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1

ICAO aviation occurrence categories significantly affecting aviation safety in Poland from 2008 to 2015

Głowacki P., Balicki W.

Zeszyty Naukowe. Transport / Politechnika Śląska

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2017

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z. 94

47--56

EN

Poland, as a member of the EU, is represented within the ICAO, by the European Aviation Safety Agency. However, this does not relieve our country from the responsibility of developing a state safety programme (SSP). The need to set up such a programme, which has to be specific to every country involved in aviation operation, was introduced by the ICAO’s Annex 19. One of the important points in Annex 19 is: “5.2.1 Each State shall establish and maintain a safety database to facilitate the effective analysis of information on actual or potential safety deficiencies obtained, including that from its incident reporting systems, and to determine any actions required for the enhancement of safety”. The Polish Civil Aviation Authority, along with other databases, manages the European Coordination Centre for Aviation Incident Reporting Systems (ECCAIRS). The authors (who are specialists dealing with exploitation processes in aviation) have conducted a laborious processing of the data contained in the ECCAIRS database, analysing them based on various criteria: aviation occurrence categories (as defined by the ICAO), phases of flight for different airports in Poland etc. Aircraft with an maximum take-off mass (MTOM) 5,700 kg (commercial aviation) were considered separately. It was found that the most events are those that relate to power plant (SCF-PP) airframes and related system (SCF-NP) failures, followed by collisions with birds (BIRD), events related to airports (ADRM) and events related to the required separation of aircraft (MAC). For lighter aircraft, the dominant categories are ARC, CTOL, GTOW and LOC-I events. The article presents a proposed method for predicting the number of events, determining the alert levels for the next years and assuming a normal distribution (Gaussian). It is one of the first attempts to use actual data contained in the database of events on airports in Poland. The results of this analysis may support the decisions of supervisory authorities in the areas where security threats are most important.

2

Usefulness of the adopted method for the number of aviation occurrences prediction

Balicki W., Glowacki P.

Journal of KONES

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2017

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Vol. 24, No. 1

23--29

EN

Poland – according to ICAO requirements, is obliged to conduct analyses of the coefficients adopted to assess the level of safety in civil aviation. They are carried out on the basis of the data contained in the ECCAIRS database. The authors have processed the data contained in this database by analysing them using various criteria (ICAO aviation occurrence categories, flight phases, different airports) to test the methodology of the safety indicators values forecasting and setting their “warning levels”. Exceedance of these levels could be a signal for taking preventive action by the relevant competent aviation authorities. The proposed method is based on the assumption that the determined parameters are governed by normal distribution rules (Gaussian). Parameter values calculated based on real data from 2016 were compared with those predicted a year earlier. It was found that the factors for different events have increased significantly - above the calculated warning levels, particularly for general aviation. The results of this analysis may support competent aviation authorities' decisions in areas where safety risks are most critical.

3

Causes of the powerplants failures installed on Polish civil aviation aircraft

Balicki W., Głowacki P.

Combustion Engines

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2017

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R. 56, nr 1

110--121

EN

Currently in Poland about 2,500 different engine types are installed on the aircraft. In the years 2008-2016 powerplants failures caused nearly 600 aviation events. Aborted flight or emergency landing, especially in the case of aircraft powered by a single piston engine occurred. The objective of the article was to determine the failure causes and assessment of their impact on the flight safety. Engine faults were assigned to particular types of powerplants, for example turboshaft, piston, etc. Causes of the failures were examined, assigning ATA chapter to each of them. Also human factor was taken into account. According to the ICAO methodology, aviation safety engine systems essential for flight safety and theirs impact on the safety risk was determined. The results of the analyzes presented in this article are useful for managing the national aviation safety and supervising SMS in aviation organizations. The article shows that preventive measures to raise the level of aviation safety should be taken. This is the first comprehensive analysis of the powerplants failure causes and an evaluation of their influence on the level of aviation safety in Poland.

4

Wspomnienie prof. Stefana Szczecińskiego

Balicki W., Chachurski R., Głowacki P., Szczeciński J.

