ADVANCED PROPULSION SYSTEMS (APSYS) LAB
High Speed Propulsion Lab in IIT Kharagpur, India
ABOUT
The APSYS lab is located at 001 ground floor of Annex Building in the Aerospace Engineering Department, IIT Kharagpur, India. Research on high speed propulsion, pulse jet ignition, vortex combustion, thermoacoustics, spark ignition, jet deflection, etc is being conducted experimentally and computationally. The group performs flow imaging, flow diagnostics, pressure measurements on scaled down test objects. Members have access to a super-computing facility for running computer codes like Fluent, SU2, OpenFoam etc. The Lab has a dedicated compressed air facility, a direct connect modular flow facility capable of running various aerothermodynamic studies. A team of PhD students, MTech students and Undergrad students work on various projects.
NEWS AND ANNOUNCEMENTS
APSYS Labs receives DST funding for turbulent combustion research. The funding will cover equipment procurement for pressure measurements and the purchase of specialty gases used in the tests.
General Information
Areas of research include combustion oscillations, vortex driven flows, pulsating flows, method of characteristics, combustion sciences etc.As part of our work in high speed combustors, we are studying flame behavior, ignition, stabilization, flashback and mode transition in high speed combustors both with cavity assisted and strut assisted flame stabilization mechanisms. As part of our work on Combustion Instability prediction and control, we are also looking at vortex driven resonant combustion in Gas Turbine combustors. Active combustion control using secondary injection targeting q' oscillation tailoring are being attempted.
As part of our work in high speed combustors, we are studying flame behavior, ignition, stabilization, flashback and mode transition in high speed combustors both with cavity assisted and strut assisted flame stabilization mechanisms. As part of our work on Combustion Instability prediction and control, we are also looking at vortex driven resonant combustion in Gas Turbine combustors. Active combustion control using secondary injection targeting q' oscillation tailoring are being attempted.
PEOPLE
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Past Members
POSTS FROM THIS GROUP
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Insights into flame flashback phenomenon utilizing a Strut-Cavity flame holder inside scramjet combustor
Pranay Singeetham #Advanced Propulsion Systems (APSYS) Lab @Amardip Ghosh
Understanding upstream flame propagation in scramjets is challenging, particularly concerning flame flashback in a combustor with a novel strut-cavity flame holder. Two-dimensional unsteady Reynolds-averaged Navier–Stokes (URANS) simulations were performed to investigate how Mach number and wall divergence affect flame behavior. The utility of the strut-cavity flame holder was highlighted through a study of its non-reacting flow characteristics. Flow dynamics are significantly altered as the shear layer above the cavity interacts with the downstream hydrogen jet. Shear layer dynamics and fuel-air mixing are improved through key factors such as shock-train behavior, cavity oscillations, and transverse fuel injection. The submerged fuel jet is less exposed to supersonic flow and demonstrates reduced entropy rise, achieving a 16% increase in mixing efficiency compared to standalone struts and a 46% improvement over transverse injection without a flame holder. Thermal choking shifts the shock train upstream, facilitating interactions with the shear layer and enhancing vortex formation, which decreases flow speed and promotes upstream flame propagation. The presence of OH radicals indicates that flame flashback follows a periodic pattern with an initial gradual slope, suggesting effective anchoring. Stability and flashback likelihood are affected by low-speed zones, vortex merging, and wall divergence. At Mach 3, combustion efficiency improves without wall divergence due to increased heat release, while wall divergence prevents flame flashback by sustaining supersonic core flow and managing flow-flame interactions. At higher core flow velocities, flame stabilization occurs at the cavity's separation corner, despite a tendency for upstream propagation, with validation of the URANS results achieved through two-dimensional large eddy simulations.
SCRAMJET Test Rig Instrumentation
Amardip Ghosh #Advanced Propulsion Systems (APSYS) Lab
The rig is being instrumentated for transitioning from cold flow supersonic mixing studies to reacting flow mode transition studies.
Attachments
| 1. Minwook Chan PhD Thesis | |
| 2. PhD Thesis |
Thermodynamics and Aerospace Propulsion Systems Class
Amardip Ghosh #Advanced Propulsion Systems (APSYS) Lab
Aerodynamics, Thermodynamics, Heat Transfer and Combustion Chemistry. The building blocks of propusion systems. While feedback control is also an integral part, courses like these primarily cover the mechanical aspects of propulsion systems.
Ex-ISRO Chairman visits APSYS Labs
Amardip Ghosh #Advanced Propulsion Systems (APSYS) Lab
Dr. Koppillil Radhakrishnan visited APSYS lab in January 2023 as a part of a visit to IIT Kharagpur India. Dr. Radhakrishnan is an Indian space scientist who headed the Indian Space Research Organisation between November 2009 and December 2014 as Chairman of Space Commission, Secretary of the Department of Space and Chairman of ISRO.
