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Zulham Hidayat
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Decision Sciences, Operations Research & Management Education Engineering Environmental Science Transportation

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KAJIAN PERENCANAAN KEBUTUHAN BRAKE ASSY PESAWAT BOEING 737-400 DI SALAH SATU PERUSAHAAN PENERBANGAN INDONESIA Zulham Hidayat
Langit Biru: Jurnal Ilmiah Aviasi Vol 12 No 2 (2019): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

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Abstract

Scheduled Air Operator ever face the situation where lack of spare part in the maintenance store. This situation will cause disruption of the aircraft operation and will contribute to delay. Delay will make the on time performance of the airline trend tend to decline. So the operator should has good maintenance system resulting of high reliability of aircraft component. PT. XXX has an Indonesian air operator certificate, operate 8 Boeing 737-400. There is a situation where maintenance store lack of spare part requested by line maintenance. Normally, Spare should be available any time when there is requested from line maintenance. This Spare part component is expensive and need specific time for procurement due to import process take a time. It is need good planning for procurement of the aircraft spare part. In this research will use the reliability method for deciding amount of spare part should be available in the store in one year. It will focus on the brake assembly component. In Boeing 737-400 there is 4 brakes installed on the aircraft.
MODIFIKASI EXTERNAL PUMP DRIVE L135M2905101 PADA PRESSURE SUPPLY SYSTEM HELIKOPTER AIRBUS EC-135 P3 SEBAGAI ALAT BANTU PERAWATAN DI HANGAR 3 SEKOLAH TINGGI PENERBANGAN INDONESIA Hanris Lukkas Adi Putra; Zulham Hidayat; Haryadi
Langit Biru: Jurnal Ilmiah Aviasi Vol 12 No 3 (2019): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

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Abstract

In maintenance process of Airbus Helicopter EC-135 P3 based on Master Servicing Manual there are several type of maintenance procedure which there are tasks like leakage test hydraulic power supply, pressure test, and bleeding. One of the tools used on this task is external pump drive. During this time the implementation of maintenance using tools from Airbus Helicopter Indonesia and there are some deficiency that is rotating speed does not reach 5145 rpm as needed hydraulic power system. Therefore, then the writer will modify the tool which has a rotating speed of 5145 rpm. General description for consideration external pump drive, the writer want to use a timing belt transmission system by utilizing accuracy when turning. The modification design stage that was undertaken was first determining the driving motor proceed with designing the timing belt, the third stage is making the internal gear drive the drive shaft, followed by the stages of making the timing belt transmission housing and determining the bearings. The results of this modification are expected to be beneficial for STPI especially Unit Perawatan Pesawat Udara to assists the process of leakage test, pressure test, and bleeding in the hydraulic power system
PERANCANGAN TURBIN AKSIAL SATU TINGKAT UNTUK MESIN TURBOJET BERBASIS TURBOCHARGER T70 Zulham Hidayat
Langit Biru: Jurnal Ilmiah Aviasi Vol 10 No 3 (2017): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

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Abstract

Turbocharger T70 has a type of radial turbine that has a value of 60% efficiency will be modified into a turbojet engine. To obtain a higher efficiency rating on the turbojet engine, the thesis is designed a one-stage axial turbine. This one-tiered axial turbine is expected to have an 87% efficiency and can supply power to a compressor of 120000 Watt and is also expected to be easy to manufacture . This one-tier axial turbine design method, drawn from various literatures. The design point taken in this design is the air mass (ṁ) 0.505kg / s, with the spin axis 1763.33rps. The total pressure on the turbine inlet is 3936 bar and the total temperature at the turbine inlet is 1260.417 K. The calculation result of the analysis shows the number of nozzle bar 49 and the number of rotor blades 35. The performance prediction on this one-tiered axle turbine uses Aeinley-Matieson method which yields efficiency value 87.3%. Turbine turbine blades and rotor turbine blades using Cascade software. The thickness distribution of the profile uses airfoil NACA 0012. The camber line on this 2 dimensional airfoil uses a circular arc type. Pada bilah turbin nosel dan bilah turbin rotor yang telah di bentuk selanjutnya dilakukakan analisis dengan menggunakan computational fluid dynamic (CFD). Dengan menggunakan CFD, efisiensi yang dihasilkan adalah 88.4 %, lebih besar dari prediksi performa turbin dengan menggunakan metode Aeiley-Matieson. Daya yang dihasilkan oleh turbin adalah 132436.74 Watt, sedangkan daya yang di butuhkan oleh kompresor adalah 119960.68 Watt.
ANALISIS KEBUTUHAN BEBAN PENDINGIN DENGAN METODE COOLING LOAD TEMPERATURE DIFFERENCE (CLTD) PADA RUANG LOBBY GEDUNG SIMULATOR SEKOLAH TINGGI PENERBANGAN INDONESIA Arief Susanto; Yenni Arnas; Zulham Hidayat
Langit Biru: Jurnal Ilmiah Aviasi Vol 10 No 3 (2017): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

