Temat: aircraft turbine - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Diagnostic investigations of turbojet injectors
Autorzy:: Opara, T.
Zaremba, R.
Powiązania:: https://bibliotekanauki.pl/articles/241589.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft turbine engines
fuel injectors
fuel spray diagnostics
Opis:: The basic aim of injectors is to supply a specified amount of fuel to the turbine engine combustion chamber. The fuel should be atomized to the extent which enables its evaporation and helps to produce a homogenous mixture of fuel vapour and air, thus ensuring high efficiency of the combustion process. The article contains the review of methods and diagnostic equipment used in Aviation Overhaul Works (Lotnicze Zakady Remontowe) in assessing the suitability of turbine jet as well as turboprop and helicopter engines sprayers. Injectors are evaluated on the basis of their fuel delivery Q(p) which determines the volume of fuel sprayed in the time unit, the spray cone angle (p) and the parameter J(p) which describes the asymmetry in the circumferential spray density distribution j(). These parameters are dependent both on structural characteristics of the sprayers as well as on fuel delivery pressure p in the fuel supply pipe. In the standard diagnostic stations, the measurement of fuel delivery Q(p) is carried out only for the two fuel supply pressures, corresponding to the extreme engine ranges, that is the rotational speed of the idle running nbj and maximum rotational speed nmax. Injectors undergo the leak test at the fuel pressure 5 to 10 times bigger than the nominal value. Tolerances adopted by the producers for the measured parameters characterizing the injectors are also presented.
Źródło:: Journal of KONES; 2013, 20, 1; 247-254
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Diagnostic model of aircraft turbine engine governor pump
Autorzy:: Ohanian, Ihor
Yepifanov, Sergiy
Powiązania:: https://bibliotekanauki.pl/articles/36455739.pdf
Data publikacji:: 2022
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: aircraft turbine engine
hydromechanical governor
governor pump
diagnostics
model
influence coefficients
Opis:: This paper presents a mathematical model for a hydromechanical fuel governor pump, to be used in parametric diagnostics. The design and operation of the governor are described. The main requirements of the model are formulated, its structure is determined, corresponding to the specifics of the diagnostic task, and assumptions to make the model simpler are presented (single-dimensional flow and absence of heat exchange). The presented model consists of idealized elements with lumped parameters (such as pressure and mass consumption of the working fluid), accounting for the compressibility of the substance and the design arrangement of the governor (presence of mechanical rests, metering orifices of complex shapes, relay switchers, etc.). Equations of elements with lumped parameters, linked by hydraulic channels in one node, are presented. The model - a system of first-order differential-algebraic equations - is solved and the parameters of the governor pump are determined for different steady-state and transient operation modes. We compare our results to the requirements for the corresponding parameters outlined in the Engineering Specifications. The model is matched to the specifications by correcting setting parameters (tightening of elastic springs, areas of throttles, etc.), and a method of initial model linearization is developed. Based on the results, we conclude that our model can be used as a diagnostic algorithm for a governor pump, at the testing and development stages, during manufacturing, repair and maintenance.
Źródło:: Transactions on Aerospace Research; 2022, 2 (267); 80-95
0509-6669
2545-2835
Pojawia się w:: Transactions on Aerospace Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Possibilities for limiting aircraft turbine engine abrasive wear of interior duct elements
Możliwości ograniczania erozyjnego zużycia elementów składowych kanałów przepływowych lotniczych silników turbinowych
Autorzy:: Szczeciński, S.
Balicki, W.
Powiązania:: https://bibliotekanauki.pl/articles/213058.pdf
Data publikacji:: 2007
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: elementy składowe kanałów przepływowych
lotnicze silniki turbinowe
aircraft turbine
interior duct elements
Opis:: The paper describes the reasons for ingestion of contaminants into turbine engine interior with inlet air, resulting in lowered efficiency of main engine elements: compressor and turbine and further reduction of engine reliability and lifetime. The direct effect of the aerodrome (landing field) surrounding landscape on the type of contaminants ingested with the turbine engine inlet air and measures used to limit quantity of them are discussed in the paper. The inlet vortex is presented as the fundamental cause for turbine engine ingestion of contaminants from aerodrome surface, and analytic and experimental research methods used in investigation of this phenomena and preventive measures undertaken are also presented in the paper.
