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All Journal Rekayasa Mesin Mesin Indonesian Journal of Aerospace
Hartono, Firman
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Aerospace Engineering Astronomy Mechanical Engineering

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DESAIN AWAL RUANG BAKAR PREMIXED UNTUK TURBIN GAS ULTRA MIKRO (TGUM) DENGAN MENGGUNAKAN PENDEKATAN TEMPERATUR ADIABATIK Al Gifari, Muhamad Maris; Hartono, Firman; Darmanto, Prihadi Setyo; Reksowardojo, Iman Kartolaksono
Jurnal Rekayasa Mesin Vol. 15 No. 3 (2024)
Publisher : Jurusan Teknik Mesin, Fakultas Teknik, Universitas Brawijaya

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21776/jrm.v15i3.1613

Abstract

The need to develop ultra-micro gas turbine (TGUM) applications is getting higher, especially as a portable energy source. Many applications whose energy requirements cannot be met by current batteries but can be handled by TGUM. The energy density of kerosene is 45 times greater than that of current batteries. The development of ultra-micro gas turbines has been carried out for more than 20 years. The challenge faced in the TGUM development process was manufacturing technology, but manufacturing developments continue to advance over time, meaning that one day high-speed bearing technology may be achieved. The development of an ultra-micro gas turbine can be started from the design of the combustion chamber. The basic concept of determining the initial size of the diameter as the initial reference length is widely available and established, but this reference is only for combustion chambers with non-premixed combustion. No one has discussed the determination of the size of the premixed combustion chamber. The basis for the initial determination of the combustion chamber in this article is the determination of the adiabatic temperature, and the energy balance equation which is simplified to become Black's Principle. This method describes the relationship between the diameter of the combustion chamber, airflow dilution portion and the flame propagation speed that must be met. This method also determines the value of the equivalence ratio, and also length of combustion chamber based on SHR (Space Heating Rate) that must be taken. The results of this method when entering the condition of the combustion chamber inlet 379 K, 2.05 bar, and outlet 879 K, 1.79 bar produce a reference decision of 5 cm diameter, flame speed of 6 m/s, equivalent ratio of 0.8 and 74% cooling portion for a gas turbine mass flow rate of 85.7 g/s.
DESIGN OF A SINGLE-STAGE AXIAL POWER TURBINE IN AN ULTRA-MICRO GAS TURBINE ENGINE Solissa, Rizal Gidion; Hartono, Firman; Al Gifar, Muhamad Maris
Jurnal Rekayasa Mesin Vol. 16 No. 2 (2025)
Publisher : Jurusan Teknik Mesin, Fakultas Teknik, Universitas Brawijaya

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21776/jrm.v16i2.1763

Abstract

Today's electrical energy needs require several alternative power and electrical energy storage. One system that can be developed to meet these needs is an ultra-micro gas turbine. The single-stage axial power turbine is designed to drive a 182.574 KV BLDC electric motor generator with 50% efficiency at 10000 rpm which will produce 600 watts of power with a turbine diameter of 10-20 cm. The utilization is based on the exhaust gas from the turbine on the GT2052 turbocharger which has an efficiency value of 70%. The design is done by free fortex analytical method and gas flow simulation using computational fluid dynamic Ansys CFX. To be able to produce the target power for the BLDC electric motor, the single-stage axial power turbine designed with CFD simulation produces a power of 1830.59 watts with an air mass flow of 0.166 kg/s, a pressure ratio of 1.06, an efficiency of 80.7%.
DESAIN AWAL RUANG BAKAR PREMIXED UNTUK TURBIN GAS ULTRA MIKRO (TGUM) DENGAN MENGGUNAKAN PENDEKATAN TEMPERATUR ADIABATIK Al Gifari, Muhamad Maris; Hartono, Firman; Darmanto, Prihadi Setyo; Reksowardojo, Iman Kartolaksono
Jurnal Rekayasa Mesin Vol. 15 No. 3 (2024)
Publisher : Jurusan Teknik Mesin, Fakultas Teknik, Universitas Brawijaya

