Kaveri engine is an afterburning turbofan project developed by the GTRE, lab under DRDO, India. GTRE is now running two separate successor engine programmes, the K9+ and the K10. Click here to know more about kaveri Engine : http://www.drdo.gov.in/drdo/English/index.jsp?pg=Kaveri.jsp
A look into historical evolution of materials used for aircraft manufacturing by 5 aircraft manufacturers with consideration to material selection aspects of it.
Kaveri engine has 7 components, these components are Low Pressure and High Pressure Compressors, Annular Combustor, High Pressure and Low Pressure Turbines, Afterburner System, Engine Gearbox, Electro-Hydro Mechanical Control Systems, Kaveri Digital Engine Control Unit.
A look into historical evolution of materials used for aircraft manufacturing by 5 aircraft manufacturers with consideration to material selection aspects of it.
Kaveri engine has 7 components, these components are Low Pressure and High Pressure Compressors, Annular Combustor, High Pressure and Low Pressure Turbines, Afterburner System, Engine Gearbox, Electro-Hydro Mechanical Control Systems, Kaveri Digital Engine Control Unit.
SOLID ROCKET PROPULSION PPT ( SPACE SOLID ROCKET ).pptxAmarnathGhosh8
Rocket propulsion is a class of jet propulsion that produces thrust by ejecting burned propellant. The thrust is generated on the basis of Newton's third law of motion. Rocket propulsion systems can be broadly classified according to the type of energy source (chemical, solar, electric, or nuclear).
Pressure Distribution on an Airfoil
The team conducted the experiment to determine the effects of pressure distribution on lift and pitching moment and the behavior of stall for laminar and turbulent boundary layers in the USNA Closed-Circuit Wing Tunnel (CCWT) with an NACA 65-012 airfoil at a Reynolds number of 1,000,000. The airfoil was tested in a clean configuration at angles of attack of 0, 5, 8, 10, and 12 degrees. Tape added to the leading edge tripped the boundary layer, and pressure distributions were taken at 8, 10, and 12 degrees angle of attack. Experimental results showed a suction peak at less than 1% of chord, providing a beneficial test article for contrast between smooth and laminar boundary layer behavior at the stall condition. The maximum lift coefficient for the clean airfoil was 0.9 at 10 degrees angle of attack, and tripped airfoil reached a maximum lift coefficient of 1.03 at 12 degrees angle of attack, a 14% increase. These data were 10% lower than the empirical airfoil data found in Theory of Wing Sections from Abbott and von Doenhoff. Pitching moment coefficient about the quarter chord remained near zero below stall as expected for a symmetrical airfoil, but rapidly became negative after stall for experimental and empirical data. The airfoil exhibited a leading edge stall for both laminar and turbulent boundary layers.
A practical approach to bump test, learn why and how to perform bump test, when machine is off or if machine is running, equipment used for this session is CSI 2130 and CSI 2140, these are the universal setting and can be used for any of vibration analyzers such as SKF, SPM, Timken, Pruif Technique or any data acquisition unit having the option of bump test.
Energy saving in compressors and compressor performance assessment, process excellence involved in running compressor section. Energy optimization potential in compressors, leakage test of compressed air.
study of jet engines & how they works
1.History of jet engine 2. Introduction 3. Parts of jet engine 4. How a get engine works 5. Types of jet engine (i) Ramjet (ii) Turbojet (iii) Turbofan (iv) Turboprop (v) Turbo shaft 6.Comparison of Turbo Jet 7.Jet engines Vs Rockets 8.Difficulties 9.Suggestion for improvement 10. Merit and Demerits 11. Jet engine uses 12.Conclusion 13.Future vision
This Presentation gives a brief idea on turbojet engines, their components, working principle and also on the materials used in both the hot and cold sections of the engine, applications, etc..
Zee News - Sept16, 2008 - Investors in IPOs lost over Rs 5,000 cr in 2008Jagannadham Thunuguntla
"Out of 34 IPOs issued this calendar year, 26 of them closed below their issue price last week.
These IPOs have raised Rs 16,920 crore but the current value stands at Rs 11,562 crore. So they
are suffering a loss of 31.67 per cent," said Jagannadham Thunuguntla, Equity Head, NEXGEN
Capitals limited
SOLID ROCKET PROPULSION PPT ( SPACE SOLID ROCKET ).pptxAmarnathGhosh8
Rocket propulsion is a class of jet propulsion that produces thrust by ejecting burned propellant. The thrust is generated on the basis of Newton's third law of motion. Rocket propulsion systems can be broadly classified according to the type of energy source (chemical, solar, electric, or nuclear).
