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Axial Fan/ Compressor, Aircraft Icing
Raman Research Fellowship
Application form for FY 2025-2026
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Name
Dr.S Satish Kumar
- Designation Principal Scientist
- Lab / Instt CSIR-National Aerospace Laboratories(CSIR-NAL), Bengaluru
- Area of research Axial Fan/ Compressor, Aircraft Icing
- Date of Birth 14-12-1983
- Age not exceeding 45 yrs. as on Jan 30, 2025
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Date Of Joining CSIR With Designation
Date of Joining CSIR2008-06-13Designation (At the time of joining CSIR)Junior Scientist
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Qualification
,DegreePh.DBoard / UniversityIndian Institute of ScienceDivision--SubjectAerospaceYear2020,DegreeM.E.Board / UniversityPSG College of Technology/ Anna UniversityDivisionMark of DistinctionSubjectMechanical (Computer Integrated Manufacturing)Year2008DegreeB.E.Board / UniversityDayananda Sagar College of Engineering/ Visvesvaraya Technological UniversityDivisionMark of DistinctionSubjectMechanicalYear2005
- Whether belonging to SC/ST/OBC Others
- Knowledge Of Foreign Languages
LanguageEnglishSelect LanguageCan SpeakCan ReadCan Write
- Experience
,Position HeldProject trainee (Advanced Composites Division, CSIR-NAL)DurationFrom2005-10-06To2006-08-04Nature of Work• Testing of Smart Materials under various environmental conditions,Position HeldProject Intern (John F Welch Technology Centre (GE), Steam Turbines COE, Buckets & Rotor Division, Bangalore)DurationFrom2007-11-19To2008-05-16Nature of Work• Optimization of tangential entry dovetail profile for Steam Turbines,Position HeldJunior Scientist (Propulsion Division, CSIR-NAL)DurationFrom2008-06-13To2011-06-13Nature of Work• Experimental investigative studies on casing treatment in axial flow compressor stage
• Calibration of Helicopter Engine Bell-mouths from HAL, Koraput
,Position HeldScientist (Propulsion Division, CSIR-NAL)DurationFrom2011-06-13To2015-06-13Nature of Work• CFD analysis of the transonic compressor stage
• Experimental performance evaluation of skewed casing treatment configurations in axial compressor stage
• Detailed project planning, stress and vibration analysis for DRDO-GTRE Fan stage performance evaluation
,Position HeldSenior Scientist (Propulsion Division, CSIR-NAL)DurationFrom2015-06-13To2020-06-13Nature of Work• Designed and developed a new Self-recirculating type casing treatment (RCT)
• Performed CFD, CSD, and experimental studies on RCT
• Characterized the aeroelastic aspects of RCT
• Steady and unsteady experimental performance evaluation of the high-speed Fan stage for various speeds
• Conjugate heat transfer CFD simulations for SARAS Engine Exhaust Jet-Propeller Interaction. Flight test data analysis and sensitivity studies for many flight events - altitudes and speeds to estimate engine installation losses
Position HeldPrincipal Scientist (Propulsion Division, CSIR-NAL)DurationFrom2020-06-13To2023-09-19Nature of Work• Established Icing Research Facility (IRF) at Propulsion Division for studying various deicing/ anti-icing systems for CSIR-NAL aircraft programs
• Demonstrated deicing of SARAS Aerofoil leading edge segment with PZT based electro-vibratory technique
• Development of anti-icing system for engine intake lips using engine exhaust gases/ bleed air to suit SARAS MKII aircraft
• Engine intake duct CFD performance evaluation
• Development of an Electric based anti-icing technique for a more electric Regional Transport Aircraft (RTA)
- Number Of Publications
International6
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Number Of Patents
National--International--
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Number Of Books
National--International--
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Awards & Recognition
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Research, Development And Innovation Output Of The Candidate. A) Details Of Technologies And Products / Services
Select Year2023 - 2024Developed--Licensed--Commercialized--New entrepreneurs developed--Rol--Rol--Rol--Rol--
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License Fee Received And Royalty Received
Select Year2023 - 2024License fee received--Royalty received--Rol--Rol--
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Skill Development
,Select Year2022 - 2023Area CoveredCompressor blade VibrationNo. of people4Rol--Rol--Select Year2023 - 2024Area CoveredFuel Cell based Aircraft Electric PropulsionNo. of people1Rol--Rol--
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Socio-Economic Interventions