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Abstract

Simulator Building is one of the buildings in Indonesia Civil Aviation Institute, which is used as supporting educational facilities. This simulator building has three floors and a lobby on the first floor which is used as the meeting room and reception area. On this building, there is already a centralized air conditioning type whose channels are distributed throughout the room in this building including a lobby room on the first floor. But, those air conditioning equipment is not working. Thus, it is causing the temperature in the lobby room calculated as 28°C - 30°C during the daylight. Those condition is exceeding the maximum thermal comfort threshold for tropics which is 22,8°C – 25,8°C. It is over the limit of maximum thermal comfort condition for the tropics, which is 22,8°C- 25,8°C. Therefore, it needs an air conditioner (AC) to keep the room temperature comfortable. in planning the installation of the eqquipment, we can analyze it by Cooling Load Temperature Difference (CLTD) calculation method for Indonesian comfort thermal zone which is generally 25oC ± 1oC on temperature and 55 % ± 10 % on relative air humidity
RANCANG BANGUN FUEL SYSTEM UNTUK TURBOCHARGER GAS TURBINE ENGINE DENGAN INDUCER DIAMETER 1,75 INCH DI HANGAR 01 TEKNIK PESAWAT UDARA SEKOLAH TINGGI PENERBANGAN INDONESIA Ridho Ramadhan; Wira Gauthama; Zulham Hidayat
Langit Biru: Jurnal Ilmiah Aviasi Vol 13 No 02 (2020): Langit Biru: Jurnal Ilmiah Aviasi Vol.13 No.2 [Juni 2020]
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (466.367 KB)

Abstract

B.Indonesia Turbocharger adalah sebuah kompresor sentrifugal yang mendapat daya dari turbin yang sumber tenaganya berasal dari gas buang kendaraan. Pada perancangan ini turbocharger digunakan sebagai pengganti dari fungsi compressor dan turbine[1]. Rancang bangun turbocharger gas turbine engine ini dibagi menjadi beberapa sistem antara lain; combustion chamber, oil system, fuel system, dan ignition system. Dari teori – teori yang ada pada referensi[2], penulis melakukan proses perancangan yang terdiri dari beberapa bahasan, antara lain menentukan bahan bakar yang akan digunakan, hose, valve dan nozzle. Bahan bakar yang digunakan dalam rancangan ini adalah LPG (Liquid Petroleum Gas)[3]. Hose dan valve yang digunakan pada rancangan ini menyesuaikan dengan debit fluida yaitu sebesar 6,89 × 10−3 ????3/????, kecepatan fluida sebesar 87,77 m/s, dan tekanan aliran fluida sebesar 238,88 psi. Nozle yang digunakan berdiameter 0,005 m. Dari perancangan fuel system yang penulis rancang dapat menyalurkan bahan bakar yang dibutuhkan agar dapat menghasilkan pembakaran yang optimal. B.English Turbocharger is a centrifugal compressor that gets power from turbines whose power source comes from vehicle exhaust gases. In this design the turbocharger is used instead of the compressor and turbine function. Refer to the References, the authors carry out the design process which consists of several topics, including determining the fuel to be used, hose, valve and nozzle. The fuel used in this design is LPG (Liquid Petroleum Gas). The hose and valve used in this design adjusts to the fluid flow of 6,89 × 10−3 ????3/????, the fluid velocity of 87,77 m/s, and the pressure of the fluid flow of 238,88 psi. The nozle used was 0,005 m in diameter. From the design of the fuel system that the author designed can deliver the fuel needed to produce optimal combustion.
Rancang Bangun Oil System untuk Turbocharger Gas Turbine Engine Dengan Inducer Diameter 1,75 Inch Noval Dwi Kurnianto; Wira Gauthama; Zulham Hidayat
Langit Biru: Jurnal Ilmiah Aviasi Vol 14 No 01 (2021): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.54147/langitbiru.v14i01.408

