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All Journal Jurnal Teknologi Dirgantara Majamecha MACHINERY: Jurnal Teknologi Terapan Industrial Research Workshop and National Seminar Jurnal Polimesin Indonesian Journal of Aerospace
Wuwung, Vicky
Jurusan Teknik Mesin,Politeknik Negeri Bandung,Bandung
Aerospace Engineering Humanities Astronomy Automotive Engineering Chemical Engineering, Chemistry & Bioengineering Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Education Electrical & Electronics Engineering Energy Engineering Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering Physics Other

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Design of Mini Turbojet Engine Combustion Chamber Liner With 200N Static Thrust Santoso, Rais Ryacudu; Wuwung, Vicky; Annisa, Reina Fadjrin Nurul; Kartanegara, Radi Suradi
Indonesian Journal of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.38

Abstract

Design of mini turbojet engine with 200N static thrust at an air mass flow of 0.55kg/s, requiring annular type combustion chamber with liner capability of dividing the air mass flow in the primary zone by 20%, secondary zone 30%, dilution zone 50%, and with 4%- 10% pressure loss. In the primary zone, it is necessary to have a recirculation zone that will become a stable combustion place. Liner geometry is obtained by analytical and empirical calculations, that is validated by numerical simulations at cold flow steady conditions. Analytical and empirical calculations resulting in the primary, secondary, and dilution zone respectively: the hole diameter: 2.153mm, 2.503mm, 5.005mm; number of holes: 44, 52, 44 holes; the distance of hole from inlet liner: 28.5mm, 47.5mm, 113.6 mm; air mass flow rates: 19.4%, 29.6%, 50%, and the pressure loss of the combustion chamber is 4%. The numerical simulation is performed by using the turbulent k-e model (extended wall) and has a difference resulted with analytical and empirical calculations on mass flow in the primary, secondary, and dilution zone: 3.44%, 9.09%, 8.88%, and the pressure drop is 10.86%. The recirculation zone that is fulfil injector placement criteria formed in the primary zone at the longitudinal cross-section position (q) from 32.72o to 360o with 32.73o in increment, with horizontal (H) and vertical (V) distance from inner liner wall are varies from 34 to 40 mm for H, and from 35 to 43 mm for V with outer recirculation tangential velocity variation from 43 to 60 m/s.
RX-320 Rocket Static Pressure Combustion Chamber Prediction and Validation by Using Invers Method Sofyan, Sofyan; Wuwung, Vicky
Indonesian Journal of Aerospace Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2018.v16.a2866

Abstract

The static pressure data of the combustion chamber which can generally be obtained by performing direct measurements when static test is performed on the rocket is an important parameter in predicting the thrust and design of the combustion chamber of the rocket. However, there is a model rocket for flight test that is used in static test. Thus, there is no mounting for static pressure sensors (for measurement) are made. To solve the problem, then the inverse method is used as an iterative solution for the basic equations of the rocket thrust force in the nozzle by guessing the value of the static pressure of the combustion chamber firstly and calculate the iteration by including the value of the rocket thrust from static test data and the efficiency variation of the nozzle. The results of this calculation are then validated by using a 3D-CFD numerical simulation to obtain a more detailed comparison on the nozzle. In this research RX 320 LAPAN rocket nozzle with focus on maximum static thrust data of static test results is used. The 3-D numerical simulation is performed using Numeca CFD software, with k-extended wall extended turbulent model, numerical multigrid level 3 scheme, center based, and convergence criteria of 10 e-05. The result of calculation by inverse method and its comparison with numerical simulation shows that the smallest difference of the combustion chamber static pressure between inverse method and numerical simulation is 0.017%, that is achieved at 92% nozzle efficiency. At this point, the static pressure of the combustion chamber is 57.94 bar. From this point of view, the results of this comparison indicate that the inverse method can be used accurately for static pressure of the combustion chamber prediction, if the nozzle efficiency is given correctly. Furthermore, with given static pressure of the combustion chamber correctly, it will be very helpful in the design of the more optimum combustion chamber.
JUSTIFIKASI CFD KEDALAMAN GROOVE BAN PADA PROSES PERAWATAN HARIAN PESAWAT B737-800 AKIBAT HYDROPLANING (B737-800 TIRE GROOVE DEPTH CFD JUSTIFICATION ON ITS DAILY MAINTENANCE PROCESS DUE TO HYDROPLANING) Wuwung, Vicky; Anggreyni, Nelli; Hitoyo, Valeri Maria; Bintoro, Carolus
Indonesian Journal of Aerospace Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2017.v15.a2528

