the project, it was the first working demonstrator engine with detonation combustion chamber in the world.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Turbine engine with detonation combustion chamber in institute of aviation
Autorzy:: Kalina, P.
Tematy:: turbine engine
rotating detonation
combustion; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/242747.pdf Link otwiera się w nowym oknie
Opis:: In Institute of Aviation from 2010 is realized a project POIG 2007-2014 “Turbine engine with detonation chamber.” The main target is to develop a turbine engine using a rotating detonation effect in the process of combustion the fuel. This article presents the most important stages leading to achieve the goals. As a facility test, we have chosen a turbo shaft engine GTD-350 characterized by the location of combustion chamber, which is outside the engine. This feature has helped in modernization the combustion chamber to adjust it to the detonation combustion. Works over the project has been started from the attempts to obtain a rotating detonation in the combustion chamber with a diameter of 500 mm powered by hydrogen. These researches have allowed the team to master the method of detonation initiation and methods for identifying the process of spinning detonation. In the same time works over the kerosene injection on the visualization bench has been begun. On this bench, we have mainly evaluated the extent and location of the fuel stream and the quality of the spray. Simultaneously the program to simulate the injection and the process of spinning detonation in actual geometries of different combustion chambers has been created. The process of initiation the detonation is discussed in the article on the example of detonator using ammo tutorial. Researches about combustion detonation with simultaneously reinforcement the combustion chamber with hydrogen and liquid fuel JET-A1 has also been discussed in this article. Presented research results includes pressure fuel waveforms in supply manifold along with the measurements of combustion pressure correlated with Air-Fuel Equivalence Ratio – lambda. Currently we are working over the integration of the combustion chamber of the engine GTD-350.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Microstructure analysis in the creep process of a gas turbine blade of the turbine engine
Autorzy:: Błachnio, J.
Kułaszka, A.
Ziętara, M.
Czyrska-Filemonowicz, A.
Tematy:: turbine engine
turbine blade
loads
microstructure
rafting; Pokaż więcej
Wydawca:: Polskie Towarzystwo Naukowe Silników Spalinowych
Powiązania:: https://bibliotekanauki.pl/articles/133291.pdf Link otwiera się w nowym oknie
Opis:: The technical condition of gas turbine blades of the turbine engine has a significant impact on the reliability and life span of the turbine and the entire engine. In order to assess the blades’ technical condition, a visual method, with the use of optoelectronic devices, is used. In order to verify this assessment, metallographic tests are conducted. The paper presents the results of microstructural tests of the turbine rotor blades made of nickel-based monocrystalline super alloys. The aim of these tests was to determine the consequences of impacting high exhaust gas temperature and stresses occurring during operation on the stability of the blade microstructure. The progress level of the blade microstructure changes in the post-operational stage for different sections towards the blade vertical axis and was compared with the blade microstructure on delivery made of the same super alloy. A varied degree of the microstructure degradation for different blade sections was shown. The changes typical of the high-temperature creep process – γ' phase directional growth (rafting), were observed only for the thinnest walls of the upper section of the turbine blade leaf.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Validation of selected presented method measured of length fatigue gap on compressor blades forming during resonant tests
Autorzy:: Kuźniar, M.
Bednarz, A.
Lichoń, D.
Witek, L.
Tematy:: crack propagation
gap
thermovision
turbine engine
blades; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/243027.pdf Link otwiera się w nowym oknie
Opis:: In this work, the validation of selected presented method measured of length fatigue gap was shown. The article describes three methods of determining fatigue gaps. The object of the study was the first stage compressor blade from aircraft engine. Blades have defects on the leading edge. This defect on the blade (as a result of the resonance vibration) was the origin point of the fatigue gap. Two of the methods, fluorescent and thermovision, were optical. The fluorescent method was a direct measurement, whereas direct-indirect thermography. The last of the presented methods was an analytical method, showing an algorithm based on amplitude-frequency characteristics. The advantages and disadvantages of these methods were compared. As a result of the analysis performed by the algorithm, there were specified patterns defining the dependence of change in crack length depending on the asymmetry of AF characteristics. The accuracy of the following methods and the results obtained for chord length were determined. Thanks to such use, these results have a utilitarian meaning. Such a compilation allowed us to evaluate the usefulness of particular measurement methods. Proposed methods of measuring the length of fatigue crack are used in experimental studies. It is also possible to implement them for research conducted during the operation of an aircraft engine.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Możliwości badania emisji związków szkodliwych w spalinach okrętowego turbinowego silnika spalinowego w warunkach eksploatacji
Possibility of emissions test harmful compounds in the exhaust marine turbine engine during operation
Autorzy:: Wirkowski, P.