Prace Instytutu Lotnictwa

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2016

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Nr 3 (244)

318--320

PL

Profesor Stefan Szczeciński był wybitnym specjalistą w dziedzinie napędów lotniczych. W ciągu pracy zawodowej zajmował się silnikami spalinowymi: tłokowymi lotniczymi i trakcyjnymi oraz lotniczymi turbinowymi i rakietowymi. Był autorem i współautorem ponad 470 publikacji naukowych i technicznych, 28 pozycji książkowych, w tym koordynatorem i współautorem wydanej w latach 80-tych 9-tomowej serii pod ogólnym tytułem Napędy Lotnicze, stanowiącej podstawowe źródło informacji 0 silnikach lotniczych we wszystkich polskich uczelniach technicznych, a także dwutomowej monografii Lotnicze silniki turbinowe - konstrukcja - eksploatacja - diagnostyka wydanej w latach 2010-2012 w Instytucie Lotnictwa. Jedna z pierwszych Jego książek Lotnicze silniki turbinowe, konstrukcja i eksploatacja (1965) została w 1969 roku wydana (po przetłumaczeniu) na zlecenie NASA. Koordynował prace nad 3- tomowym podręcznikiem akademickim Lotnicze zespoły napędowe, przeznaczonym przede wszystkim dla studentów WAT, ale także dla innych uczelni prowadzących studia o specjalnościach lotniczych.

5

Możliwości rozwoju silników turbinowych z detonacyjną komorą spalania

Wolański P., Kalina P., Balicki W., Rowiński A., Perkowski W., Kawalec M., Łukasik B.

Prace Instytutu Lotnictwa

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2016

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Nr 3 (244)

202--214

PL

W artykule zaprezentowano obszerne badania zastosowania wirującej detonacji w silniku turbinowym. Stanowisko badawcze umożliwiało dostarczenie powietrza o wydatku 2,5 kg/s i ciśnieniu 2,5 bara z możliwością jego podgrzewania do ponad 100°C. Wykonano układ zasilania stanowiska paliwem podgrzewanym do 170°C oraz dodatkowo gazowym wodorem. Stanowisko badawcze wyposażone było w układy pomiarowe i sterowania: wydatkiem powietrza i paliwa oraz w system akwizycji danych w tym szybkozmiennych przebiegów cisnień w komorze spalania. Szeroko zakrojone badania wirującej detonacji realizowane były na otwartych i zdławionych komorach spalania oraz po dołączeniu ich do turbowałowego silnika GTD-350. Przedstawiono warunki uzyskania stabilnej detonacji. Stwierdzono, że w przypadku wirującej detonacji w silniku zasilanym gazowym wodorem sprawność cieplna może być podwyższona o 5-7 % w porównaniu do sprawności silnika z deflagracyjną komorą spalania.

EN

Extensive and complex studies of the application of continuously rotating detonation (CRD) to gas turbine are presented. Special installation of high pressure preheated air supply system was constructed which allows to supply air at rate of a few kg/s, preheated to more than 100°C and at initial pressure up to 2,5 bar. Supply system for Jet-A fuel which could be preheated to 170°C was also constructed. Additionally gaseous hydrogen supply system was added to the installation. Also measuring system for controlling air flow and measurements of detonation parameters was installed and data acquisition and control system implemented. Extensive research of conditions in which CRD could be established and supported in open flow detonation chambers, throttled chambers and finally in detonation chambers attached to the GTD-350 gas turbine engine where conducted. Condition for which stable detonation was achieved are presented. It was found that for conditions when the GTD-350 engine was supplied by gaseous hydrogen, thermal efficiency of the engine could be improved even by 5-7% as compare to the efficiency of the base engine.

6

Bilans energetyczny wirników dwuprzepływowych silników odrzutowych

Balicki W., Głowacki P., Szczeciński S., Kozakiewicz A.

