Wszystkie pola: jet engine - Katalog OPAC zbiorów

Skocz do pozycji: 1.

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: 2.

Tytuł:: Advantages of compressor downstream air partial bleed and supplying it downstream of the turbine in a turbojet engine
Autorzy:: Ćwik, D.
Kowalski, M.
Stężycki, P.
Powiązania:: https://bibliotekanauki.pl/articles/247092.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aviation engine operating parameters
jet engine designs
aviation engine air bleed
Opis:: The research article discusses the advantages of using compressor downstream air partial bleed and supplying it downstream of the turbine, which was applied in a prototype of a “bypass” turbojet engine. The objective of such a turbo engine structural solution was discussed along with its elements and principle of operation. Further part of the article determines the impact of such partial air bleed on the value of achieved basic operating parameters of the engine, i.e., unit thrust and unit power consumption. The presented attempt to compare these parameters with the parameters achieved for a turbojet, single flow engine is very important; in the first case without air bleed, and in the second, with air bleed to the environment. Further sections of the article compared these parameters relative to a turbojet, turbofan engine with a jet mixer. Such comparisons enabled to determine the actual benefits of using compressor downstream air partial bleed and supplying it downstream of the turbine, which may constitute an intermediate solution between single flow turbine engines and turbo fan engines. Wide possibilities for the application of such structural solutions were shown, which was summarised in the conclusions.
Źródło:: Journal of KONES; 2018, 25, 4; 501-508
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Noise emission level versus the structure of the aircraft turbine engine
Autorzy:: Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/241859.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: noise of aircraft engines
environmental impact of a jet engine turbine
Opis:: This article presents the problem of noise generated by turbine jet engines. 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 essay ends with short conclusions. In order to struggle with the air noise special "Environmental Protection Programmes" are prepared. Civil airports and military airports prepare new procedures for taking off and approaching planes as well as optimize the approach and take off airport flight zone corridors. Unfortunately, in the case of so big surfaces, acoustic screens would not bring desired effects, also due to costs.
Źródło:: Journal of KONES; 2012, 19, 4; 325-332
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Parametry określające wejście lotniczego silnika turbinowego w niestateczną pracę sprężarki
Parameters defining entry of the turbine engine into the unstable work of the compressor
Autorzy:: Kozakiewicz, A.
Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/213610.pdf
Data publikacji:: 2016
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: sprężarka osiowa
pompaż
lotnicze silniki turbinowe
portret fazowy
axial compressor
surge
turbine jet engine
phase portrait
Opis:: W artykule przedstawiono przyczyny generowania nierównomiernego pola parametrów na wejściu do sprężarki lotniczego silnika turbinowego i ich wpływ na kinematykę strumienia powietrza przy obniżającej się wytrzymałości zmęczeniowej łopatki sprężarkowej. Dokonano analizy przebiegu zmian momentu obrotowego wirnika jako funkcji czasu. Przedstawiono przebiegi podstawowych parametrów pracy silnika turbinowego podczas wchodzenia w zakres niestatecznej pracy. Określono istotną rolę w tej ocenie zmian pierwszej pochodnej momentu obrotowego w relacji do zmian przyspieszeń wirnika, która może być istotnym sygnałem o możliwości wystąpienia pompażu w sprężarce. Parametr ten może być sygnałem dla układu sterowania do eliminowania tego szkodliwego zjawiska. Przedstawiono także dynamikę silnika wspartą badaniem podczas pompażu poprzez opracowanie portretów fazowych podstawowych parametrów jego pracy. Artykuł zawiera analizę dynamiki zmian temperatury spalin.
This paper presents reasons for generating non uniform area of parameters on the entry to the compressor of the turbine engine and their influence on the air stream kinematics at the decreasing fatigue strength of the compressor blade. Analysis of the course of the torque rotor changes as the function of time was presented. Courses of basic parameters of the turbine engine work during the ingress into the range of unstable work were presented. The crucial role in this estimation of changes of the first differential of the torque in relation to changes in acceleration of the rotor which can be a significant signal of the possibility of surge occurrence in the compressor were defined. This parameter can be a signal for the control system to eliminate this bad phenomenon. The dynamics of the engine supported with the research during surge through the study of parameters'phase portraits of its work were also presented. The article contains analysis of the dynamics of changes in temperature of combustion gas.
Źródło:: Prace Instytutu Lotnictwa; 2016, 3 (244); 373-384
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Adaptive jet engines, advantages and application opportunities
Autorzy:: Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/245535.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
combustion engine
adaptation engine
parameters of the engine air
Opis:: The paper has been intended to shortly describe the design of an adaptive jet engine, commonly termed 'the bypass engine'. Examples have been presented of how the bleeding of air affects the most essential engine performance characteristics, i.e. thrust, specific fuel consumption, and efficiency. Pointed out are economic advantages (only slight) of the application of this design as compared to the one-pass turbojet engine with no bleed. Furthermore, considered are capabilities to adapt an engine design of the bypass type for a one-pass turbojet engine K-15 as one of several upgrade opportunities. Simulation-based computations have proved, however, that there are some limitations on the bleed air amount and initial engine operational range for the accomplishment of the idea from the standpoint of capabilities to maintain conditions for the compressor-turbine matching. Also, the effect of this type of air bleeding upon the engine running-up process and the change in the running-up time for this type of the upgraded engine has been shown. In the Recapitulation and Conclusions section a mention has been made on the amount of bleed air to be passed through external channels from behind the compressor to behind the turbine: the bleed air amount increases as the total rate of the air flow along the engine flow path increases. It means that better effects of applying this type of air bleeding processes are gained in large engines. Presented are also capabilities of further developments and applications.
Źródło:: Journal of KONES; 2011, 18, 3; 161-168
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Adaptive jet engines work analysis and control
Autorzy:: Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/242121.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: adaptation engine
parameters of the engine air
sensitivity of work cycle
Opis:: The paper describes major designs of adaptive jet engines as well as their structural and operational advantages. Attention is paid to actual thermodynamic cycles of such engines and energy balance of flows. Particular attention paid to a double-rotor engine designed by Pratt & Whitney, where a portion of air is bled from downstream of the compressor and then supplied to the area downstream the turbine when the engine is operated at its maximum performance (turbine bypass engine). Then attention is paid to actual thermodynamic cycles of such engines and energy balance of flows. It was shown that real working cycles of these engines represent figures with variable surface areas, which is the reason for the second name of these units - engines with variable thermodynamic cycle. It is explained how basic parameters of such engines affect sensitiveness of operating cycles and controllability. The analysis has been conducted separately for internal and external channel. The sensitivity analysis for the working cycle makes it possible to select parameters that are potentially controllable and adjustable. To sum up the foregoing deliberations one has to state that operation of turbojet adaptive engines is the topic that needs much more investigation. Even the design solution of the engine itself, although being really exciting and promising, is troublesome in the aspects of the design and process engineering, and will lead to a series of operation and maintenance problems.
Źródło:: Journal of KONES; 2011, 18, 2; 225-234
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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