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1

Selection of turbocharger for the T3.251 engine

Kalina P.

Journal of KONES

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2018

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Vol. 25, No. 1

191--196

EN

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.

2

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

|

2016

|

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.

3

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

Kalina P.

Journal of KONES

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2016

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Vol. 23, No. 2

171--176

EN

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.

4

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.

5

The influence of the shape of the combustion chamber on exhaust gases toxicity in T370 engine

Kalina P., Kawalec M.

Journal of KONES

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2015

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Vol. 22, No. 2

104--108

EN

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.

6

The effect of location on the combustion chamber for the toxicity exhaust in self-ignition engine Ursus 4390

Kalina P.

Journal of KONES

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2015

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Vol. 22, No. 2

97--102

EN

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.

7

SOKiK zmienił zdanie w sprawie przyłączy

Kalina P.

Wodociągi - Kanalizacja

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2014

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nr 11

32--33

8

Nowe obowiązki przedsiębiorstw wod-kan

Kalina P.

Wodociągi - Kanalizacja

|

2014

|

nr 10

26--27

9

Książki obiektów budowlanych dla sieci wod-kan

Kalina P.

Wodociągi - Kanalizacja

|

2014

|

nr 5

48--49

10

Zintegrowany silnik rakietowo-strumieniowy

Wolański P., Kalina P., Kawalec M.

Prace Instytutu Lotnictwa

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2014

|

Nr 1 (234) March 2014

104--108

PL

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.

EN

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.

11

Turbine engine with detonation combustion chamber in institute of aviation

Kalina P.

Journal of KONES

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2014

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Vol. 21, No. 1

119--124

EN

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.

12

Some problems resulting from powering of turbine engines by liquified petroleum gas (LPG)

Balicki Wł., Kalina P., Snopkiewicz K., Irzycki A.

Journal of KONES

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2013

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Vol. 20, No. 4

17--22

EN

There has been observed for several years a number of attempts to introduce for everyday use small power units which utilize turbine engine as propulsion unit (the U.S., Japan, and Europe). Efficiency increase of such devices is achieved by improving of turbine engine design as well as utilizing of exhaust gas thermal energy to heat the compressed air supplied to combustion chamber and, for example to heat usable water. Significant orientation of turbine engine improvements lead to the modernization of combustion processes by applying of gaseous fuels (such as compressed natural gas) or implementation of high-temperature catalytic combustion. The purpose of these changes reduction of hydrocarbons, carbon monoxide and nitrogen oxides emissions. In Propulsion Department of Aviation Institute a scientific project has been realized, in which the object of study was aircraft turbine engine powered by a liquid propane-butane mixture. The paper presents some results of engine tests carried out, especially concerning feeding system, special fuel system applied LPG pumping systems with the use of sliding-vane pump and by means of pressure reservoir and combustion process of LPG atomized with the use of original GTD-350 vortex injector, adapted for aviation kerosene Jet-A.

13

GTD-350 engine powered by LPG : research work

Kalina P., Niedziałek B., Gryglewski W., Irzycki A., Snopkiewicz K.

Journal of KONES

|

2013

|

Vol. 20, No. 3

209--214

EN

The paper presents results of comparative tests of exhaust gases toxicity of GTD-350 turboshaft engine powered by Liquefied Petroleum Gas (LPG) and conventional JET-A1 fuel. Structure of GTD-350 engine’s test bed was discussed. Because of explosion danger of LPG vapour the test stand was arranged in the open air. Paper comprises specification of LPG supply system, gas injector’s construction and visualization of LPG injection. The supply system was based on the newly constructed pressurized injectors. Required LPG operating pressure was obtained by pressurizing LPG tank using nitrogen and LPG-flow was controlled using needle valve. A series of photographs presents shape of fuel streams for new injector supplied by JET-A1 and LPG. Photos of flame torches for multi-hole and conical type injectors fuelled by LPG are inserted as well. A comparative study of carbon monoxide, nitrogen oxides, hydrocarbons and carbon dioxide as well as oxygen concentration for GTD-350 equipped with new injectors fuelled by LPG and standard supplied by Jet-A1 was carried out. The study comprised turbocharger speed range between 40 and 80% of NTS. The exhaust gas temperature comparison for above-mentioned configuration is presented as well. All data shown in presented figures are mean of 6 measurements. All completed tests were carried out for standard GTD-350 engine combustion chamber.

14

Procedures and treatments leading to reduction of toxic components emission in diesel engine's exhaust gas

Kalina P., Irzycki A., Snopkiewicz K.

