Autor: Kalina, P. - Prolib Integro

Skocz do pozycji: 1.

Tytuł:: Analiza wpływu parametrów samolotu na poziom hałasu mierzonego według przepisów FAR 36 APPENDIX G i rozdziału 10 założeń 16 założeń 16 konwencji ICAO
Analysis aircraft performance impact on noise level measured by FAR 36 APPENDIX G and annex 16 chapter 10 ICAO Convention
Autorzy:: Kalina, P.
Tematy:: parametry lotu samolotu
przepisy FAR 36 APPENDIX G
Konwencja ICAO
aircraft noise measurements
FAR 36 APPENDIX G
ICAO Convention; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Powiązania:: https://bibliotekanauki.pl/articles/213290.pdf Link otwiera się w nowym oknie
Opis:: W artykule przedstawiono wyniki pomiarów hałasu samolotów realizowanych przez Laboratorium Badań Akustycznych lnstytutu Lotnictwa w ciągu ostatnich lat wraz z oceną czułości metody liczenia poprawek na parametry mające wpływ na hałas samolotów. Wyniki analizy oparto na kilkudziesięciu pomiarach 5 typów samolotów produkcji polskiej.
The paper presents results of aircraft noise measurements carried out by Acoustic Research Laboratory of the Institute of Aviation within recent years with an evaluation of sensitivity calculation method of corrections to the parameters affecting the noise of airplanes. The results of the analysis were based on tens measurements of 5 types of Polish aircrafts.
Dostawca treści:: Biblioteka Nauki

Artykuł

na półce

Skocz do pozycji: 2.

Tytuł:: The influence of the size and shape of the “central body” of a combustion chamber on the toxicity of the exhaust gases in the Ursus 4390 engine
Autorzy:: Kalina, P.
Tematy:: combustion engines
toxicity
combustion chamber; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/246739.pdf Link otwiera się w nowym oknie
Opis:: This work is the third part of the articles published on the effects of the shape and position of the combustion chamber in piston compression diesel engines on the toxicity of exhaust gases. In two previous articles presented at the KONES 2015 conference, the impact of position of the combustion chamber in relation to position of the injector, and the influence of the shape of the chamber (diameter, depth, lip on the CO, HC and NOx emissions was analysed. In the current article, the shape of the “central body” in a combustion chamber is analysed. “Central body” is the protrusion located in the central part of a toroidal combustion chamber. Subsequent modifications to the basic combustion chamber consisted of reducing the size of this protrusion. The study involved four versions of combustion chambers. Modifications caused a slight decrease in the compression ratio, which could have an impact on the unambiguousness of the results, as the effect of changes in shape of the “central body”. However, to maintain a constant compression ratio would require a change in diameter or depth of the chamber cavity, which would obscure the obtained results with even greater impact. Emission tests in discussed study were performed according to ECE-R4. During the tests, the completion of the engine and the engine settings were not changed.
Dostawca treści:: Biblioteka Nauki

Artykuł

na półce

Skocz do pozycji: 3.

Tytuł:: Selection of turbocharger for the T3.251 engine
Autorzy:: Kalina, P.
Tematy:: transport
self-ignition engine
turbocharging
silnik samozapłonu
turbodoładowanie; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/247831.pdf Link otwiera się w nowym oknie
Opis:: In this research, a selection of turbocharger for atmospheric engine with automatic ignition T3.251 is described. This experimental engine was designed for driving small tractors. The purpose of turbocharging was to achieve a power of 45 kW. This atmospheric engine at 2250 rpm had power of 35 kW. In the first phase, the initial calculations of the turbocharger parameters were made according to the method proposed be Garret Company. The B65 turbocharger was selected for the study with flue gas exhaust in a multi-variant combination of turbines and compressors. Modifications were made to both turbine and compressor bodies as well as the size of their rotors. Altogether, eleven variants of the B-65 turbocharger were studied. The B65 turbochargers were fitted with an adjustable exhaust valve. By changing the spring preload, the supercharging pressure was adjusted. The research was carried out by performing the external characteristics and load characteristics of the engine under the same operating conditions and settings of the engine and injection equipment. The article presents the co-operation lines of an engine and superchargers using the characteristics of the discussed earlier compressors at Institute of Aviation. The effects of different turbocharger configurations on engine performance, power, fuel consumption, temperature and smoke emissions were also analysed. An analysis of the correct selection of turbochargers was performed.
Dostawca treści:: Biblioteka Nauki

Artykuł

na półce

Skocz do pozycji: 4.

