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Gaz türbinlerinde diagnostik test metodları

Başlık çevirisi mevcut değil.

  1. Tez No: 46113
  2. Yazar: MEHMET AYAZ
  3. Danışmanlar: PROF.DR. OĞUZ BORAT
  4. Tez Türü: Yüksek Lisans
  5. Konular: Uçak Mühendisliği, Aircraft Engineering
  6. Anahtar Kelimeler: Belirtilmemiş.
  7. Yıl: 1995
  8. Dil: Türkçe
  9. Üniversite: İstanbul Teknik Üniversitesi
  10. Enstitü: Fen Bilimleri Enstitüsü
  11. Ana Bilim Dalı: Belirtilmemiş.
  12. Bilim Dalı: Belirtilmemiş.
  13. Sayfa Sayısı: 97

Özet

ÖZET Çalışan makinaların, çeşitli cihazların ve motorların verimli çalıştırılması, bakımlarının zamanında ve düzenli olarak yapılmasına bağlıdır. Ancak her ne kadar periyodik ve koruyucu bakımları yapılmasına rağmen, cihazlar, zamanla azalabilmektedir. Bu durumda arızanın teşhisi ve giderilme süreci önem kazanmaktadır. Arızanın teşhisine yönelik kantitatif verilerin çokluğu, bu süreci oldukça kısaltmaktadır. İlgili bakım klavuzlarında arızaların teşhisine yönelik çeşitli teknik bilgi ve şemalar bulunmasma rağmen, bazende özel tekniklerin alet ve takımların kullanılması, arıza teşhis sürecini kısaltmaktadır. Tezime konu olan gaz türbinlerinde diagnostik testlerin yapılması işte bu amaca yöneliktir. Yapılan çalışmalarda, önce arızasız bir GT'ni karekterize eden sinyal grafikleri (izler), FFT teknikleri uygulanmak sureti ile çıkarılmıştır. Daha sonra arızalı olan GT grafikleri elde edilmiştir. Grafiklerin karşılaştırılması ile arızası bilinen motorun frekansuıdaki değişme, deneysel olarak tesbit edilmiştir. Özellikle GT'lerinde yatak boşlukları, dişli kutusu ve dönel parçalan bulunan komponent arızalarının tesbiti bu yöntemle mümkün olmaktadır.

Özet (Çeviri)