Prace Instytutu Lotnictwa

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2016

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Nr 3 (244)

321--328

PL

W artykule przybliżono problematykę bilansowania procesów energetycznych turbinowych silników odrzutowych pracujących w lotniczych zespołach napędowych dla potrzeb analizy i oceny podstawowych parametrów pracy. Przedstawiono - rzadko podejmowany w literaturze specjalistycznej w i programach nauczania - problem ogromnych energii niezbędnych do napędu wentylatorów i sprężarek największych współczesnych dwuprzepływowych turbinowych silników odrzutowych wykorzystywanych powszechnie w lotnictwie dalekiego zasięgu. Na podstawie prostego modelu obliczeniowego oceniono wartości przenoszonych mocy oraz wpływ parametrów przepływowych i cech konstrukcyjnych silników na ich osiągi i sprawność efektywną. Moce potrzebne do napędu wentylatorów najwiekszych obecnie używanych silników sięgają 70 MW, a momenty przenoszone przez wary łaczące turbiny z wentylatorami mogą - w warunkach startowych - sięgać 70 000 Nm.

EN

The article presents problems of energy balancing processes in the turbine jet engines that work in aircraft propulsion units and its influence on analysis and evaluation of basic operating parameters. The paper describes the problem - which is rarely discussed in the specialist literature and in school curricula - of huge amounts of energy required to drive the fan and compressor of huge modern turbofan jet engines which are widely used in long-range aviation. On the basis of a simple calculation model, the value of transmitted power as well as the influence of flow parameters and the design characteristics of engines on their performance and efficiency have been estimated. Powers needed for propulsion of the fans at the biggest engines that are currently in use are up to 70 MW, while torques on shafts connecting turbines with fans can reach up to 70,000 Nm at take-off conditions.

7

Safety performance indicators assessment for small aircraft airframe systems

Balicki W., Głowacki P., Loroch L.

Journal of KONES

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2016

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Vol. 23, No. 2

31--38

EN

Safety performance indicators are the parameters used for monitoring and assessing safety performance. Such factors are determined based on available safety databases, collected on government level (in Poland Civil Aviation Authority) or by aircraft operators. Aircraft system failure during different flight phases can cause an accident or an incident. Polish Civil Aviation Authority between other data bases manages two important ones called: European Coordination Centre for Aviation Incident Reporting Systems (ECCAIRS) and Aircraft Continuing Airworthiness Monitoring (ACAM).General Aviation (GA) operates mainly aircraft with MTOM<5700 kg powered by the single piston engine. At present, reliability of GA aircraft systems in Poland is unknown. Increasing size of this fleet in Poland requires taking necessary measures in order to establish safety risks and safety performance targets for GA fleet. The authors have performed processing of the data included in available databases analysing airframe failures based on criteria like: phases of flight, ATA chapters concerning aircraft systems and the category of occurrence. The goal of this article is to present method of the current reliability of GA aircraft systems assessment. The results of this analysis can support the decisions of supervisory authorities in the areas where security threats are most important also can help production organizations in identification of the aircraft systems, which required design changes.

8

Report on the implementation of the POIG project „turbine engine with a detonation combustion chamber”

Kalina P., Wolański P., Balicki W., Perkowski W., Rowiński A.

Journal of KONES

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2016

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Vol. 23, No. 2

177--184

EN

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.

9

Assessment of the airframe systems affecting safety risks caused by large aircraft

Balicki W., Głowacki P., Kawalec M.

Journal of KONES

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2016

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Vol. 23, No. 1

39--46

EN

Hazard is a safety condition that could cause or be a part of unsafe aircraft operation. It also has an impact on aviation safety related to aircraft systems as well as services. Safety risk is a part of so-called safety management and is the predicted probability and severity of the outcomes of a hazard. Aircraft utilized by airlines and cargo operators which have MTOM >5700 kg are defined by authors as a large aircraft and have to be treated in their systems reliability analysis separately from small aircraft. Despite the fact that both types of aircraft categories events are included in the same databases - European Coordination Centre for Aviation Incident Reporting Systems (ECCAIRS) and Aircraft Continuing Airworthiness Monitoring (ACAM), due to different predominant systems failures could not be considered in the same way. The authors have performed processing of the data contained in available databases analysing large aircraft airframe systems faults, which were assigned to the specific ATA chapters. The most frequently occurring defects of the aircraft systems were identified. The goal of this article is to present a method of the current reliability of large aircraft systems assessment. Based on it, the authors are proposing a way of safety risk estimation and prediction of the safety levels for the next two years. The results of this analysis may support the decisions of supervisory authorities in the areas where security threats are most important. They can also help aircraft operators with identification of the aircraft systems, which require special attention.