Select Year2023 - 2024No. of technologies deployed--Extension activities--Rol--Rol--
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Major achievements/contribution of international level in the proposed area of research
• Dual benefits of enhanced stall margin without drop in performance and also improved aeroelastic benefits were demonstrated for the transonic compressor stage with Self-Recirculating type casing treatment (Self-RCT)
• The outcome of this research led to many international publications notably in the ASME Journal of Turbomachinery
• Fan stage performance evaluation for DRDO-GTRE and DST-funded programs aided in understanding the detailed flow characteristics
Enclose file, if any -
Name of the host Professor/Guide and full address of the Foreign Instt/Univ/R&D lab
Prof. Arvind Gangoli Rao Professor and Chair of Sustainable Aircraft Propulsion Faculty of Aerospace Engineering, Delft University of Technology Netherlands
Acceptance letter of host institute Prof. Arvind Gangoli Rao - Hosting of Satish Kumar_1.pdf (218.37 KB) - Research accomplishments of the host He is a specialist in aircraft propulsion and has worked on a variety of problems related to combustion, turbine cooling, and engine architectures. He has worked extensively on Fan BLI under sustainable aviation research. Dr. Arvind Gangoli Rao has been involved in several EU projects and is a member of the ACARE working group on Energy and Environment and Dutch national representative of the International Society of Air Breathing Engines (ISABE). He has more than 112 research publications.
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Major research facilities at the host laboratory/institute
1. High Speed Wind Tunnels
• TST-27 Transonic/Supersonic wind tunnel
• Hypersonic wind tunnel
2. Low Speed Wind Tunnels
• Open Jet facility
• Low Turbulence tunnel
• W, M and A tunnel
3. Hot wire anemometry
4. PIV systems
5. Flow visualization using infra-red camera
- Prior linkage/cooperation with the host Correspondence with the professor regarding the Fan boundary layer ingestion and its application
- Reason for selecting the proposed host He has been actively involved in the development and application of Fan BLI to the futuristic and advanced aircraft programs which is aligned with my research efforts at CSIR-NAL. The techniques and knowledge gained will also enhance the capabilities of CSIR-NAL
- Title of the research proposal to be carried out abroad Fan Boundary Layer Ingestion Behavior and Flow Control
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Detailed description of the research work to be carried out abroad
Modern aircraft designs demand more sustainable and eco-friendly propulsion solutions. One of the solutions is the Fan Boundary Layer Ingestion (BLI) to achieve enhanced improvements in propulsive efficiency. This technique is being evaluated in many modern aircrafts such as hybrid and blended wing bodies, aircraft with distributed propulsion, NASA’s STARC-ABL single aisle 150-passenger class commercial transport electric aircraft, Cambridge-MIT Silent blended wing Aircraft, and the D8 “double-bubble” with a wide fuselage.
Understanding the complex flow behavior of the fan stage with a low-velocity boundary layer being ingested is critical. The non-uniform loading of the fan blades along the span affects the aerodynamic performance if the design doesn’t cater to the distorted entry flow. Also, the fan performance at various operating conditions/speeds needs to be studied to estimate the safe operating margin. The proposed research work aims to address the challenges pertaining to the complex flow behavior of the fan with BLI, and the safe operating margin is estimated. A suitable fan distortion tolerant flow control technique will be implemented to mitigate the associated aerodynamic penalty.
Background and Current Work
Axial compressor flow behavior and control
Over the years, my research work has focused on understanding the complex flow physics of the axial compressor stage available at the Propulsion Division, CSIR-NAL. This primarily involves having detailed steady and unsteady measurements along and across the compressor stage assisted by steady and unsteady RANS CFD computations. The stability margin, or the safe operating margin, is a very critical input for the pilot. A correct estimate will lead to harnessing higher performance from the aero-engine. Due to inlet flow distortions and adverse pilot maneuvers, the stall margin will be reduced. Hence, the eminent objective is to enhance the stall margin to cater for these events. This is achieved by incorporating active and passive flow control devices.