W opracowaniu opisano przyczyny przedostawania się zanieczyszczeń do wnętrza silników wraz z powietrzem wlotowym oraz wynikające stąd skutki w postaci zmniejszenia sprawności głównych zespołów: sprężarki i turbiny, a także ograniczenia niezawodności i trwałości silników. Omówiono wpływ bezpośredniego otoczenia lotnisk (lądowisk) na rodzaj zanieczyszczeń i sposoby ograniczania ilości zanieczyszczeń w strumieniu dolotowym silników turbinowych. Przedstawiono wir wlotowy jako podstawową przyczynę zasysania zanieczyszczeń z płyt lotniskowych przez silniki odrzutowe, a także analityczne i eksperymentalne metody badania tego zjawiska oraz sposoby utrudniajace jego powstawanie.
Źródło:: Prace Instytutu Lotnictwa; 2007, 4(191); 3-12
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Optical measurement of aircraft engine turbine blades
Autorzy:: Budzik, G.
Kubiak, K.
Rokicki, P.
Dziubek, T.
Nowotnik, A.
Matysiak, H.
Cygan, R.
Tutak, M.
Boś, P.
Powiązania:: https://bibliotekanauki.pl/articles/247470.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines turbine blades
optical measurements
coordinate measuring technique
Opis:: Manufacturing of aircraft engine turbine blades requires control of blade geometric parameters at different stages of technological process. Acceleration and automation of measurement process can affect the duration of the finished item production. Modern technologies for measurement of aircraft engine turbine blades are based on numerical machines - measurement process is based on processing of numerical data obtained by measurement using coordinate measuring machines. The paper presents the opportunity of automation of aircraft engine turbine blades measurements using scanner ATOS II Triple Scan with blue light source technology. Coordinate measuring technique allows to specify full methodology for designation of complex dimensions of physical objects and transform them into a computer program space of coordinate measuring devices. Presented paper includes capabilities of device used in the study to improve the measurement process in the technological and economical aspects. Another issue described in the paper is impact of measurement performance in automatic mode on the quality of performance – the numerical model of surface, from the standpoint of accuracy and number of collected data points in time. The paper includes an analysis of conditions related to the measurement works, such as the process of preparing the model, measurement equipment and data processing capacity. As the result methodology for automated scanning measurements of aircraft engine turbine blades will be presented.
Źródło:: Journal of KONES; 2013, 20, 2; 21-26
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Analysis of dimensional accuracy of blade of aircraft engine using a coordinate measuring machine
Autorzy:: Budzik, G
Kubiak, Krzysztof
Zaborniak, M.
Przeszłowski, Ł.
Dziubek, T.
Cygan, M.
Tutak, M.
Matysiak, H
Powiązania:: https://bibliotekanauki.pl/articles/244267.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines turbine blades
optical measurements
coordinate measuring technique
Opis:: Technological process of aircraft engine turbine blades requires control of blade geometric parameters. Innovation technologies for measurement of aircraft engine turbine blades are based on coordinate numerical machines – measurement process is based on processing of numerical data obtained by measurement using coordinate measuring machines. The paper presents the opportunity of analysis of dimensional accuracy of aircraft engine turbine blades measurements using coordinate measuring machine (CMM). Coordinate measuring machine allows specifying full methodology for designation of complex dimensions of physical objects (blade of aircraft engine) and transforming them into a computer program space of coordinate measuring devices. Presented paper includes capabilities of device used in the study to improve the measurement process and blades geometry analysis in the technological and economical aspects. Another issue described in the paper is impact of measurement performance in automatic mode on the quality of performance – the numerical model of geometry, from the standpoint of accuracy and number of collected data points in time. Measurements using a coordinate measuring machine are among the most accurate methods of measuring. The paper includes an analysis of conditions related to the measurement works, such as the process of preparing the model, measurement equipment and data processing capacity. As the result, methodology of (CMM) measurements of aircraft engine turbine blades will be presented.
Źródło:: Journal of KONES; 2014, 21, 2; 33-37
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Impact of the additives used in mineral jet fuels on the lubricating properties of synthetic fuels for turbine aircraft engines
Autorzy:: Dzięgielewski, W.
Kaźmierczak, U.
Kulczycki, A.
Ozimina, D.