10

Aircraft engines : analysis of reported systems failures in Polish aviation during years 2008-2015

Balicki W., Glowacki P.

Journal of KONES

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2016

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Vol. 23, No. 1

31--37

EN

Aircraft engine failure during different aircraft flight phases can cause accidents or incidents. ICAO Annex 19 requires from each state establishing the state safety program (SSP) and from the subordinate aviation organizations safety management system (SMS). Point 5.2.1 of Annex 19 instructs to establish safety database, which should be used for effective analysis of actual and potential safety deficiencies. Such analysis should lead to determining necessary measures in order to improve safety. Polish Civil Aviation Authority among other databases manages an important one called European Coordination Centre for Aviation Incident Reporting Systems (ECCAIRS). The authors have done a laborious processing of the data contained in that database analysing engine failures based on criteria like phases of flight, ATA chapters concerning powerplant and category of the occurrence. Separately, under consideration were taken engines installed on aircraft with an MTOM <5700 kg (mainly General Aviation) and for aircraft with MTOM > 5700 kg (commercial aviation). The article presents a proposed method of predicting the number of events, the alert levels for the next years and for ATA chapters’ determination, assuming a normal distribution (Gaussian). It is one of the first attempts to use the actual data contained in the database of events in Poland. The results of this analysis can support the decisions of supervisory authorities in the areas where security threats are most important.

11

Start-up and acceleration control of the turbine engine with the detonation combustion chamber

Balicki W.

Journal of KONES

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2015

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Vol. 22, No. 4

21--27

EN

This article presents the results of tests of helicopter turbine engine, where the classic combustion chamber was replaced with an innovative solution. In this chamber instead of the classic combustion deflagration, was generated a rotating detonation. Theoretical considerations expected to get a higher engine efficiency, because as the thermodynamic Fickett-Jacobs cycle, which can describe the working principle turbine engine detonation chamber, has a higher efficiency than a Brayton cycle, according to which the engines of conventional chamber are working. The appearance of detonation combustion was diagnosed basing on observation of the gas pressure flue in the chamber, using piezoelectric sensors. Before the detonation chamber was used in turbine engine, a series of problems on the various methods of initiation of detonation process and the procedures for controlling the flow rate into the chamber of air and fuel were solved. There was a test stand constructed, which used a helicopter turbine engine GTD-350, wherein the jugs combustion chamber was replaced with detonation chamber. A control system for the flow of fuel in the combustion chamber was developed: aviation kerosene Jet-A1 with addition of hydrogen. With its use obtained unfailing starts of chamber, also the engine running on the idle and on the flight range and accelerations at idle range to flight range. The possibility of the detonation combustion for a long time, especially in transient states - practically limited only by the capacity of fuel tanks – is the achievement of the research team.

12

Balancing energy processes in turbine engines

Balicki W., Głowacki P., Szczeciński S., Korczewski Z., Kozakiewicz A., Szczeciński J.

Polish Maritime Research

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2014

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nr 4

48--56

EN

The article discusses the issue of balancing energy processes in turbine engines in operation in aeronautic and marine propulsion systems with the aim to analyse and evaluate basic operating parameters. The first part presents the problem of enormous amounts of energy needed for driving fans and compressors of the largest contemporary turbofan engines commonly used in long-distance aviation. The amounts of the transmitted power and the effect of flow parameters and constructional properties of the engines on their performance and real efficiency are evaluated. The second part of the article, devoted to marine applications of turbine engines, presents the energy balance of the kinetic system of torque transmission from main engine turbines to screw propellers in the combined system of COGAG type. The physical model of energy conversion processes executed in this system is presented, along with the physical model of gasodynamic processes taking place in a separate driving turbine of a reversing engine. These models have made the basis for formulating balance equations, which then were used for analysing static and dynamic properties of the analysed type of propulsion, in particular in the aspect of mechanical loss evaluation in its kinematic system.