Tytuł:: Pomiar hałasu zewnętrznego samolotów śmigłowych wg przepisów FAR 36 Appendix G i Rozdz. 10 Zał. 16 Konwencji ICAO
Autorzy:: Kalina, P.
Tematy:: awionika
hałas zewnętrzny
pomiar
przepisy FAR 36
Konwencja ICAO
avionics
rules to perform aircrofr
certification tests; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Powiązania:: https://bibliotekanauki.pl/articles/212486.pdf Link otwiera się w nowym oknie
Opis:: W referacie przedstawiono wymagania oraz zasady przeprowadzenia hałasowej próby certyfikacyjnej samolotów wg amerykańskich przepisów FAR 36 Appendix G oraz Rozdziału 10 Załącznika 16 Konwencji ICAO.
The paper presents the requirements and rules to perform aircraft noise certification tests according to the U.S. FAR 36 Appendix G and Chapter 10 of Annex 16 of the ICAO Convention.
Dostawca treści:: Biblioteka Nauki

Artykuł

na półce

Skocz do pozycji: 5.

Tytuł:: Pomiar hałasu zewnętrznego samolotów według przepisów FAR 36 Appendix G i rozdziału 10 założeń 16 Konwencji ICAO
External noise measurement of propeller airplanesller by FAR 36 Appendix and nnex 16 Chapter 10 of ICAO Convention
Autorzy:: Kalina, P.
Tematy:: pomiar hałasu
hałas zewnętrzny samolotów
przepisy FAR 36 APPENDIX G
Konwencja ICAO
hałas i czynnik ludzki w lotnictwie
external noise
noise and human factors in aviation
ICAO Convention; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Powiązania:: https://bibliotekanauki.pl/articles/213259.pdf Link otwiera się w nowym oknie
Opis:: W artykule przedstawiono wymagania oraz zasady przeprowadzenia hałasowej próby certyfikacyjnej samolotów wg amerykańskich przepisów FAR 36 Appendix G oraz Rozdzialu 10 Załącznika 16 Konwencji ICAO (Tom 1. Hałas Statków Powietrznych - Wydanie Trzecie -1993 r).
The paper presents requirements and rules to carrying out certification tests of aircraft noise according to U.S. regulations FAR 36 Appendix G and Annex 16 Chapter 10 of ICAO Convention (Volume 1. Noise of Aircrafts - 3-rd Edition -1993).
Dostawca treści:: Biblioteka Nauki

Artykuł

na półce

Skocz do pozycji: 6.

Tytuł:: The effect of location on the combustion chamber for the toxicity exhaust in self-ignition engine Ursus 4390
Autorzy:: Kalina, P.
Tematy:: piston engine
diesel
combustion chamber; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/247388.pdf Link otwiera się w nowym oknie
Opis:: As a part of the research work done on the engine URSUS 4390 which aimed at increasing power while reducing exhaust gas emissions, intake channels in the head, shape of the combustion chamber and compression ratio were modified. Proper injection equipment was selected and atomizer nozzles were constructed. In the first phase of the research, toroidal combustion chamber was located in factory design location. In the article there are presented results of exhaust gas emissions in selected operating points of engine URSUS 4390 for various positions of experimental combustion chamber. An innovative method of changing the position of the combustion chamber related to the piston axis was developed. A rotating insert with eccentrically extruded combustion chamber was mounted in piston axis. Rotation of the insert by a given angle resulted in displacement of combustion chamber around the axis of rotation. For each particular position of combustion chamber, concentration of toxic flue gas components and smoke index was measured at full load with rotational speed of 1400 and 2000 rpm. Proposed piston construction with rotating insert allowed to significantly decreasing duration of the research, which aimed at verification of combustion chamber relative location to injector and inlet nozzle. This way the necessity of construction of new sets of pistons and lapping them each time was avoided. As a result of the work, 11 locations of combustion chamber were tested. The study allowed picking the position of combustion chamber, which guarantees lowest emissions of toxic flue gas components.
Dostawca treści:: Biblioteka Nauki

Artykuł

na półce

Skocz do pozycji: 7.

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

Artykuł

na półce

Skocz do pozycji: 8.