Powiązania:: https://bibliotekanauki.pl/articles/245539.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: lubricity
fuels for turbine aircraft engines
synthetic components
additives
Opis:: Hydrocarbon containing synthetic fuels represent a promising alternative fuels. Despite different chemical compositions, their properties should be similar to properties of mineral fuels, as they are designed for the same drive units. The basic parameter related to the protection of the adequate service life of the power supply devices, including precision pairs, is lubricity. Lubricity depends on a number of factors, including these related to the chemical composition of fuel components and operating additives introduced into fuels in order to modify their properties. The preliminary results of research on the effect of additives: lubricating, anti-corrosion and anti-electrostatic once, on the lubricating properties of a synthetic fuel are shown in the paper. It was observed that there are relations between the content of additives and the dynamics of film formation. It is significant that this does not apply only to the lubricating additive, but also the additive, which protects the correct electrostatic balance by providing sufficiently high electrical conductivity of the fuel. This may indicate that the formation of a lubricating film remains in relation to the intensity of energy transport from the lubricated surface to the molecules of lubricating additives inside the film. The results shown in the paper preliminary confirm the hypothesis, that synthetic components of fuels change the concentration of ordered molecular structures (which are present in mineral part of fuels and which can be responsible for energy transport inside the lubricating film), what resulted in worse fuel ability to create protective film, and anti-electrostatic additive improves lubricity of blends of synthetic and mineral components.
Źródło:: Journal of KONES; 2018, 25, 2; 121-128
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Wpływ dodatku glikolu poli(etylenowego) na właściwości mas lejnych do wytwarzania form ceramicznych na osnowie SiC do zastosowań w odlewnictwie precyzyjnym części turbin lotniczych
Effect of polyethylene glycol addition on ceramic slurry properties used in investment casting
Autorzy:: Małek, M.
Wiśniewski, P.
Matysiak, H.
Sitek, R.
Kurzydłowski, K. J.
Powiązania:: https://bibliotekanauki.pl/articles/279094.pdf
Data publikacji:: 2014
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Inżynierii Materiałów Polimerowych i Barwników
Tematy:: masa ceramiczna
odlewanie precyzyjne
glikol polietylenowy
forma odlewnicza
spoiwo
turbina lotnicza
ceramic slurry
investment casting
polyethylene glycol
shell mould
binder
aircraft turbine
Opis:: W artykule przedstawiono wyniki badań właściwości technologicznych mas ceramicznych na osnowie SiC mogących znaleźć zastosowanie do produkcji form odlewniczych do odlewania precyzyjnego części turbin lotniczych. Zawiesiny ceramiczne z SiC o stężeniu 65% otrzymano w mieszadle mechanicznym z dodatkiem 6, 10, 15% wag. glikolu poli(etylenowego) spełniającego rolę spoiwa oraz upłynniacza. Przeprowadzono szereg badań materiałoznawczych dla proszku, polimeru oraz wytworzonych mas lejnych, w tym lepkość względną i dynamiczną, pomiar gęstości, pH oraz zanurzeniowy test płyty mosiężnej. Pomiary prowadzono przez 96 h.
The presented paper relate the application of SiC in manufacturing shell moulds for investment casting of aircraft turbine elements. The tested shell moulds were produced through the „dip and stucco” method. Ceramic slurries with a SiC concentration of 65% wt. were applied. The polyethylene glycol was added at different ranges (6, 10, 15% wt.) as a binder and a flow agent. The characterization of SiC powder was done by Scanning Electron Microscopy (SEM) and X-Ray Diffraction (XRD) methods. Properties of ceramic slurries such as: relative and dynamic viscosity, density, pH and plate weight were studied using a range of techniques. The results shows that slurries based on SiC and polyethylene glycol meet the investment casting requirements of aircraft turbine parts and have very promising properties.
Źródło:: Przetwórstwo Tworzyw; 2014, [R.] 20, nr 1 (157), 1 (157); 40-49
1429-0472
Pojawia się w:: Przetwórstwo Tworzyw
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Checking the Correctness of the Process of Brazing of the Honeycomb Seal to the Base by Ultrasonic Method
Autorzy:: Świerek, Agata
Krysztofik, Józef
Matczak, Wojciech
Niepokólczycki, Antoni
Powiązania:: https://bibliotekanauki.pl/articles/24201175.pdf
Data publikacji:: 2022
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: turbine aircraft engines
honeycomb seals
hard soldering
non-destructive testing
soldering correctness control
Opis:: This work is focused on the checking of the correctness of the brazing process of honeycomb seals to stationary elements of aircraft turbine engines. It describes this process, paying attention to the aspects that have a fundamental impact on whether the seal will be brazed to the base as required, or whether unacceptable areas of non-brazing will appear. The aim of the study was to check the possibility of using the ultrasonic method to check the correctness of the brazing process of honeycomb seals and to compare the tests carried out using this method with the mostly used visual tests. The research carried out as part of the work showed very well that there are reasons to use the ultrasonic defectoscopy method to test the correctness of the brazing process of honeycomb seals in the elements of aircraft engines. This method also makes it possible to automate the checking process, fully document it and objectively assess the correctness of the connection. The results obtained in the study provide a very good starting point for further research, the aim of which will be to implement the ultrasonic defectoscopy method for testing the correctness of brazing honeycomb seals into practice in industrial conditions.
