Informacja

Drogi użytkowniku, aplikacja do prawidłowego działania wymaga obsługi JavaScript. Proszę włącz obsługę JavaScript w Twojej przeglądarce.

Wyszukujesz frazę "turbo" wg kryterium: Temat


Wyświetlanie 1-5 z 5
Tytuł:
A trial to improve fuel-efficiency rates of a turbo-charged engine
Autorzy:
Mysłowski, J.
Powiązania:
https://bibliotekanauki.pl/articles/243654.pdf
Data publikacji:
2008
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
engine
supercharging
turbo-compound
Opis:
The paper discusses theoretical bases and examples of practical application of the turbo-compound supercharging. The turbo-compound engines had been supposed to be used for propelling of buses, where it turned out that they were not fully meeting the expectations. This in particular applies to Volvo, where an axial-flow turbine was used as a power turbine. Such solution was given up in the construction of turbochargers for vehicles long time ago, for the benefit of turbines with radial flow (centripetal) due to much better dynamic rates of turbochargers with centripetal turbine and with centrifugal compressor. The solution with such turbocharger combined with the power axial-flow turbine impairs follow-up of the engine-turbocharger-power turbine set and hence the departure from such type of solution. As mentioned by the authors of the Volvo solution, it is much more suitable for aircraft engines (jet turbine engines) that operate at the maximum speed all the time, which is the most advantageous due to the efficiency of rotor machines. Application of the radial-flow turbine as a power turbine - as it is the case in the Scania engines -is much more advantageous solution. Results of simulation and operational tests of engines with such type of supercharging have been presented. A method of proceeding at determination of the engine operational parameters by means of simulation calculations has been described.
Źródło:
Journal of KONES; 2008, 15, 3; 375-380
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
PZL-10 turboshaft engine : system design review
Autorzy:
Czarnecki, Michał
Olsen, John
Ma, Ruixian
Powiązania:
https://bibliotekanauki.pl/articles/245142.pdf
Data publikacji:
2019
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
gas turbine
design
topology
turbo shaft
performance
Opis:
The PZL – 10-turboshaft gas turbine engine is straight derivative of GTD-10 turboshaft design by OKMB (Omsk Engine Design Bureau). Prototype engine first run take place in 1968. Selected engine is interested platform to modify due gas generator layout 6A+R-2, which is modern. For example axial compressor design from successful Klimov designs TB2-117 (10A-2-2) or TB3-117 (12A-2-2) become obsolete in favour to TB7-117B (5A+R-2-2). In comparison to competitive engines: Klimov TB3-117 (1974 – Mi-14/17/24), General Electric T-700 (1970 – UH60/AH64), Turbomeca Makila (1976 – H225M) the PZL-10 engine design is limited by asymmetric power turbine design layout. This layout is common to early turboshaft design such as Soloview D-25V (Mil-6 power plant). Presented article review base engine configuration (6A+R+2+1). Proposed modifications are divided into different variants in terms of design complexity. Simplest variant is limited to increase turbine inlet temperature (TIT) by safe margin. Advanced configuration replace engine layout to 5A+R+2-2 and increase engine compressor pressure ratio to 9.4:1. Upgraded configuration after modification offers increase of generated power by 28% and SFC reduction by 9% – validated by gas turbine performance model. Design proposal corresponds to a major trend of increasing available power for helicopter engines – Mi-8T to Mi-8MT – 46%, H225M – Makila 1A to 1A2 – 9%, Makila 1A2 to Makila 2-25%.
Źródło:
Journal of KONES; 2019, 26, 1; 23-29
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Full-electric, hybrid and turbo-electric technologies for future aircraft propulsion systems
Autorzy:
Łukasik, B.
Wiśniowski, W.
Powiązania:
https://bibliotekanauki.pl/articles/243487.pdf
Data publikacji:
2016
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
full electric
turbo-electric
hybrid systems
distributed propulsion systems
Opis:
Recently a huge progress in the field of electrical machines makes them more available for aviation. Assuming a big leap forward of electric technology in the near future, many research institutes around the World examine a revolutionary propulsion system which employs electrical machines. This idea can be a perfect response to a drastically growing air traffic and its demands about emission and fuel consumption reduction. There are already manufactured full electric, ultralight airplanes, which show that the technology is promising and future-proof. What is more it seems to be a key enabler for the development of the other technology that will influence the future of aircraft design and will allow introducing completely new airplane architectures. That is why Institute of Aviation in collaboration with The Ohio State University conducts investigation and analysis on feasibility of using such systems for aircraft propulsion. For this task a completely new tool based on Numerical Propulsion System Simulation (NPSS) environment is being developed. It will enable to analyse the electric devices conjugated with turbine engine as a whole propulsion system in the matter of its performance characteristics. The purpose of this paper is to present some of the most promising ideas and already accomplished analysis of different kinds of architectures. The analysis and optimization of the system, as well as cost effectiveness will be presented.
Źródło:
Journal of KONES; 2016, 23, 4; 305-310
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Operational verification of a ship main power system element choice : case study
Autorzy:
Adamkiewicz, Andrzej
Powiązania:
https://bibliotekanauki.pl/articles/245251.pdf
Data publikacji:
2019
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
ship main power system
turbo-charging system
operational parameters
main engine
ship propeller
Opis:
The article refers to results and conclusions on post-emergency repairs of a turbo-charging system of a DEUTZ engine of the SBV 8M 628 type of 1715 kW – the main power unit of a cement carrier. The failure of the turbocharger led to severing of a part of the exhaust outlet valve head. In order to determine the cause of the turbocharger fault, parametric identification of the reference state of the turbocharging system interacting with the ship main power engine has been carried out. The post-emergency servicing of the turbocharger comprised mounting a new blade rim of expansive instruments of smaller capacity than the so far used. Control measurement results of the power system after the replacement of the turbocharger turbine nozzle have been presented. Limitations of correct engine operation have been noted in the range of maximum load with continuous power (MCR). A range of corrective maintenance servicing of fuel equipment has been presented. Using the values of measured torque at the propeller shaft, incorrect interaction between the shaft and the main engine has been noted. A new propeller, adequate to the design operational parameters of the engine characteristics, has been chosen and mounted. The correctness of turbine expansive instrument replacement has been verified by correct interaction between the elements of the power system: propeller – main engine – turbocharging system. Thus, a wider range of economically acceptable ship operation has been obtained.
Źródło:
Journal of KONES; 2019, 26, 4; 7-14
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Review of design of high-pressure turbine
Autorzy:
Bugała, P.
Powiązania:
https://bibliotekanauki.pl/articles/246988.pdf
Data publikacji:
2017
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
preliminary design
turbomachinery
gas turbine
high-pressure turbine
HPT
projekt wstępny
turbo mechanizm
turbina gazowa
turbina wysokociśnieniowa
Opis:
The engine manufacturers adopt new measures in order to further improve the characteristics of a turbine engine. They pose new challenges to reduce a fuel consumption and an emission of pollution to the environment (including noise), but also keeping the highest level of reliability. Based on those considerations, current research in propulsion is conducted. Modern turbines are characterised by high inlet temperature. This has implications for engine efficiency, which is expressed with a change of mass, cross-section and fuel consumption. In this article, main trends in the development of turbine engines are presented. This analysis was carried out on the basis of Rolls-Royce engine data. The article presents literature review concerning the analytical methods of high-pressure turbines preliminary design. The aerodynamic design process is highly iterative, multidisciplinary and complex. Due to this, modern gas turbines need sophisticated tools in terms of aerodynamics, mechanical properties and materials. The article depicts simplified model of real turbine engine. As showed in the article, this model gives only a 10% error level in engine thrust value. The calculations may be used for preliminary engine analyses.
Źródło:
Journal of KONES; 2017, 24, 1; 67-76
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
    Wyświetlanie 1-5 z 5

    Ta witryna wykorzystuje pliki cookies do przechowywania informacji na Twoim komputerze. Pliki cookies stosujemy w celu świadczenia usług na najwyższym poziomie, w tym w sposób dostosowany do indywidualnych potrzeb. Korzystanie z witryny bez zmiany ustawień dotyczących cookies oznacza, że będą one zamieszczane w Twoim komputerze. W każdym momencie możesz dokonać zmiany ustawień dotyczących cookies