Pressure Distribution on an Airfoil
The team conducted the experiment to determine the effects of pressure distribution on lift and pitching moment and the behavior of stall for laminar and turbulent boundary layers in the USNA Closed-Circuit Wing Tunnel (CCWT) with an NACA 65-012 airfoil at a Reynolds number of 1,000,000. The airfoil was tested in a clean configuration at angles of attack of 0, 5, 8, 10, and 12 degrees. Tape added to the leading edge tripped the boundary layer, and pressure distributions were taken at 8, 10, and 12 degrees angle of attack. Experimental results showed a suction peak at less than 1% of chord, providing a beneficial test article for contrast between smooth and laminar boundary layer behavior at the stall condition. The maximum lift coefficient for the clean airfoil was 0.9 at 10 degrees angle of attack, and tripped airfoil reached a maximum lift coefficient of 1.03 at 12 degrees angle of attack, a 14% increase. These data were 10% lower than the empirical airfoil data found in Theory of Wing Sections from Abbott and von Doenhoff. Pitching moment coefficient about the quarter chord remained near zero below stall as expected for a symmetrical airfoil, but rapidly became negative after stall for experimental and empirical data. The airfoil exhibited a leading edge stall for both laminar and turbulent boundary layers.
A practical approach to bump test, learn why and how to perform bump test, when machine is off or if machine is running, equipment used for this session is CSI 2130 and CSI 2140, these are the universal setting and can be used for any of vibration analyzers such as SKF, SPM, Timken, Pruif Technique or any data acquisition unit having the option of bump test.
Energy saving in compressors and compressor performance assessment, process excellence involved in running compressor section. Energy optimization potential in compressors, leakage test of compressed air.
study of jet engines & how they works
1.History of jet engine 2. Introduction 3. Parts of jet engine 4. How a get engine works 5. Types of jet engine (i) Ramjet (ii) Turbojet (iii) Turbofan (iv) Turboprop (v) Turbo shaft 6.Comparison of Turbo Jet 7.Jet engines Vs Rockets 8.Difficulties 9.Suggestion for improvement 10. Merit and Demerits 11. Jet engine uses 12.Conclusion 13.Future vision
This Presentation gives a brief idea on turbojet engines, their components, working principle and also on the materials used in both the hot and cold sections of the engine, applications, etc..
Zee News - Sept16, 2008 - Investors in IPOs lost over Rs 5,000 cr in 2008Jagannadham Thunuguntla
"Out of 34 IPOs issued this calendar year, 26 of them closed below their issue price last week.
These IPOs have raised Rs 16,920 crore but the current value stands at Rs 11,562 crore. So they
are suffering a loss of 31.67 per cent," said Jagannadham Thunuguntla, Equity Head, NEXGEN
Capitals limited
From Elvis Presley to Oscar Wilde this huge collection of famous travel quotes will serve to inspire you to explore more of this wonderful world we live in. Read more > https://www.mercuryholidays.co.uk/oyster/features/70-top-travel-quotes-holiday-inspiration/
La Junta de Castilla y León, dentro del marco de actuaciones de la Estrategia Regional para la Sociedad Digital
del Conocimiento de Castilla y León 2007-2013 (en adelante ERSDI), ha puesto en marcha una serie de iniciativas
para impulsar el uso inteligente de las Nuevas Tecnologías como herramientas clave para el correcto disfrute
de los servicios y contenidos que nos ofrece la Sociedad Digital del Conocimiento.
Concept Study for Adaptive Gas Turbine Rotor Bladetheijes
Articulating the pitch angle of a turbine blade can improve performance by maintaining optimum design incidence and thus reduce the probability of flow separation and thermal stresses developed due to aerothermal loads for variable speed gas turbine engine applications. Potential benefits to Army Aviation are highly efficient (aerodynamically) turbine blades, possible reduction of the need for active blade cooling and thermal barrier coatings, increased fuel efficiency, power density, and the ability to fly faster and longer. The goal of this effort is to assess the benefit and feasibility of an adaptable variable pitch turbine blade for maintaining attached flow and optimal thermal design for a gas turbine engine. A technology concept study has been conducted to enable a viable adaptable turbine rotor blade that can enhance the performance and efficiency of future aircraft gas turbine engines. A typical aircraft turbine blade is used for this technology concept study. An adaptable turbine rotor blade, if made feasible, can lead to a leap ahead technology innovation in improving part-load efficiency of gas turbine engines.