Markowski, J.
Kniaziewicz, T.
Tematy:: okrętowy silnik turbinowy
silnik turbinowy
spaliny statków
emisja spalin
marine turbine engine
turbine engine
ship exhaust
exhaust emission; Pokaż więcej
Wydawca:: Instytut Naukowo-Wydawniczy "SPATIUM"
Powiązania:: https://bibliotekanauki.pl/articles/315237.pdf Link otwiera się w nowym oknie
Opis:: W artykule przedstawiono mechanizmy powstawania szkodliwych związków spalin silnika turbinowego oraz ogólnie opisano jak parametry pracy silnika turbinowego wpływają na emisję takich związków szkodliwych spalin jak tlenki azotu (NOx), tlenek węgla (CO), dwutlenek węgla (CO₂), niespalone węglowodory (HC) oraz cząstki stałe (PM). Zaprezentowane zostały wyniki wstępnych badań emisji związków szkodliwych spalin laboratoryjnego silnika turbinowego. Dokonano również analizy możliwości przeprowadzenia pomiarów stężeń związków szkodliwych w spalinach okrętowego turbinowego silnika spalinowego układu napędowego w warunkach jego eksploatacji na jednostce pływającej.
The article presents the mechanisms of formation of harmful compounds flue gas turbine engine and is generally described as the parameters of the turbine engine affect the emission of these compounds harmful exhaust emissions like nitrogen oxides (NOx), carbon monoxide (CO), carbon dioxide (CO₂), unburned hydrocarbons (HC) and particulate matter (PM). Presented preliminary results of emission of harmful exhaust emissions laboratory turbine engine. Also examined the possibility of carrying out measurements of concentrations of pollutants in the exhaust marine gas turbine engine propulsion system in terms of its operation on the vessel.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Aircraft fuel consumption and emissions during cruise, effect of the jet stream
Autorzy:: Głowacki, P.
Kawalec, M.
Tematy:: turbine engine
cruise
jet stream
exhaust emissions; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/242826.pdf Link otwiera się w nowym oknie
Opis:: Article presents the results of fuel consumption calculation during cruise compared to remaining aircraft flight phases. Based on fuel consumption, methodology of pollutants quantitative estimation emitted by turbine engines has been developed. Material provides evaluation results of aircraft CO2, CO and NOx effusion using fuel consumption data taken from aircraft Flight Data Recorder (FDR) during cruise of various aircraft types. Knowledge of the amount of aircraft emissions on high altitudes is very important for climatologists in order to understand eventual changes in the Earth atmosphere due to aviation activities. The authors would like to draw attention of the aviation professionals to the fact that aircraft fuel consumption during cruise; thereby amount of toxic content in the exhaust from the turbine engine is significantly higher especially during flights against jet stream. Thousands flights of two operators were processed using algorithms developed by authors. The article gives an example of fuel consumption and thereby CO2, CO and NOx emission estimation based on engine performance taken from their test cell results. Calculations were performed with the consideration of the factor for engines deterioration through operation time provided by its manufacturer.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Aviation : environmental threats
Autorzy:: Balicki, Wł.
Głowacki, P.
Szczeciński, S.
Chachurski, R.
Tematy:: turbine engine
exhaust gases
pollutant, ecology
environment
engine noise; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/244965.pdf Link otwiera się w nowym oknie
Opis:: Based on the available information and authors self-assessments, this article presents turbine engine exhaust gases effect on the environment, especially near to the aircraft and helicopters during their engines idle setting and take-offs. The concentration level of pollutants in gas turbine exhaust and its relation to the temperature and time of the combustion process is discussed. The article presents diffusion of the aircraft turbine engine exhaust in the airport area, focusing on aircraft take-off manoeuvre. The authors would like to draw attention of the aviation professionals to the fact that amount of exhaust from the turbine engine is so significant that may adversely change the ambient air near to the aircraft. Consequently, smaller amount of oxygen with increased level of carbon monoxide during engine start –up and idle can be a threat to the maintenance staff health. Also high emission level of the nitrogen oxides, especially during take-off and climb is indifferent for the environment. The paper gives an example of real fuel consumption and toxic gases emissions in the so-called landing and takeoff cycle (LTO) and during long-range flight. Turbine engines noise distribution and its intensity because of complex aerodynamic and thermodynamic processes is presented.
Dostawca treści:: Biblioteka Nauki

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