Źródło:: Fatigue of Aircraft Structures; 2022, 14; 47--68
2081-7738
2300-7591
Pojawia się w:: Fatigue of Aircraft Structures
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Wyznaczanie emisji związków toksycznych w spalinach turbiny gazowej do zastosowań morskich w oparciu o charakterystyki emisji turbinowego silnika lotniczego
Determination of toxic exhaust emissions of a gas turbine for seagoing vessels based on a jet engine emission characteristic
Autorzy:: Pawlak, M.
Kuźniar, M.
Powiązania:: https://bibliotekanauki.pl/articles/316453.pdf
Data publikacji:: 2017
Wydawca:: Instytut Naukowo-Wydawniczy "SPATIUM"
Tematy:: turbina gazowa
silniki okrętowe
turbinowe silniki lotnicze
współczynnik emisji
porównanie silników
gas turbine
marine engines
turbine aircraft engine
emission factor
engine comparison
Opis:: W artykule opisano metodykę wyznaczenia emisji wybranych szkodliwych związków do atmosfery przez turbinę gazową napędzającą morską jednostkę pływającą. Opisano konstrukcję takiego silnika, porównano go do spokrewnionego z nim silnika odrzutowego. Powiązano parametry obiegu silników używając do tego formuł gazodynamicznych, a na tej podstawie dobrano współczynniki emisji NOx, CO, HC. Wyniki zebrano w tabelach i przedstawiono na wykresach. Rezultaty analizy zostały omówione i są podstawą do dalszych, bardziej szczegółowych symulacji i analiz.
The paper describes the methodology for determining the emission into the atmosphere of selected harmful compounds generated by a gas turbine that drives a seagoing vessel. The design of such an engine was described and compared to its related jet engine. The engine parameters were adjusted using gasodynamic formulas and the NOx, CO, HC emission coefficients were adjusted accordingly. The results are summarized in tables and graphed. The results of the analysis are discussed and are the basis for further, more detailed simulations and analyzes.
Źródło:: Autobusy : technika, eksploatacja, systemy transportowe; 2017, 18, 12; 345-350, CD
1509-5878
2450-7725
Pojawia się w:: Autobusy : technika, eksploatacja, systemy transportowe
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Estimating emissions of harmful exhaust components by aircraft engines during the takeoff and landing cycle in airport space
Szacowanie emisji toksycznych składników spalin wytwarzanych przez samoloty w cyklu startu i lądowania w przestrzeni portu lotniczego
Autorzy:: Głowacki, Paweł
Kalina, Piotr
Kawalec, Michal
Powiązania:: https://bibliotekanauki.pl/articles/36441042.pdf
Data publikacji:: 2021
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: ecology
aircraft turbine engine
engine exhaust
toxic exhaust gas components
nitrogen oxides
carbon monoxide
hydrocarbons
carbon dioxide
ekologia
lotniczy silnik turbinowy
spaliny silnika
toksyczne składniki spalin
tlenki azotu
tlenek węgla
węglowodory
dwutlenek węgla
Opis:: This articleexamines, based on the availableinformation and authors’ self-assessments, theenvironmental impact of turbine engine exhaust gases effect on the environment in the airport space during engines flight phases in the landing and takeoff cycle (LTO). The attention of aviation professionals is drawn to the fact that the amount of exhaust from the turbine engine is so significant that it may adversely change the ambient air at the airport. Consequently, increased emission level of carbon monoxide (CO), hydrocarbons (HC) during engine start-up and idle may pose a threat to the health of ramp staff. Also, high emission levels of nitrogen oxides (NO_x) during takeoff, climb, cruise and descent is not without importance for the environment around the airport space. The paper gives CO₂, HC, CO and NO_x emission estimations based on ICAO Engine Emission Data Bank and the number of passenger operations at a medium-sized airport. It also provides calculation results of aircraft CO₂, HC, CO and NO_x emission using average times of aircraft maneuvers taken from aircraft Flight Data Recorder (FDR) in the LTO cycle various aircraft types at the airport. The latter, based on actual maneuvering times, lead to significantly reduced estimates of toxic exhaust gas emission volumes.