My interest in flow control led to the development of a novel Self-Recirculating type Casing Treatment (Self-RCT) during my doctoral studies. I designed and developed a new Self-recirculating type casing treatment (RCT). Using numerical and experimental techniques, the dual benefits of enhanced stall margin without drop in performance and improved aeroelastic benefits were demonstrated for the transonic compressor stage with Self-RCT. The outcome of this research led to many international publications [1-7], notably in the ASME Journal of Turbomachinery. The knowledge gained from the flow control research will be very useful for the present proposed work on Fan with BLI.
Fan stage performance evaluation
I was a co-PI for the steady and unsteady aerodynamic performance evaluation of the high-speed fan stage of the 4kN thrust category Small Turbofan Engine (STFE) developed by M/s. DRDO-GTRE for Subsonic Cruise Nirbhay Missile. A new fan stage test rig was completely designed and commissioned with necessary instrumentation schemes for fan stage performance evaluation.
Similarly, I was responsible for the test rig preparation, test rig health (vibration) monitoring (data acquisition and analysis), and conducting experiments for the technology demonstration program on the design and development of the aerodynamically advanced lightweight composite (non-metallic) blades for the transonic axial flow fans/compressors.
References
1. S Satish Kumar, D. B. Alone, M. T. Shobhavathy, J. R. Reddy, L. Kumar, S. Jana, S B Kandagal, R. Ganguli, “Aeroelastic Aspects of Axial Compressor Stage With Self-Recirculating Casing Treatment,” ASME Journal of Turbomachinery Vol. 144(6), 061008, 2022. Impact Factor: 1.7, Citations: 4
2. S Satish Kumar, D. B. Alone, M. T. Shobhavathy, J. R. Reddy, L. Kumar, R. Ganguli, S. B. Kandagal and S. Jana, “Aerodynamic Behavior of a Transonic Axial Flow Compressor Stage with Self-Recirculating Casing Treatment,” Aerospace Science and Technology Vol. 112, 106587, 2021. Impact Factor: 5.6, Citations: 17
3. S Satish Kumar, Dilipkumar Bhanudasji Alone, Shobhavathy M. Thimmaiah, Janaki Rami Reddy Mudipalli, Ranjan Ganguli, S. B. Kandagal, Soumendu Jana, “Aerodynamic characterization of a transonic axial flow compressor stage – with asymmetric tip clearance effects,” Aerospace Science and Technology Vol. 82–83, PP: 272–283, 2018. Impact Factor: 5.6, Citations: 23
4. S Satish Kumar, Ravi J. Chotalia, Soumendu Jana, Ranjan Ganguli, S. B. Kandagal, “Single Stage Axial Compressor Stability Management with Self-Recirculating Casing Treatment,” AIAA Science and Technology Forum and Exposition 2019, January 7–11, 2019 San Diego, California.
5. S Satish Kumar, Ranjan Ganguli, S B Kandagal, Soumendu Jana, “Structural Dynamic Behavior of Axial Compressor Rotor”, GTINDIA2017-4715, Proceedings of the ASME 2017 Gas Turbine India Conference, December 7-8, 2017, Bangalore, India.
6. S Satish Kumar, Ranjan Ganguli, S B Kandagal, Soumendu Jana, “Flow Behavior in A Transonic Axial Compressor Stage”, GTINDIA2015-1231, Proceedings of the ASME 2015 Gas Turbine India Conference, December 1-3, 2015, Hyderabad, India.
7. S Satish Kumar, Dilipkumar Bhanudasji Alone, Shobhavathy Thimmaiah, Janaki Rami Reddy Mudipalli, Ranjan Ganguli, S B Kandagal, Soumendu Jana, “Experimental Investigation of Unsteady Flow in a Transonic Uni-stage Axial Compressor”, GTINDIA2014-8167, Proceedings of the ASME 2014 Gas Turbine India Conference, December 15-17, 2014, Delhi, India.
Research Proposal
Futuristic advanced airframe-propulsion concepts are going for fan boundary layer ingestion concepts. In conventional wing-mounted engine configurations, a part of the total energy dissipation occurs in the wake of the airframe elements, such as the fuselage and in the jets of the engines. In the BLI technique, boundary layer fluid from the airframe is energized by the propulsor that reduces the wake and jet dissipation, hence increasing the overall propulsive efficiency. As a result, less propulsive power is required to sustain the flight.