Instability of isolator shocks to fuel flow rate modulations in a strut-stabilised scramjet combustor
Amardip Ghosh #Advanced Propulsion Systems (APSYS) Lab
In this recent paper from our group on SCRAM-RAM modes inside a Dual-Mode-Scramjet-Engine (DMSJ), Rajesh Kumar shows that for the Supersonic-at-Strut modes, shockwaves in the combustor respond predictably to an increase or decrease in fuel flow rates. Intermediate and final flow fields bear close resemblance to the steady state flow fields predicted by RANS for those fuel flow rates. Shocks adjust accordingly to match the combustion driven pressure rise. Under the Supersonic-at-Strut mode, when fuel flow rate is increased, the shocks steepen and concentrate near the base of the strut. When fuel flow rate is decreased, the opposite trend is observed wherein shocks become more oblique and spread away downstream from the base of the strut. For the Subsonic-at-Strut modes, shockwaves in the flow field are rather unstable to fuel flow rate modulations. Any change in fuel flow rates causes the isolator shocks to immediately move upstream irrespective of if the fuel flow rate is increased or decreased, suddenly or gradually. Because of this instability of isolator shocks for the Subsonic-at-Strut modes, feedback control of isolator shocks using fuel-flow rate modulations alone may not be feasible.
Attachments
| 1. Instability of isolator shocks to fuel flow rate modulations in a strut-stabilised scramjet combustor |
Teacher's day celebration 2024 in APSYS Lab
Rajesh Kumar #Advanced Propulsion Systems (APSYS) Lab @Amardip Ghosh
"Thank you for shaping the future with your wisdom, dedication, and guidance. Your impact on our life is immeasurable, and we are forever grateful. Happy Teacher’s Day!"
Effect of Wall Divergence on the Flow Field Inside a Scramjet Engine
Rajesh Kumar #Advanced Propulsion Systems (APSYS) Lab @Amardip Ghosh
🚀 Just returned from the Aviation Forum 2024, and what an incredible experience it was! I am grateful to my supervisor, Dr. Amardip Ghosh, for his consistent support and insightful advice, and many thanks to my institute, the Indian Institute of Technology Kharagpur, India, for the financial support that made this journey possible. 🙏
What happens in Vegas doesn’t stay in Vegas – it’s coming with me as newfound knowledge and inspiration for my future work! ✈️
I had the pleasure of presenting my paper titled "Effect of Wall Divergence on the Flow Field Inside a Scramjet Engine" (DOI: 10.2514/6.2024-3891). Engaging with fellow researchers and exchanging ideas has truly been inspiring. The conference was a fantastic opportunity to connect with some brilliant minds in the field of aerodynamics and propulsion.
I’m also deeply thankful to my co-authors for their dedication and hard work in ensuring we met the submission deadline. Your contribution was key to our success. A special thanks to Dipesh Raj, a fellow researcher, for his invaluable help in planning and organizing everything – we couldn't have done it without you!
Looking forward to applying these experiences and insights as I continue the journey in aviation research! ✈️
#AviationForum2024 #Research #Networking #Gratitude
Attachments
| 1. Effect of Wall Divergence on the Flow Field Inside a Scramjet Engine |
Showcase Our Work to ISRO Chairman S. Somanath and Dr. V. Narayanan
Rajesh Kumar #Advanced Propulsion Systems (APSYS) Lab @Amardip Ghosh
🚀 Proud to Showcase Our Work to ISRO Chairman S. Somanath and Dr. V. Narayanan at the Department of Aerospace, IIT Kharagpur! 🚀
We had the immense honor of hosting ISRO Chairman S. Somanath, along with Dr. V. Narayanan, Director of the Liquid Propulsion Systems Centre, at our Department of Aerospace, IIT Kharagpur. During their visit, we demonstrated the experimental setup of a scramjet engine that I developed from scratch under the invaluable guidance of Dr. Amardip Ghosh.
Their keen interest in our work and their encouraging words have fueled our determination to expand our research in aerospace engineering.
A heartfelt thanks to our Head of Department, Prof. Arnab Roy, for his continuous support and for facilitating such impactful interactions. Special thanks also to Dr. Ghosh for his mentorship and guidance, and to the entire team at APSYS Lab for making the setup ready on time.
We look forward to contributing even more to India's space research!
#Aerospace #ISRO #Innovation #Research #IITKharagpur #SpaceExploration #EngineeringExcellence
Heat Release Distribution
Saisanthosh Iyer #Advanced Propulsion Systems (APSYS) Lab @Amardip Ghosh
Multistep CFD simulations on HPC cluster using Fluent showing Heat Release Distribution
Flame flashback in supersonic flowfields
Amardip Ghosh #Advanced Propulsion Systems (APSYS) Lab
A Mach 2 inflow with a split ramp configuration with an offset shows upstream flame front movement ahead of the expansion corner of the ramp. Multistep CFD simulations on HPC cluster using OpenFOAM.
Flame oscillations under certain flow and equivalence ratio conditions can be controlled using open loop and closed loop controls. Different flame shapes, lift off characteristics can be observed, along with periodic behavious in flame anchoring location. Flame heat release modulations, anchoring, oscillations suppression using acoustic forcing and the effect of resonant burning on NOx emission are important topics of research being addressed.
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Schlieren flow visualization is based on the deflection of light by a refractive index gradient. The index gradient is directly related to flow density gradient. Due to this deflection an intensity pattern is created on a screen. Here an initial test of Schlieren using a cangle flame is shown.
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BTP and MTP Project Topics - 2023 Batch
Amardip Ghosh #Advanced Propulsion Systems (APSYS) Lab
This year we have a large number of BTP and MTP students as well as students from outside schools interning with our lab. While we remain open to project suggestions from students and sponsors, we also want to create a thematic focus of projects we want students to work on. If you have signed up with our lab for your BTP, MTP or Summer Internship, you can go over the list of topics we are proposing. Also read up the literature in the attachments section. You may be able to extend the work described in those papers or theses or you may be able to do them in a different way. If that is the case, let us know of your idea after you have gone through any of the attachments.
Attachments