Abstract

Groove atau ‘kembang†pada ban pesawat merupakan sarana untuk mengalirkan air dari bagian depan menuju bagian belakang melalui bagian bawah ban, tanpa mengangkat ban sehingga dapat mencegah terjadinya hydroplaning. Sehingga, pengaruh nilai kedalaman groove terhadap gaya angkat pada ban pesawat B737-800 yang bergerak di landasan dengan genangan air perlu dijustifikasi dalam proses perawatan harian. Penelitian ini menyimulasikan proses mengalirnya air pada bagian bawah ban dengan menggunakan simulasi numerik (CFD Numeca Fine/Marine) 3-D unsteady sebagai metode untuk menjustifikasi pengaruh groove. Simulasi dilakukan untuk kondisi gerakan ban pesawat pada saat proses landing (V = 62,275 m/s) beberapa saat setelah touch down (setelah skidding) dengan ban pesawat dianggap rigid body sebagai kondisi batas. Selanjutnya tinggi genangan air dipilih pada saat runway dinyatakan dalam kondisi flood (tinggi genangan air = 2,54mm). Simulasi tersebut menampilkan hasil perhitungan ban pesawat Boeing 737-800, dengan hydroplaning mulai terjadi ketika kedalaman groove ban berada dibawah 0,4 inch. Hal ini menunjukkan bahwa semakin kecil kedalaman groove, maka semakin kecil luas penampang groove dan semakin besar gaya kompresi yang terjadi pada bagian bawah ban dan semakin memperbesar kemungkinan terjadinya fenomena hydroplaning. Dengan diketahuinya hasil dari simulasi tersebut, maka hasil penelitian ini dapat digunakan sebagai masukan bagi proses maintenance harian pesawat B737-800 dan mampu memberikan suatu hal baru dalam pembelajaran khususnya mengenai fenomena hydroplaning.
APLIKASI CFD DALAM PENENTUAN PERFORMA MESIN TURBOFAN MODEL CFM56-5B YANG MENGALAMI CACAT PADA KIPAS UNTUK KEPUTUSAN MAINTENANCE Wuwung, Vicky; Wandani, Puspa; Bintoro , Carolus
Indonesian Journal of Aerospace Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2945

Abstract

Penelitian ini membahas mengenai kajian kerusakan yang terjadi pada bilah kipas mesin turbofan CFM56-5B. Kerusakan tersebut memerlukan adanya sebuah keputusan maintenance, apakah bilah kipas tersebut masih layak digunakan ataukah perlu di repair atau diganti. Meskipun regulasi menetapkan bahwa kerusakan tersebut masih dapat diterima, namun perlu ditinjau dari segi performanya, apakah kipas masih dapat memberikan performa yang baik atau tidak. Kajian dilakukan dengan menyimulasikan model bilah kipas CFM56-5B pada kondisi baik dan cacat pada perangkat lunak CFD-Numeca di kondisi take-off dan cruise. Cacat pada bilah berupa dent dengan kedalaman 0.069†dan terletak seragam di semua bilah pada 70% span bilah di bagian leading edge sebagai simulasi kerusakan akibat adanya bird strike. Simulasi numerik dilakukan dengan kondisi pemodelan aliran steady, dan menggunakan model turbulen Spallart-Allmaras. Hasil simulasi numerik menunjukkan adanya penurunan performa mesin pada Thrust di kondisi take-off sebesar 14% dan penurunan efisiensi sebesar 16%, sedangkan pada kondisi cruise, penurunan Thrust dan efisiensi berturut-turut adalah sebesar 55%, dan 54%. Penurunan Thrust pada saat take-off berdasarkan regulasi AC 25-13 adalah aman dan tidak perlu dilakukan repair atau replacement. Namun, meskipun aman, mesin akan boros bahan bakar ketika berada dalam kondisi cruise sehingga perlu dilakukan repair atau replacement. Penentuan keputusan maintenance jika didasarkan pada regulasi AC 25-13 pada akhirnya adalah tidak diperlukannya repair atau replacement pada bilah kipas.
Co-Authors Anggreyni, Nelli Annisa, Reina Fadjrin Nurul Ardi, Hanni Maksum Bintoro , Carolus Bintoro, Carolus Bintoro, Carolus Budi Triyono Budi Triyono C Bintoro Dibyo Setiawan Faishal Farras Fathurrohman Nurdin Haryadi - Haryadi Haryadi Hitoyo, Valeri Maria M. Ilham Nelli Anggreyni Norhafizan Ahmad Pasaribu, Mori Theresya Elisabet Puspa Wandani Radi Suradi Kartanegara Santoso, Rais Ryacudu setiawan, Dibyo Sofyan Sofyan Sofyan Sofyan Suseno, Bella Maharani Marcellia sutiana Teguh Wibowo Valeri Maria Hitoyo Wandani, Puspa Yohanes Sinung Nugroho Zaim Sidqi Islami Zaki Odang