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21776/jrm.v15i3.1613

Abstract

The need to develop ultra-micro gas turbine (TGUM) applications is getting higher, especially as a portable energy source. Many applications whose energy requirements cannot be met by current batteries but can be handled by TGUM. The energy density of kerosene is 45 times greater than that of current batteries. The development of ultra-micro gas turbines has been carried out for more than 20 years. The challenge faced in the TGUM development process was manufacturing technology, but manufacturing developments continue to advance over time, meaning that one day high-speed bearing technology may be achieved. The development of an ultra-micro gas turbine can be started from the design of the combustion chamber. The basic concept of determining the initial size of the diameter as the initial reference length is widely available and established, but this reference is only for combustion chambers with non-premixed combustion. No one has discussed the determination of the size of the premixed combustion chamber. The basis for the initial determination of the combustion chamber in this article is the determination of the adiabatic temperature, and the energy balance equation which is simplified to become Black's Principle. This method describes the relationship between the diameter of the combustion chamber, airflow dilution portion and the flame propagation speed that must be met. This method also determines the value of the equivalence ratio, and also length of combustion chamber based on SHR (Space Heating Rate) that must be taken. The results of this method when entering the condition of the combustion chamber inlet 379 K, 2.05 bar, and outlet 879 K, 1.79 bar produce a reference decision of 5 cm diameter, flame speed of 6 m/s, equivalent ratio of 0.8 and 74% cooling portion for a gas turbine mass flow rate of 85.7 g/s.
ANALYSIS ON THE INFLUENCE OF DUCT CASING GEOMETRY ON THE PERFORMANCE OF A DUCTED FAN Pangaribuan, Marcellino; Hartono, Firman
Mesin Vol 30 No 1 (2024)
Publisher : Faculty of Mechanical and Aerospace Engineering

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.5614/MESIN.2024.30.1.3

Abstract

This paper aims to evaluate the influence of an electric ducted fan’s (EDF) geometry on its performance through parameter correlation analysis. Sample data was first built by generating new EDF models with varying duct casing geometries through optimal space-filling (OSF) sampling method. Afterwards, each model was numerically solved with computational fluid dynamics (CFD) analysis to obtain each model’s thrust, required power, and efficiency. It is found that the casing’s inlet lip diameter displays the greatest influence on the EDF’s total thrust, as the inlet diameter determines the casing’s surface area affected by the low-pressure region ahead of the rotating fan blades. Additionally, it is found that length of the casing’s exhaust lip affects the EDF’s efficiency, while the exhaust lip diameter displays the highest correlation with the fan’s required power.
PEMBUATAN KODE DESAIN DAN ANALISIS TURBIN ANGIN SUMBU VERTIKAL DARRIEUS TIPE-H Arsad, Agus Muhamad; Hartono, Firman
Indonesian Journal of Aerospace Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Makalah ini menjelaskan tentang pembuatan kode desain dan analisis turbin angin sumbu vertikal Darrieus. Dalam kode yang dikembangkan ini, turbin angin dimodelkan sebagai airfoil dua dimensi yang berputar sementara gaya sudu dihitung dengan menggunakan model tabung aliran tunggal dengan mengasumsikan distribusi kecepatan free stream sepanjang arah aksial turbin bervariasi linier. Teori elemen sudu dan teori momentum digunakan untuk mencari hubungan antara nilai parameter turbin dengan performa turbin angin. Pada kode ini, jumlah sudu dapat divariasikan antara 2 sampai dengan 10 buah. Tipe airfoil sudu dapat disesuaikan, namun kode ini menyediakan 5 tipe airfoil yang dapat dipilih yaitu NACA 0012, 0015, 0018, 0021 dan 0025. Dibandingkan dengan referensi, hasil analisis menunjukkan bahwa secara kualitatif kode ini cukup baik.
PENGUKURAN TURBULENSI DAN ANGULARITAS ALIRAN PADA TEROWONGAN ANGIN SUBSONIK LAPAN (THE MEASUREMENT OF TURBULENCE AND FLOW ANGULARITY IN LAPAN’S SUBSONIC WIND TUNNEL) Hartono, Firman; Bessie, Ronald; Aribowo, Agus
Indonesian Journal of Aerospace Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2481

Abstract

This paper explains the measurement of turbulence intensity and angularity in LAPAN’s Open Loop Subsonic Wind Tunnel. The objective of the research is to find out the aerodynamic characterstic of the tunnel. Turbulence intensities were measured using 200 mm and 300 mm diameter turbulence sphere. The flow angularity in the cross section of tunnel’s test section was measured using five holes probe at two different axial position i.e. 1. above internal balance turning table and 2. above external balance turning table. The number of measured points are 110 for every cross section plane and the average velocity during angular flow measurement is 15 m/s. Turbulence measurements shows wind tunnel’s turbulence intensity of 0.26% at 25.9 m/s and 0.1% at 19 m/s. Angularity measurement shows relatively large angular flow variation in the jet, i.e. pitch angle of ±3o and achieving +7o at some locations and yaw angle of ±2.5o.
ANALISA PEMILIHAN BENTUK VORTEX GENERATOR UNTUK SAYAP PESAWAT LSU-05 MENGGUNAKAN METODE NUMERIK Herdiana, Dana; Hartono, Firman
Indonesian Journal of Aerospace Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3211