Abstract

Rancang bangun mesin turbin gas dimulai dengan mengidentifikasi beberapa komponen yang dibutuhkan dalam membangun sebuah mesin turbin gas. Turbocharger yang terdiri dari kompresor dan turbin sebagai penyusun utama komponen ini diambil untuk dijadikan Kompresor dan turbin mesin turbin gas yang juga merupakan unsur utama dalam sebuah mesin turbin gas. Agar sebuah mesin turbin gas dapat beroperasi maka perlu dirancang beberapa system pendukung seperti Oil System, Fuel System, Ignation System, Combustion Chamber dan beberapa system yang lain. Pada perancangan ini, penulis mendapat bagian dalam perancangan Sistem pelumas (Oil System) dimana tantangan yang dihadapi adalah mendapatkan jenis oil yang tepat untuk mesin turbin gas yang akan dibangun. Adapun rumusan masalah dalam perancangan system pelumas ini antara lain bagaimana menentukan viskositas pelumas yang digunakan, menghitung critical pressure bearing, menghitung jumlah pelumas yang digunakan, menghitung head pompa dan menghitung kapasitas reservoir yang digunakan. Output akhir yang dihasilkan dari perancangan ini adalah suplai oli yang mampu untuk melumasi shaft bearing pada turbocharger sehingga tidak terjadi overheating yang menyebabkan keausan serta metal to metal contact. Dari hasil perhitungan, didapatkan tekanan oli sebesar 37 psi yang diperlukan untuk melumasi shaft bearing pada turbocharger. Dan dihasilkan pembakaran yang continuous.
RANCANG BANGUN FUEL SYSTEM UNTUK TURBOCHARGER GAS TURBINE ENGINE DENGAN INDUCER DIAMETER 1,75 INCH DI HANGAR 01 TEKNIK PESAWAT UDARA SEKOLAH TINGGI PENERBANGAN INDONESIA Ridho Ramadhan; Wira Gauthama; Zulham Hidayat
Langit Biru: Jurnal Ilmiah Aviasi Vol 13 No 02 (2020): Langit Biru: Jurnal Ilmiah Aviasi Vol.13 No.2 [Juni 2020]
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

B.Indonesia Turbocharger adalah sebuah kompresor sentrifugal yang mendapat daya dari turbin yang sumber tenaganya berasal dari gas buang kendaraan. Pada perancangan ini turbocharger digunakan sebagai pengganti dari fungsi compressor dan turbine[1]. Rancang bangun turbocharger gas turbine engine ini dibagi menjadi beberapa sistem antara lain; combustion chamber, oil system, fuel system, dan ignition system. Dari teori – teori yang ada pada referensi[2], penulis melakukan proses perancangan yang terdiri dari beberapa bahasan, antara lain menentukan bahan bakar yang akan digunakan, hose, valve dan nozzle. Bahan bakar yang digunakan dalam rancangan ini adalah LPG (Liquid Petroleum Gas)[3]. Hose dan valve yang digunakan pada rancangan ini menyesuaikan dengan debit fluida yaitu sebesar 6,89 × 10−3 ????3/????, kecepatan fluida sebesar 87,77 m/s, dan tekanan aliran fluida sebesar 238,88 psi. Nozle yang digunakan berdiameter 0,005 m. Dari perancangan fuel system yang penulis rancang dapat menyalurkan bahan bakar yang dibutuhkan agar dapat menghasilkan pembakaran yang optimal. B.English Turbocharger is a centrifugal compressor that gets power from turbines whose power source comes from vehicle exhaust gases. In this design the turbocharger is used instead of the compressor and turbine function. Refer to the References, the authors carry out the design process which consists of several topics, including determining the fuel to be used, hose, valve and nozzle. The fuel used in this design is LPG (Liquid Petroleum Gas). The hose and valve used in this design adjusts to the fluid flow of 6,89 × 10−3 ????3/????, the fluid velocity of 87,77 m/s, and the pressure of the fluid flow of 238,88 psi. The nozle used was 0,005 m in diameter. From the design of the fuel system that the author designed can deliver the fuel needed to produce optimal combustion.
Rancang Bangun Oil System untuk Turbocharger Gas Turbine Engine Dengan Inducer Diameter 1,75 Inch Noval Dwi Kurnianto; Wira Gauthama; Zulham Hidayat
Langit Biru: Jurnal Ilmiah Aviasi Vol 14 No 01 (2021): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.54147/langitbiru.v14i01.408