Many renowned scientists, professors, and industries across the globe are working on the proposed futuristic and advanced aircraft design concept with Fan boundary layer ingestion that has shown improvements in propulsive efficiency by energizing the boundary layer.
Higher velocities are induced on the boundary layer fluid due to fan suction pressure hence altering the boundary layer profile. The aft-mounted fan stage receives non-uniform inlet total pressure and velocity distribution that leads to a performance penalty for the fan. Moreover, the periodic unsteady blade loadings can have a detrimental impact on the aeroelastic aspects as well.
The objective of the proposal is to understand the complex flow physics involved in the fan stage due to distorted inlet flow, estimate the safe aerodynamic margin available, and develop a suitable flow control technique. The stall limit/ operating margin will be established at various operating speeds for the fan stage with BLI. A flow control technique will be developed to overcome the drop in fan stage performance due to inlet distortion due to fan BLI. The knowledge gained from this study would be helpful in developing new fan stage configurations with BLI without sacrificing the stall margin.
I have 15 years of experience in carrying out experimental and numerical studies on transonic axial compressor stage and fan performance evaluations. At present, CSIR-NAL does not have the capability of using fan propulsors with boundary layer ingestion. This fellowship would provide experience in designing and understanding the fan BLI concept, which would be highly valuable to CSIR-NAL and other aircraft manufacturers in the country.
With my research experience at Propulsion Division, I am well equipped with the skill set required to accomplish the aforementioned research work. My fundamental research works on stall margin improvement studies on axial compressors will immensely aid in addressing the proposed research. I look forward to working closely with a number of fellow researchers toward understanding complex flows and developing solutions for challenging practical problems involved with fan BLI. I am sure that this opportunity could provide me with the right kind of research atmosphere to enrich my technical skills in the area.
Enclose separate sheet Research Statement and Proposal - Fan_BLI_1.pdf (94.65 KB) -
Please give one page write-up on the novelty of the research topic
Modern aviation is confronted with the pressing need for more sustainable and eco-friendly propulsion solutions. Fan Boundary Layer Ingestion (BLI) is a unique approach, especially for aircraft with fuselage aft-mounted engines/ propulsors. The BLI technique promises significant enhancement of the efficiency and performance of aero-engines.
This approach is being widely studied and proposed in electric aircraft propulsion such as hybrid and blended wing bodies, aircraft with distributed propulsion, NASA’s STARC-ABL single aisle 150-passenger class commercial transport electric aircraft, Cambridge-MIT Silent blended wing Aircraft, and the D8 “double-bubble” with a wide fuselage.
Traditionally, the boundary layer air that accumulates on the aircraft fuselage induces drag and is treated as a hindrance to performance. This novel approach involves ingesting the slow-moving boundary layer air, that naturally forms on the surface of an aircraft's fuselage during flight. By reimagining the traditional design and aerodynamics, the BLI technique seeks to optimize the utilization of this boundary layer air, thereby reducing fuel consumption, emissions, and noise while improving overall propulsion system efficiency.
The BLI works by having a portion of an aircraft’s boundary layer pass through the propulsor, thus adding propulsive power to the flow at a lower average velocity, decreasing the excess kinetic energy in the downstream jet and increasing propulsive efficiency, potentially reducing aircraft fuel burn. The BLI fan energizes the boundary layer flow and reduces the dissipation from the wake and jet, which in turn increases the overall propulsive efficiency. Low-speed wind tunnel experiments have reported a reduction of propulsive power of up to 10% using BLI.
The thick wall boundary layer (BL) at the fan inlet will produce substantially increased local loading at the blade tips and hence by BLI, reduces fan power but is limited by blade tip stall. The non-uniform radial flow distribution is detrimental to the fan performance margin.
The proposed research aims to assess the significant impact on fan aerodynamic margin available at various operating speeds due to fan boundary layer ingestion and develop a suitable mitigating flow control technique to overcome the deficit in performance/ stall margin. This work is particularly relevant to India and CSIR-NAL as it has embarked on major aircraft development programs such as SARAS MKII, Regional Transport Aircraft, and also programs on all-electric aircraft for the future wherein any additional gain in propulsive efficiency is always beneficial, thereby overcoming some of the limitations posed by battery technology.