DIAGNOSTIC TEST METHODS IN GAS TURBINE ENGINES SUMMARY The efficient operation of the any machine, equipment and engine is depend on to the timely and regular(periodic) maintenance. Although the periodic and preventation maintenance applied regularly to any equipment, some malfunctions may occurs. In this case the time for the determination of the malfunction and maintains period becomes very important. The higher the amount of the analytical information for the malfunction of the any equipment the lower the repairmen period will be. For this reason in this study we examined the possibility of the to increase the analytical information of the malfunction of the jet engines. Although there are different technical information and diagrams for the determination of a specific malfunction in the maintenance manual of the jet engines, special techniques and equipments will decrease the time for the determination of a malfunction. Here we studied the some diagnostic testing techniques for obtaining the necessary analytical information for the malfunction of the jet engine. In this thesis work after giving some information about the gas turbine, we examined the engine components which produce noise and vibration. These are as follow: a) In the air inlet, high speed air will be pass from inlet that produces some noises. b) The compressor blades, the impellers which increase the speed of the air and the vanes which increase the pressure of the air are the noise sources. c) A continous combustion will be occur by the injection of the fuel to the compressed air in the combustion chamber. This combustion process also produces a good amount af noise. d) When the hot gases reach to the turbine section, some vibration occurs in the turbine blades. These vibration will produce very high amount of noise by interacting with the hot gases in the motion. IXe) Exhaust unit is the last section which the hot gases will be pass. In the exhaust duct some level of noise will be produce by the living of the hot gases from the engine. f) Different component such as generator, cooling fan, oil and fuel pump on the reduction gear unit are other noise sources. g) The ball bearings that used for to support the main shaft is also a noise source. h) APU is also works as a compressor. 40 psi bleed air that is produced by the compressor unit is noise source. i) Also an APU gas turbine engine has very intensive level of automatic control units. The control valves are also a noise source. At the second stage of this work we introduced the periodic maintenance, dea. Apart from the malfunction of the engine in certain time period the engine noise should be measure and this will help to the preventative maintenance. The vibration and the noise that occur in the engine are related to each other. In the engine one of the important mechanical vibration will be the torsional vibration of the main shaft. Here we give the mathematical model of this torsional vibration. From this we calculate the natural frequencies. Later on the mathematical model for the lateral vibration of the main shaft is introduced. From this model the bending natural frequencies can be determined. These natural frequencies are very smaller than the excitation frequency of the main shaft, impellers and turbine blades. After that we introduced the fundamental definition and description about the diagnostic testing. In order to achieve high quality and reliability in the measured data the related standards are followed. In the experimental work ISO-5129 standards are used. In the thesis the experimental equipments and the materials that used in testing are examined in detail. The technical information about the microphone, the test bench for the diagnostic measurement, the oscilloscope for data acquisition, and other equipments are given. Some technical information about the engine which was used in the testing are as followed:Engine Type: GTCP85-98 CK/129H APU. Weigh: 284 Lb. Power: 50 SHP Bleed Air Flow Rate: 104 ppm. Bleed Air Pressure : 40 PSI. Engine Speed: 41500 RPM. EGT: 1150° F Noise Level: 120 dB. The experimental equipment that used in the noise measurement: * Quest brand Model 1800 sound level meter * HP brand Model 54600A two channel 8 bit oscilloscope * PC-486 DX computer * Matlab software In the experimental work we used Allied signal Aerospace product GTCP 85- 98CK / 129H series APU gas turbine. In the thesis some technical information about this turbine is given. The measurement is done as follow: In the test bench, a sound level meter was place on 0.5 m distance from the engine on a fix location. The signals from the microphone are amplify and reach to the digital oscilloscope through a coaxial cable. The oscilloscope was 8 bit and the RS 232 cables was connected to a 486 DX PC. The oscilloscope store 4000 data points and transfer them to the PC. In the PC a mathematical software, Matlab was used to obtain FFT transformation and the spectral density graphics by using these 4000 data points. At first the spectral density (signature) of a normal working GT was obtained. Later a malfunction GT was tested. Alter comparing the spectral density of these to engine some differences was observed. Because these differences are due to the mechanical variance between the two engines, we can easily observed the effect of the malfunction to the spectral density graphics. According to the experimental result a shift at 10-50 Hz was observed in the spectral density curves due to the malfunction of the engine gear box. Very high level of sound occurs at 800 Hz and this should be due to the resonance motion of the hot gases in the engine. Because of the rotation speed of a gas turbine is very high, after the occurence of any malfunction of a rotating component the engine will go to out of order very quickly. Consequently it is very difficult to obtained XIenough information about the malfunction before the engine going to the out of order. The experimental work was completed in a close room. This result some reflection of the sound waves from the walls. Beside this the advantages of the system are as follow: - The diagnostic test techniques can be applied to the engine before remove it from aircraft. This will bring an important amount of time saving for the aircraft maintenance here the noise measurement system is portable and the data may store a magnetic recorder and process later on. - The measurement may repeated with certain period. After examined previously collected data with the new one the maintaince time schedule of the engine can be estimated very well. - We should remember that the gas turbine operates with 41500 RPM and any small amount of malfunction will result out of work in very sort time period. The approaches that developed in this study may applied to main jet engines and hydraulic pumps and systems. The following important points should be consider for a high quality experimental result: The reflection of the sound wave from the other object should be consider. For this purpose the experimental room should be very well design and the measurement should be repeated from several locations. The connection cable between the microphone, amplifier and data acquisition system should be very well consider. Otherwise very high level of electronic noise problem will be occur. The affect of the humidity, environmental temperature and atmospheric pressure on the experimental data should be consider in detail. The microphone for noise measurement should be calibrated periodically. Here we used a 8 bit data acquisition system. The data first store a digital oscilloscope and later transfer to a computer. But 12 bit or 16 bit a data acquistion system can be results much better data than we can obtain in this xnstudy. In briefly, the purpose of these diagnostic testing study is to predict the malfunction of the jet engine in advance in order to increase the reliability and decrease the maintaince and operation cost. For this purpose some experimental techniques were developed and some analytical diagnostic data were collected. xni

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