W artykule przeanalizowano, w oparciu o dostępne informacje oraz ocenę autorów, wpływ gazów spalinowych z silników turbinowych na środowisko w przestrzeni wokół portu lotniczego podczas cyklu lądowania i startu (LTO) samolotów. Autorzy zwracają uwagę na fakt, że ilość spalin produkowanych przez silniki turbinowe jest na tyle znacząca, iż może niekorzystnie zmienić powietrze otaczające lotniska. Zwiększony poziom emisji tlenku węgla (CO) i węglowodorów (HC) podczas rozruchu silnika i na biegu jałowym może więc stanowić zagrożenie dla zdrowia pracowników obsługi naziemnej. Wysoki poziom emisji tlenków azotu (NO_x) podczas startu, wznoszenia, schodzenia i kołowania również nie jest obojętny dla środowiska wokół lotniska. W artykule najpierw przedstawiono szacunki emisji CO₂, HC, CO i NO_x w oparciu o normy ICAO oraz liczbę operacji pasażerskich na lotnisku średniej wielkości. Następnie obliczono szacunkowe emisje CO₂, HC, CO i NO_x na podstawie danych pobranych z rejestratora lotu (FDR) podczas cyklu LTO różnych typów statków powietrznych na lotnisku. Te drugie obliczenia, oparte na rzeczywistych czasach manewrowych, wskazują na znacznie niższe szacunkowe emisje toksycznych gazów w obrębie portu lotniczego.
Źródło:: Transactions on Aerospace Research; 2021, 2 (263); 63-70
0509-6669
2545-2835
Pojawia się w:: Transactions on Aerospace Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Numerical simulation of thermally loaded aircraft engine turbine blade covered with thermal barrier coating - TBC
Autorzy:: Łazarczyk, M.
Domański, R.
Powiązania:: https://bibliotekanauki.pl/articles/246553.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
turbine
TBC
coating
blade cooling
Opis:: The objective of this thesis is to present the impact of the turbine blade cooling on blade material temperature as well as to assess advantages and disadvantages of applied cooling method (TBC coating combined with internal cooling). To calculate the conjugated heat transfer analysis generating 3d model and mesh of the blade and its cooling was required. Model mesh was covered with boundary layer in order to properly simulate conditions near the blade walls and obtain accurate results. Calculated blade was put in the canal simulating hot combustion gasses flow. Geometry of model described above was created using Unigraphics NX5 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization was done in commercial pre--processor GAMBITŽ. Conjugated heat transfer analysis was conducted in program FLUENTŽ for two different cases, where the TBC material properties were changed. The goal of this thesis was to obtain temperature fields and distribution in the turbine blade airfoil and to evaluate if applied cooling is sufficient to cool down this thermally loaded part of the engine. Calculated results show that proposed blade heat protection with TBC and internal cooling canal is insufficient during steady state condition, especially on the blade leading and trailing edge. In these two locations, the TBC coating is overheated, and the high temperature level of blade material is unacceptable for materials used in jet engine turbine industry.
Źródło:: Journal of KONES; 2012, 19, 3; 271-277
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Impact of work of turbine adaptive engines for the natural environment
Autorzy:: Ćwik, D.
Kowalski, M.
Steżycki, P.
Powiązania:: https://bibliotekanauki.pl/articles/246614.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: noise of aircraft engines
environmental impact
jet engine turbine
emission of toxic compounds
aircraft engines
turbine jet engine
Opis:: The article describes the problem of the operation of turbine jet, adaptive engine work on the natural environment. In particular, the analysis of noise generated by turbine jet engines has been made. It points out possible directions of noise decrease with particular emphasis upon structural changes within the engines, the task of which is to reduce the noise mission. The example of the modernization is based upon the “bypass” type of one-flow turbine jet engine. The essay contains theoretical basis of calculation of the noise emission level and the results, which graphically indicate a relative level of noise of this type of engine depending upon the amount of discharged air and the diameter of the discharge nozzle and the radius, upon the basis of which the noise level is determined. This work also includes a comparison of the relative noise level of this type of engine with regard to one-flow turbine engine equipped with the function of air discharge to the environment and with regard to two-flow turbine jet engine equipped with air stream flow mixing device. The use of low-emission combustion chambers in the "bypass" turbine engine was indicated. This allowed addressing the problem of emissions of toxic exhaust components by this type of aircraft engines. At the same time, the dependence of this emission related to the mass of fuel used on the engine's thrust range was indicated. The article was concluded with a short summary.