International Journal of Engineering and Science Invention (IJESI) is an international journal intended for professionals and researchers in all fields of computer science and electronics. IJESI publishes research articles and reviews within the whole field Engineering Science and Technology, new teaching methods, assessment, validation and the impact of new technologies and it will continue to provide information on the latest trends and developments in this ever-expanding subject. The publications of papers are selected through double peer reviewed to ensure originality, relevance, and readability. The articles published in our journal can be accessed online.
We supply Various Performance, Fatigue Test Machine,
Automotive, Bike, Vehicle Parts Test Facilities
Bearing, Gear, Joint, Coupling, Transmission Test Bench
Dynamometer: for Electric Motor, Engine, Generator Brake Test
Hydraulic Testing Equipments: Pump, Valve, Pipe Test
Shaking Table, Seismic Simulator
Automatic Assembly Line
Review Paper on New Automotive Camless Engineijtsrd
Internal combustion engine occupies a significant spot in present day. with the most recent plan alteration in different part being advanced to improve the efficiency and generally speaking performance, one segment has been kept untouched that is camshaft. Cam control the breathing channels of the engine that is the planning of valves through which fuel air mixture enters and fumes is driven out. with help of push rods , rocker arms, stiff springs. With increasing performance demands engine specialists and researchers over the world are perusing radical cam less structure which promises to give ICEs a greater improvement in effectiveness. The fantasy about accomplishing cam less technology is shutting reality at rapid rate. With cam less technology put into practice, the engine power can be improved, pollutant emissions could be controlled and better mileage is acquired, in addition to that the whole mechanism of pulley or belt drive is replaced by the camless engine with greater efficiency than earlier i.e intake and exhaust of the IC engine by camless actuation technology with the camless engine variable valve timing also controls the intake and exhaust gas recirculation. Its one of the major advantage is it offers continously variable and independent control of all types of motion. Priyanshu Kumar Tiwari | Pushkar Verma | Prince Tiwari | Vijay Kumar Gupta ""Review Paper on New Automotive 'Camless Engine'"" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-4 | Issue-2 , February 2020,
URL: https://www.ijtsrd.com/papers/ijtsrd29892.pdf
Paper Url : https://www.ijtsrd.com/engineering/automotive-engineering/29892/review-paper-on-new-automotive-camless-engine/priyanshu-kumar-tiwari
Propulsion Selection and Analysis for Unmanned Aerial Vehicles for SAE Aero D...theijes
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
DYNAMIC ANALYSIS OF ENGINE BLOCK FOR SELECTION OF SUITABLE MATERIAL FOR COST ...Ijripublishers Ijri
The Aim of this project is to design a combustion chamber using Pro-E and perform analysis using ANSYS software.
The analysis of the combustion chamber is done by using different materials. By conducting the above analysis on the
combustion chamber combustion rate, pressure and temperature gradient conditions are found and the best material
for the combustion chamber is suggested.
Thermal analysis is conducted to find heat dissipation rate in engine block with the variation of materials Structural
and fatigue analysis(dynamic) is conduct on engine block at working load conditions to evaluate and compare stress,
strain, deformation and fatigue life with the variation of materials.
Frequency analysis is conducted on engine block with the variation of materials to evaluate frequency,
Using these values material selection will be done, the value should be nearby previous one (cast iron) maximum accepted
variation value 65HZ.
Development of a 300 kWe Integrated Axial Turbine and Generator for ORC Appli...Keith D. Patch
2nd International Seminar on ORC Power Systems: Turbo Expanders II, Rotterdam, The Netherlands
Publisher: ASME, International Gas Turbine Institute (IGTI)
Abstract
Concepts NREC has completed its design and development of an integrated high speed axial turbine and permanent magnet generator. The Turbine –Generator Unit (TGU) is ideal for ORC applications for its compactness, reliability, and versatility. The 20,000 rpm TGU does not use a shaft seal or gearbox and the generator is evaporatively cooled using the ORC working fluid. The TGU is designed with the intent of having the same turbine housing and generator used with a range of operating ORC fluid operating pressures and temperatures to enable its wide spread use in a variety of ORC heat recovery applications. The rotor and nozzle stators are changed to aerodynamically optimize the performance of the turbine at different ORC fluid operating conditions and flow rates. The output voltage of the generator can range from 300 to 480 VAC and at 50 hz and 60 hz. This facilitates its use in waste heat recovery applications throughout the world. This technical paper will review the mechanical and electrical design features of the turbine-generator unit.