13

Testing of initiation of rotating detonation process in hydrogen - air mixtures

Balicki W., Irzycki A., Łukasik B., Snopkiewicz K.

Journal of KONES

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2012

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Vol. 19, No. 2

25-34

EN

The paper presents results of some research work done in the project, which aims to apply of an innovative combustion chamber to the turbine engine. Expected benefits of using of a new chamber in which classical deflagration type combustion process would be replaced with a detonation combustion type, arise from greater efficiency of FickettJacobs cycle, which corresponds to rotating detonation combustion, in comparison to "classical" Brayton cycle, characteristic of deflagration combustion. The presented task concerned fundamental research carried out on test bench designed and built at the Institute of Aviation in Warsaw. To initiate the detonation combustion in the fuel-air mixtures the ignition device of appropriately high energy is necessary. The released energy should be directed to the area where the mixture has proper constitution - preferably close to stoichiometric one. Four different ignition manners were examined in the course of research: electrical ignition system adapted from turbine engine (semiconductor spark plug), powder charge ignition (handgun cartridges), detonation primer ignition using pentryt, and high voltage discharge (plasma jet). The appearance of detonation type combustion was identified on the basis of combustion gas pressure run, measured using piezoelectric sensors at a frequency of 1 MHz.

14

Wloty powietrza turbinowych silników odrzutowych i ich wpływ na właściwości lotne samolotów oraz zagrozenia bezpieczeństwa latania

Balicki W., Głowacki P., Szczeciński S., Chachurski R., Kozakiewicz A., Szczeciński J.

Prace Instytutu Lotnictwa

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2011

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Nr 4 (213)

47-54

PL

W pracy starano się opisać kompleksowo specyfikę dopływu i przepływu powietrza przed wlotami i w kanałach wlotowych silników odrzutowych w różnych warunkach lotu oraz startu i lądowania samolotów. Zwrócono uwagę na zagrożenia uszkodzeń silników przez zderzenia łopatek wirników sprężarek (wentylatorów silników dwuprzepływowych) z ciałami ptaków, bryłkami lodu osadzającego się na krawędziach wlotu oraz "ciał obcych" zasysanych z nawierzchni lotniska podczas startu i lądowania z włączonym odwracaczem ciągu. Wskazano na wpływ ukształtowania kanałów wlotowych powietrza do silników samolotów bojowych na intensywność echa radarowego.

15

Realizacja ograniczeń dopuszczalnych parametrów pracy w strukturze układu automatycznego sterowania lotniczego silnika turbinowego

Balicki W.

Prace Instytutu Lotnictwa

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2011

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Nr 4 (213)

212-223

PL

W artykule opisano ograniczenia, którym muszą podlegać niektóre parametry pracy lotniczych silników turbinowych (m.in. prędkości obrotowe wirników, temperatura spalin) ze względu na wytrzymałość szczególnie wysilonych podzespołów: wirników i komór spalania. Przedstawiono przykłady realizacji tych ograniczeń przez układy automatycznego sterowania silników.

16

Przetwarzanie informacji zapisanych w rejestratorze eksploatacyjnym dla celów diagnozowania stanu lotniczego silnika turbinowego

Balicki W.

Prace Instytutu Lotnictwa

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2011

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Nr 4 (213)

235-244

PL

W artykule przedstawiono przykłady schematów algorytmów umożliwiających rozpoznawanie poszczególnych dynamicznych faz pracy silnika odrzutowego oraz ocenę ich przebiegu na podstawie wartości parametrów zapisanych w rejestratorze eksploatacyjnym.

17

Obserwowany stan i tendencje rozwojowe podstawowych cech i osiagów lotniczych silników turbinowych

Balicki W., Chachurski R., Kozakiewicz A., Szczeciński S.