Tytuł:: The influence of the shape of the combustion chamber on exhaust gases toxicity in T370 engine
Autorzy:: Kalina, P.
Kawalec, M.
Tematy:: diesel engine
combustion chamber
geometry
toxicity; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/243782.pdf Link otwiera się w nowym oknie
Opis:: An important issue in construction of combustion chamber in compression-ignition engines is proper selection of its shape and size. Both features are dependent on several factors such as fuel injector location and angle, spray atomizer selection (amount of holes, their diameter and angular position), location of inlet valve and air turbulence. By doing research on prototype engine T370, an analysis of influence of combustion chamber size and its modifications going towards lip construction on flue gas toxicity was done. The diameter and depth of combustion chamber was being changed while maintaining the same compression ratio. After that, a modification of tested combustion chambers was made by creating so called “lip”, which aim was to create a swirl of injected fuel in the vertical plane. To visualize the changes in swirl, a numerical analysis of fuel injection into combustion chamber was made. In discussed study, emission tests were performed according to ECE-R49. During the research six combustion chambers with diameters 60, 63 and 66 mm (and their modification) were investigated. Tests were performed for several types of injectors and different injection timing. However, for analysis of combustion chamber size the results are presented for the same injectors but with optimized injection timing.
Dostawca treści:: Biblioteka Nauki

Artykuł

na półce

Skocz do pozycji: 9.

Tytuł:: Zintegrowany silnik rakietowo-strumieniowy
Integrated rocket-ramjet engine
Autorzy:: Wolański, P.
Kalina, P.
Kawalec, M.
Tematy:: silnik rakietowo-strumieniowy
spalanie detonacyjne
wirująca detonacja
rocket-ramjet engine
rotating detonation
detonative combustion; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Powiązania:: https://bibliotekanauki.pl/articles/213011.pdf Link otwiera się w nowym oknie
Opis:: W artykule przedstawiono unikatową koncepcję budowy zintegrowanego silnika rakietowostrumieniowego. Proponowany system napędowy łączy różne tryby pracy tj.: rakietowy, rakietowo-strumieniowy, strumieniowy. Odpowiedni tryb pracy jest włączany w zależności od warunków lotu i realizowanej misji w celu optymalnego wykorzystania zalet poszczególnych układów wytwarzających siłę ciągu. Silnik rakietowy służy do przyspieszenia obiektu do prędkości okołodźwiekowej. Dla zakresu prędkości 1-2 Ma napęd przechodzi w tryb rakietowo-strumieniowy. Następnie układ napędowy przechodzi stopniowo na napęd strumieniowy. Silnik wyposażono w pierścieniową komorę spalania wykorzystującą efekt wirującej detonacji. Silnik taki ma prostą i zwartą konstrukcję dzięki wyeliminowaniu ciężkiego i skomplikowanego zespołu silnika turbinowego.
The article presents a unique concept for the construction of integrated rocket-ramjet engine. The proposed power system combines following operation modes of engine: rocket, rocket-ramjet and ramjet. The appropriate mode of operation is activated depending on flight conditions and undertaken mission in order to optimal utilization of advantages of particular thrust generating systems. Rocket engine is used to accelerate an object to the circum-sound speed. For object speed in range of 1 to 2 Ma the drive changes mode of operation to rocket-ramjet one. Then the driving system gradually undergoes to ramjet mode. Engine is equipped with toroidal combustion chamber which uses effect of rotating detonation. Thanks to elimination of heavy and complex turbine engine assembly the presented engine is distinguished by simple and compact structure.
Dostawca treści:: Biblioteka Nauki

Artykuł

na półce

Skocz do pozycji: 10.

Tytuł:: Impact of low-temperature corona discharges on gaseous pollutants level in diesel engines exhaust gas
Autorzy:: Irzycki, A.
Kalina, P.
Snopkiewicz, K.
Tematy:: exhaust gas
plasma reactor
emissions of gaseous toxins
experimental study; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/246916.pdf Link otwiera się w nowym oknie
Opis:: This publication presents the results of research on level changes of gaseous pollutants contained in the exhaust gas in the consequence of applying of equipment taking advantage of low-temperature corona discharges. Not only influence of different plasma reactor configurations on the emission of toxins have been evaluated, but also on the main parameters of the engine under test and exhaust gas cleaning efficiency as well. The device supplied by DC voltage of 10-15 kV the operating value generated a low-temperature corona discharge in the especially formed electrostatic field. The devices were located behind the exhaust manifold of Diesel engine then operated in the high temperature zone of exhaust. The survey was realized in parallel with on-going research program at Institute of Aviation which has related to purification of Diesel engine's exhaust gas from particulates. The test results of emission of toxins obtained using the flat-arrangement and the axial-symmetric reactor systems were compared and discussed. The multi-variant designs of axial-symmetric device allowed the purposeful formation of favourable shape and intensity of electrostatic field and values of current, which induced the corona discharge. This activity has created better research capabilities for different geometric configurations of the reactors, namely linear and angular location and size of deflecting electrodes, structure of blade assembly generating a corona discharge, matching of proper distance between deflecting electrodes and blades.
Dostawca treści:: Biblioteka Nauki

Artykuł

na półce

Informacja

Wyszukujesz frazę "Kalina, P." wg kryterium: Autor