Journal of KONES

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2012

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Vol. 19, No. 1

163-169

EN

The fight against global warming and Earth atmosphere pollution has been for years one of the most important tasks of governments and national economies of the European Union members. Abandonment of efforts leading to reduction mainly of carbon dioxide emission by heavy industry, electric power generation based on coal, passenger aviation and wheeled passenger transport will inevitably be leading to deterioration of health condition of our citizens. This article presents an overview of commonly used structural and technological treatments which have impact on reduction of toxic standardized exhaust pollutants in the surface transport, exemplified on SW 400 engine version of L2 / 3 and its turbocharged version 6CT 107 2/L2. The impact of: engine's adjustment parameters, catalytic afterburners, exhaust gas recirculation, modifications of injectors, turbochargers, supercharging air-cooling and particulates filter on carbon monoxide, hydrocarbons, nitrogen oxides and particulates emission was thoroughly examined. The parameters being compared were the results of toxicity tests according to ECE-R49 Regulation and a maximal smoke values on full-load characteristics. In conclusion, of the paper the limiting allowable values of toxic components emitted in Diesel engines exhaust gases in the following EU Emission Standards are presented.

15

Pomiar hałasu zewnętrznego samolotów według przepisów FAR 36 Appendix G i rozdziału 10 założeń 16 Konwencji ICAO

Kalina P.

Prace Instytutu Lotnictwa

|

2011

|

Nr 12 (221)

109-114

PL

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).

EN

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).

16

Analiza wpływu parametrów samolotu na poziom hałasu mierzonego według przepisów FAR 36 APPENDIX G i rozdziału 10 założeń 16 założeń 16 konwencji ICAO

Kalina P.

Prace Instytutu Lotnictwa

|

2011

|

Nr 12 (221)

115-120

PL

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.

EN

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.

17

Investigation of blade piston compressor

Kalina P., Wodyński P., Irzycki A., Snopkiewicz K.

Journal of KONES

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2011

|

Vol. 18, No. 3

143-148

EN

The paper presents the results of scientific research of the blade-type piston compressor which were conducted on the test rig built especially for this purpose. The construction concept of the compressor, design calculation of its main elements and tests of contact- and contactless sealing types were discussed in papers published at subsequent KONES-symposia 2009 and 2010. The results shown in present document are focused on studies of compressor having the piston equipped with labyrinth or contact seals. When testing on test bench, the intake air flow to the compressor as well as temperature and pressure of air compressed in the tank of 0.1 m3 were measured. Quick-changing pressure in the compression chamber and air temperature at the compressor's outlet were recorded and analyzed, also. The research was carried out for contact-type seals made of various materials which do not require lubrication and for contactless-type seals (labyrinth). In the course of studies the proper backlash between the piston and the cylinder wall was matched to ensure trouble-free operation of installation. The results of compressor power demand were presented in this article, too. This research work is performed under the framework program "Inicjatywa Technologiczna I" No 12218.

18

Impact of low-temperature corona discharges on gaseous pollutants level in diesel engine's exhaust gas

Irzycki A., Kalina P., Snopkiewicz K.

Journal of KONES

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2010

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Vol. 17, No. 2

145-152

EN

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.

19

Blade-type piston compressor investigation of seals

Kalina P., Chomczyk W., Irzycki A., Snopkiewicz K.

Journal of KONES

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2010

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Vol. 17, No. 1

199-204

EN

The paper presents the test results of selected seals applied in the blade-type piston compressor designed and realized in Propulsion Department of Institute of Aviation according to Patent No 6822 specification. Principle of operation of the compressor and the construction of test stand utilized to the seals testing were presented in the paper published in the Journal of KONES 2009. The special blade-type piston realizes a pendulous movement in the circular cylinder divided into two bulkheads. Each of bulkheads, fitted out with a set of bidirectional operating valves, creates by sequential opening and closing of them two compression chambers for one blade. Comprehensive tests of different kinds of seals were carried out on a single-compression machine driven by pneumatic actuator. The pressure rise vs. blade movement and drop of pressure when the piston was stayed at top dead centre were measured. The results of leak tightness of other structures of blade-type piston were analyzed as well and are subject to the following paper. The new design of piston relied on fitting-out of piston with side disc was prepared with intention of eliminating the loss of usable pressure in compression chamber, especially in area of top dead centre. The proposed design eliminated the leaks on the drive shaft and lateral seals, but not on the cylindrical surface of disco.

20

Pomiar hałasu zewnętrznego samolotów śmigłowych wg przepisów FAR 36 Appendix G i Rozdz. 10 Zał. 16 Konwencji ICAO

Kalina P.

Prace Instytutu Lotnictwa

|

2009

|

Nr 6 (201)

81-85

PL

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.

EN

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.