Prace Instytutu Lotnictwa

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2011

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Nr 4 (213)

11-21

PL

Początek artykułu stanowi opis stanu wyjściowego podstawowych parametrów termodynamicznych, układów i cech konstrukcyjno - użytkowych turbinowych silników odrzutowych wdrażanych do lotnictwa w końcowej fazie II-ej Wojny Światowej i tuż po niej. Wskazano wpływ pomysłów konstrukcyjnych, nowych materiałów, nowych technologii wytwarzanych części i całych zespołów (modułów), oraz metod badawczych na wzrost osiągów silników. Zwrócono uwagę na ograniczenia postępu w tej dziedzinie względami finansowymi kosztów poznawczo - badawczych, dostępnością materiałów konstrukcyjnych, a także kadrami inżynierów i ich nauczycieli, z wymogiem bezpieczeństwa latania i ochrony środowiska.

18

Possibilities of the performance improvement of the aero- and marine propulsion units equipped with combustion piston engines

Balicki W., Korczewski Z., Szczeciński S.

Journal of Polish CIMAC

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2010

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Vol. 5, no 1

7-21

EN

Within the paper there have been presented the authors’ opinions concerning possibilities and needs of the performance optimization of the aero- and marine units powered by piston engines both of "classic" and contemporary construction. There have been also discussed the reserves contained within combustion piston engines which enable its performance improvement (the power and specific fuel consumption) as well as the fulfillment of the ecological requirements.

19

Comparison the piston air engine performance with aviation gasoline (Avgas) or the E-85 ecological fuel supply

Balicki W., Irzycki A., Snopkiewicz K.

Journal of KONES

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2010

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Vol. 17, No. 3

25-32

EN

The fuel presently used for feeding of aircraft piston engines (petrol including TEL) is characterized by "strong unfriendliness" for environment. Many research centres have been going on fuels investigation, which could substitute Avgas utilized in aviation. This is why are there no being in force for Europe standards defining the allowable emission of pollutions in exhaust gases of aircraft piston engines (equivalent to EURO - standards introduced for traction engines). The mixtures of gas o line and alcohols are tested as "alternative" aircraft fuels for spark ignition engines, and in case of Diesel engines - evenjet kerosene. During the research works on test bed carried out at Institute of Aviation the performance offour-stroke aircraft carburettor piston engine supplied by "classical" aircraft petrol and the E - 85 fuel (mixture of petrol and ethanol) were compared. Except for measuring the functional parameters of engine (rotational speed, torque, specific fuel consumption, pressures and temperatures) the emissions of gaseous pollutants incorporated in exhaust gas were measured and analyzed. The range of modifications of engine supply system - necessary to introduce in case of changing of fuel type within the tested engine -was worked up. There are foreseen comparative test of fuelling the engine with mixtures of petrol and alcohols in different proportions in the next phase of research works.

20

Wloty turbinowych silników odrzutowych - zagrożenia wirem wlotowym

Balicki W., Kawalec K., Pągowski Z., Szczeciński S., Chachurski R., Kozakiewicz A., Głowicki P.

Prace Instytutu Lotnictwa

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2009

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Nr 4 (199)

17-24

PL

W artykule przedstawiono warunki otoczenia wlotów silników odrzutowych sprzyjające powstaniu wiru wlotowego i jego zagrożeniach polegających na poderwaniu z ziemi tzw. „ciał obcych” i ich wrzuceniu do kanału przepływowego silnika. Znaleziono podobieństwo powstania wiru wlotowego do powstania trąb powietrznych w atmosferze ziemskiej. Przedstawiono sposoby „lotniskowe” ograniczające możliwość powstania wiru oraz przez odpowiednie kształtowanie wlotów. Przy okazji zwrócono uwagę na możliwość kształtowania samolotowych kanałów dolotowych do silników samolotów bojowych tak aby ograniczyć skutki zderzenia z ptactwem oraz namiarów radarowych nieprzyjaciela. Przytoczono charakterystyki stopnia wykorzystania ciśnienia spiętrze - nia we wlotach współczesnych samolotów bojowych. Zwracano uwagę na obraz fizykalny zjawisk zachodzących we wlotach i przed nimi.