Źródło:: Journal of KONES; 2018, 25, 4; 509-516
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: The influence of on-design bypass turbine engine parameters on multipurpose aircraft missions energy-consuming
Autorzy:: Wygonik, P.
Powiązania:: https://bibliotekanauki.pl/articles/243880.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: military gas turbine engine
military aircraft mission analysis
multipurpose aircraft
energy consuming
Opis:: In the article there was presented a quality assessment of parameters selection of bypass turbine engine for a multipurpose aircraft. It was assumed that the assessment criterion results from the energy-consumption of a flight. The criteria of energy-consumption range were defined as the relation of sum ofenergy supplied to the aircraft on the driven stages to the distance during a mission. The second criterion of unitary energy-consumption is defined as the relation of the movement energy-consumption to the product of the aircraft mass and the route during the elementary stage of the flight. With the use of the already worked out models of the power unit (bypass turbine engine with jet mixer and afterburner) of an aircraft (already known mass and aerodynamic characteristics) there were determined the ranges of thrust which are indispensable for a flight and available for the engine at each stage of the mission: take off, climb, subsonic and supersonic flight and turn with different overload factor. On the example of three chosen aircraft missions (Lo-Lo-Lo, Hi-Lo-Hi and Hi-Hi-Hi) the models of mission energy-consumption were developed. For the accepted change ranges of the comparative cycle parameters of the turbine engine the run of energy-consumption was tested. It was stated that for the assumed data the most energy-consuming mission is Lo-Lo-Lo, wherefore the increase of the compression and the rate of bypass reduces the energy-consumption of the mission.
Źródło:: Journal of KONES; 2010, 17, 1; 499-506
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Investigation of the dynamic properties of engine fan titanium rotor blades in a high manoeuvrability aircraft in FOD aspect
Autorzy:: Szczepanik, R.
Powiązania:: https://bibliotekanauki.pl/articles/244435.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft
combustion engines
turbine engines
engine diagnostic
blades
Opis:: A current problem concerning the use of military and civilian aircraft is the damage caused to turbine compressor blades by ‘foreign objects’. Here the term ‘foreign objects’ means small stones, pieces of metal, cement pitch, asphalt, etc., left on runways and taxiways. Foreign objects also include ice and iced lumps of snow as well as birds sucked into aircraft engine air ducts. All such objects pose a serious threat to proper engine operation. They are very harmful in two respects. One is the direct danger during flight when a bird or some other object is sucked into the engine. The other danger is in what might occur in later flights if the engine, especially the compressor and turbine blades, are not inspected for durability reassessment. This paper presents an analysis of how the size and distribution of defects on blade edges affect, the frequencies and fatigue strength of titanium blades in the first four stages of a high manoeuvrability jet engine fan (low pressure compressor). In particular, damaged high manoeuvrability aircraft fan stage rotor blades and measured natural vibration frequencies and logarithmic decrement of damping of high manoeuvrability aircraft fan titanium blades are presented in the paper.
Źródło:: Journal of KONES; 2013, 20, 2; 371-376
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Usage of Cold Forcing Method for a Gas Turbine Engine of Supersonic Transport
Autorzy:: Gutakovskis, Viktors
Gudakovskis, Vladimirs
Blumbergs, Ilmārs
Sarma, Elina
Powiązania:: https://bibliotekanauki.pl/articles/2201886.pdf
Data publikacji:: 2023
Wydawca:: Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:: aviation
GTE
gas turbine engine
supersonic
plane
aircraft
Opis:: The article discusses the current state of development of supersonic transport, analyses the main limitation of the use of gas turbine engines when flying at high supersonic flight speeds, proposes a method for expanding the range of GTE limitations in these flight modes of the aircraft, using cold forcing of the engine, conducts an analytical study of the effectiveness of this approach, proposes one of the possible devices for the implementation of cold forcing, the efficiency of an engine with cold forcing is shown, which may be of significant interest for the application of cold forcing methods in gas turbine engines of supersonic transport.
Źródło:: Advances in Science and Technology. Research Journal; 2023, 17, 1; 267--273
2299-8624
Pojawia się w:: Advances in Science and Technology. Research Journal
Dostawca treści:: Biblioteka Nauki

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