Abstract

Telah dilakukan pengujian perdana dari pesawat LSU-05 buatan LAPAN dimana hasil evaluasi pengujian terdapat kekurangan yaitu pada saat pesawat melakukan manuver, hal tersebut diakibatkan oleh beberapa faktor. Salah satu faktor adalah kurangnya koefisien gaya angkat maksimum. Untuk mengatasi hal tersebut maka ada beberapa solusi yang dapat mengatasi hal tersebut. Salah satunya yaitu dengan penambahan komponen pada sayap yaitu vortex generator. Metode yang digunakan untuk penelitian ini adalah metode numerik yaitu mensimulasikan penambahan vortex generator pada sayap dengan berbagai varian bentuk dan posisi pemasangan dari vortex generator menggunakan CFD (Computational Fluid Dynamic). Model yang disimulasikan adalah model sayap saja dan sayap dengan vortex generator. Bentuk yang dipilih untuk vortex generator adalah rectangular, triangular, dan gothic (mod) serta posisi pasang mulai dari 15 %, 20 %, dan 25 % dari panjang chord. Dari hasil yang diperoleh bentuk triangular memiliki nilai CLmax yang lebih besar dibanding bentuk rectangular dan gothic (mod) yaitu 1.4553 dan posisi pasang yang memiliki CLmax yang lebih besar yaitu di posisi pasang 20%. Bentuk vortex generator yang cocok dipasang pada sayap pesawat LSU-05 adalah bentuk triangular di posisi pasang 20%.
PENGARUH VARIASI SUDUT SERANG SUDU PADA PRESTASI TURBIN ANGIN Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin; Hartono, Firman
Indonesian Journal of Aerospace Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Research on variations of angle of attack turbine blade has been conducted to investigate their correlation with windturbine performances, and for these purposes, AEROFOIL LS (1)-0417 MOD has been selected with 4 angle variations. The first variation is selscted with constant slipstream, the second with Cl max of 0.3, while the third and fouth variations with Cl max of 0.5 and 0.7 respectively. Based on blade element and momentum theory for obtaining efficiency, the following results for all the four variations are 18.15 percent, 16.46 percent, 16.15 percent and 16.26 percent. Hence, it can be concluded that, a highest efficiency is obtained with a constant slipstream as in case 1. In practice, to achieve such configuration, a more accurate blade fabricantion process is required to obtain the highest efficiency.
RANCANGAN DAN ANALISIS STRUKTUR SUDU TURBIN ANGIN LPN 10000 E Atmadi, Sulistyo; Hartono, Firman
Indonesian Journal of Aerospace Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a816

Abstract

Structure of the LPN 10000 E wind turbine blade has been manufactured and its structural analysis to find out the strenght of this structure during its operation has also been conducted. The method of aero bending moment and centrifugal bending moment and load has been used while neglegting frcitional and torsional load. The analysis is obtained for composite blade strengthened by high strength carbon unidirectional reinforcement composite. With safety factor of 1.3 minimum, it was concluded that the blade is strong enough to use at its designed operational load.
ANALISIS COMPUTATIONAL FLUID DYNAMIC (CFD) RUANG BAKAR MESIN TURBOJET TJE500FH V.1 (COMPUTATIONAL FLUID DYNAMIC ANALYSIS OF TURBOJET TJE500FH V.1’S COMBUSTION CHAMBER) Hartono, Firman; Arizal, Arizal
Indonesian Journal of Aerospace Vol. 11 No. 2 Desember (2013): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Pada makalah ini dijelaskan hasil-hasil Computational Fluid Dynamics (CFD) dari ruang bakar versi 1 mesin TJE500FH. Tujuan dari simulasi ini adalah untuk menyelidiki karakteristik aliran udara di dalam ruang bakar terutama terkait fenomena adanya pembakaran di luar nosel. Simulasi ruang bakar dalam makalah ini menggunakan model 3D pada kondisi dingin, tunak dan dengan kerapatan udara dianggap konstan. Model turbulensi k – ï¥ standar digunakan untuk menghitung efek turbulensi terhadap medan aliran yang dihasilkan. Dari simulasi ini, diketahui bahwa massa udara yang masuk zona primer dan zona sekunder liner lebih kecil dari rancangannya sehingga kemungkinan tercipta campuran bahan bakar – udara yang terlalu kaya di daerah tersebut. Selanjutnya, sebagian besar udara masuk liner ruang bakar pada zona dilusi sehingga alih-alih terjadi pendinginan malah terjadi reaksi pembakaran. Kurangnya udara pada zona primer dan zona sekunder tampaknya disebabkan oleh bentuk sisi-sisi luar liner yang tajam.
Co-Authors Al Gifar, Muhamad Maris Aribowo, Agus Arizal, Arizal Arsad, Agus Muhamad Bessie, Ronald Darmanto, Prihadi Setyo Fitroh, Ahmad Jamaludin Herdiana, Dana Iman Kartolaksono Reksowardojo Muhamad Maris Al Gifari Pangaribuan, Marcellino Solissa, Rizal Gidion Sulistyo Atmadi