- Linkage of the proposed work with priority Themes/Projects/Programmes of CSIR Fan propulsor with boundary layer ingestion (BLI) leads to additional performance improvements. The boundary layer fluid leads to non-uniform blade loading that can affect the aerodynamic margins. Performance evaluation of the fan stage with BLI would be helpful for defining the operating range of the engine. Also, the study of flow control mechanisms to overcome the drop in fan stage performance with BLI is critical. The outcome of the study would aid in the development and certification of various national aircraft programs such as SARAS, Regional Transport Aircraft, and future all-electric aircraft. The development of the technique to estimate and improve the Fan aerodynamic margin with BLI at CSIR-NAL will be useful in all these programs.
- Does the proposed research work involve IPR issues. If yes, has the host institute agreed to share the same with CSIR? No
- Could the proposed work be carried out within India at CSIR/non CSIR S&T institutions? There are no facilities/ institutes in India that can deal with fan stage with boundary layer ingestion, and the development of the evaluation technique will add value to the national aerospace programs.
- Please enclose separate sheet, if necessary
- Minimum period required for conducting proposed research. (2-6 months) 6 Months
- Relevance of proposed research with the activities/programmes of Lab/CSIR The proposed topic is of high relevance to CSIR-NAL as it has embarked on the aircraft development program. Understanding the fan flow behavior with BLI will pave the wave for incorporating the Fan propulsor indigenously with the benefit of BLI.
- Nature of expected output from the proposed study and its likely uses The proposed study will give impetus to understanding the effects of fan stage with BLI. Determination of the aerodynamic/ stall margins and implementation of a flow control technique for alleviating the distortion will aid in keeping the engine at safe operation limits.
- What benefits will accrue to CSIR by conducting this research work The effect of BLI on the fan stage and its implications is not well understood. The knowledge gained from the proposed work will be helpful for the national aircraft programs of CSIR-NAL.
- Commercialisation prospects of the proposed research work The technical know-how and experience will aid in DRDO-GTRE, HAL, or other private industries' aircraft and engine development activities
- Previous visits abroad during last 3 years Presented a research paper “Coupled Field Harmonic Analysis on a Flat Cantilever Plate for Deicing Studies” at the XVII Vibration Engineering & Technology of Machinery Conference, VETOMAC 2022, Dec 15 - 17, 2022, Institute of Engineering, Lalitpur, Nepal
- Any other relevant information you may feel necessary to give --
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signature
- Recommendations Of The Director Of The Lab/Instt
- a) Comments of the Director on the information given above by the applicant. The information provided is found correct.
- b) Remark of the Director on the potential and credentials of the applicant He has been working in the field of axial compressors/ fans for the past 15 years and is capable of working on fan BLI.
- c) Field of proposed study and its relation to the Lab's Priorities, particularly with regards to the Priority Themes/Projects/Prog Fan BLI studies are crucial for national programs such as SARAS, RTA, and future electric aircraft.
- d) Remarks on chosen place of work, special features of the concerned Lab Delft University of Technology and the fan group are one of the leading researchers in the field of Fan BLI techniques.
- e) Scientific and economic implication of the proposed work during the Fellowship (both on Indian as well as global) The fan performance evaluation with BLI will be helpful in designing airframes that can harness the benefits of improved propulsive efficiency. This technique can be implemented for all future aircraft programs in the country.
- f) Commercialisation prospect and likely users of the proposed research in the industrial sectors The Fan BLI technique will be used by all major aerospace organizations such as ADA, GTRE, and HAL.
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g) List of scientific peers, who can appreciate and comment on the scientific approach and overall utlity of the proposed work
Prof. A M Pradeep, IITB
Mr. Ajay Pratap, GTRE
Prof. Jayant Sabnis, MIT, USA
- Recommendations of the Director of the Lab/Instt
- Summary Sheet of the RRF Applicant fill Annexure III of the RRF Guidelines Annexure III - Summary Sheet.pdf (62.75 KB)