Abstract

Manufacturing of gas turbine engine was started by identification of some components and systems involve in building the gas turbine engine. A turbocharger which consist of turbine and compressor as the main part was taken to make a turbine and compressor in Gas turbine engine. Those component is also the essential part of the machine. To operate the gas turbine engine, it is important to design some system such as Oil system, fuel System, Ignition System, combustion chamber, and others. In this design project the writer obtains the task to design the oil system that fit and suitable for this type of gas turbine engine. Any issue related to this design such as how to decide the viscosity of the oil, calculate critical pressure of bearing, calculate mass of the oil fluid, head pressure of the pump and reservoir capacity. The final outcome of this design is correct supply of the oil flow which is used to lubricate shaft bearing in gas turbine engine. This system also prevent the machine from over heating that can degrade components of the engine due to metal to metal contact. From the final calculation found 37 psi oil pressure is needed to lubricate shaft bearing and can maintain the continuous operation of the engine.
RANCANG BANGUN FUEL SYSTEM UNTUK TURBOCHARGER GAS TURBINE ENGINE DENGAN INDUCER DIAMETER 1,75 INCH DI HANGAR 01 TEKNIK PESAWAT UDARA SEKOLAH TINGGI PENERBANGAN INDONESIA Ridho Ramadhan; Wira Gauthama; Zulham Hidayat
Langit Biru: Jurnal Ilmiah Aviasi Vol 13 No 02 (2020): Langit Biru: Jurnal Ilmiah Aviasi Vol.13 No.2 [Juni 2020]
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

B.Indonesia Turbocharger adalah sebuah kompresor sentrifugal yang mendapat daya dari turbin yang sumber tenaganya berasal dari gas buang kendaraan. Pada perancangan ini turbocharger digunakan sebagai pengganti dari fungsi compressor dan turbine[1]. Rancang bangun turbocharger gas turbine engine ini dibagi menjadi beberapa sistem antara lain; combustion chamber, oil system, fuel system, dan ignition system. Dari teori – teori yang ada pada referensi[2], penulis melakukan proses perancangan yang terdiri dari beberapa bahasan, antara lain menentukan bahan bakar yang akan digunakan, hose, valve dan nozzle. Bahan bakar yang digunakan dalam rancangan ini adalah LPG (Liquid Petroleum Gas)[3]. Hose dan valve yang digunakan pada rancangan ini menyesuaikan dengan debit fluida yaitu sebesar 6,89 × 10−3 ????3/????, kecepatan fluida sebesar 87,77 m/s, dan tekanan aliran fluida sebesar 238,88 psi. Nozle yang digunakan berdiameter 0,005 m. Dari perancangan fuel system yang penulis rancang dapat menyalurkan bahan bakar yang dibutuhkan agar dapat menghasilkan pembakaran yang optimal. B.English Turbocharger is a centrifugal compressor that gets power from turbines whose power source comes from vehicle exhaust gases. In this design the turbocharger is used instead of the compressor and turbine function. Refer to the References, the authors carry out the design process which consists of several topics, including determining the fuel to be used, hose, valve and nozzle. The fuel used in this design is LPG (Liquid Petroleum Gas). The hose and valve used in this design adjusts to the fluid flow of 6,89 × 10−3 ????3/????, the fluid velocity of 87,77 m/s, and the pressure of the fluid flow of 238,88 psi. The nozle used was 0,005 m in diameter. From the design of the fuel system that the author designed can deliver the fuel needed to produce optimal combustion.
Rancang Bangun Oil System untuk Turbocharger Gas Turbine Engine Dengan Inducer Diameter 1,75 Inch Noval Dwi Kurnianto; Wira Gauthama; Zulham Hidayat
Langit Biru: Jurnal Ilmiah Aviasi Vol 14 No 01 (2021): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.54147/langitbiru.v14i01.408

Abstract

Manufacturing of gas turbine engine was started by identification of some components and systems involve in building the gas turbine engine. A turbocharger which consist of turbine and compressor as the main part was taken to make a turbine and compressor in Gas turbine engine. Those component is also the essential part of the machine. To operate the gas turbine engine, it is important to design some system such as Oil system, fuel System, Ignition System, combustion chamber, and others. In this design project the writer obtains the task to design the oil system that fit and suitable for this type of gas turbine engine. Any issue related to this design such as how to decide the viscosity of the oil, calculate critical pressure of bearing, calculate mass of the oil fluid, head pressure of the pump and reservoir capacity. The final outcome of this design is correct supply of the oil flow which is used to lubricate shaft bearing in gas turbine engine. This system also prevent the machine from over heating that can degrade components of the engine due to metal to metal contact. From the final calculation found 37 psi oil pressure is needed to lubricate shaft bearing and can maintain the continuous operation of the engine.
Co-Authors Arief Susanto Hanris Lukkas Adi Putra Haryadi Noval Dwi Kurnianto Ridho Ramadhan Wira Gauthama Wira Gauthama Yenni Arnas