The 15 m Sarvatra bridging system is capable of bridging both dry and wet gaps. All user trials comprising four phases have been completed and the system has been accepted by the Army for introduction into the Services.
http://www.drdo.gov.in/drdo/pub/techfocus/feb02/Mobile.htm
Agni-II is a 2 stage, solid fuelled, road and rail mobile, medium range ballistic missile. It is 2000 km range nuclear weapon capable missile with secure delivery system.
http://www.drdo.gov.in/drdo/English/index.jsp?pg=agni2.jsp
(MBT) Arjun is a third generation main battle tank developed by India's Defence Research and Development Organization (DRDO), for the Indian Army. It is a multi-laboratory programme of DRDO with CVRDE with superior fire power, high mobility, and excellent protection
LCA Tejas, India's first indigenous Light Combat Aircraft (LCA) is a single engine powered multi-role jet fighter with tailless, compound delta wing design developed by DRDO
http://www.drdo.gov.in/drdo/English/index.jsp?pg=LCA.jsp
Akash is an all weather area air defence weapon system for defending vulnerable areas against medium range air targets penetrating from low, medium and high altitudes. The system is designed to neutralize multiple aerial targets attacking from several directions simultaneously. The system is autonomous and its operation is fully automated.
http://www.drdo.gov.in/drdo/English/bnews/jan08/akash_test.htm
Abhay tank is futuristic infantry combat vehicle (ICV) developed by DRDO, India as a technology demonstrator for replacement of BMP-II vehicle.It led to development of FICV in Public-Private Partnership mode
http://www.drdo.gov.in/drdo/English/index.jsp?pg=Abhay.jsp
Agni 5 is a 3 stage solid fuelled, road mobile, intercontinental ballistic missile. It is 5,800 km range nuclear weapon capable missile with durability and operational flexibility
http://www.drdo.gov.in/drdo/English/index.jsp?pg=agni_5.jsp
Smart TV Buyer Insights Survey 2024 by 91mobiles.pdf91mobiles
91mobiles recently conducted a Smart TV Buyer Insights Survey in which we asked over 3,000 respondents about the TV they own, aspects they look at on a new TV, and their TV buying preferences.
Epistemic Interaction - tuning interfaces to provide information for AI supportAlan Dix
Paper presented at SYNERGY workshop at AVI 2024, Genoa, Italy. 3rd June 2024
https://alandix.com/academic/papers/synergy2024-epistemic/
As machine learning integrates deeper into human-computer interactions, the concept of epistemic interaction emerges, aiming to refine these interactions to enhance system adaptability. This approach encourages minor, intentional adjustments in user behaviour to enrich the data available for system learning. This paper introduces epistemic interaction within the context of human-system communication, illustrating how deliberate interaction design can improve system understanding and adaptation. Through concrete examples, we demonstrate the potential of epistemic interaction to significantly advance human-computer interaction by leveraging intuitive human communication strategies to inform system design and functionality, offering a novel pathway for enriching user-system engagements.
GDG Cloud Southlake #33: Boule & Rebala: Effective AppSec in SDLC using Deplo...James Anderson
Effective Application Security in Software Delivery lifecycle using Deployment Firewall and DBOM
The modern software delivery process (or the CI/CD process) includes many tools, distributed teams, open-source code, and cloud platforms. Constant focus on speed to release software to market, along with the traditional slow and manual security checks has caused gaps in continuous security as an important piece in the software supply chain. Today organizations feel more susceptible to external and internal cyber threats due to the vast attack surface in their applications supply chain and the lack of end-to-end governance and risk management.
The software team must secure its software delivery process to avoid vulnerability and security breaches. This needs to be achieved with existing tool chains and without extensive rework of the delivery processes. This talk will present strategies and techniques for providing visibility into the true risk of the existing vulnerabilities, preventing the introduction of security issues in the software, resolving vulnerabilities in production environments quickly, and capturing the deployment bill of materials (DBOM).
Speakers:
Bob Boule
Robert Boule is a technology enthusiast with PASSION for technology and making things work along with a knack for helping others understand how things work. He comes with around 20 years of solution engineering experience in application security, software continuous delivery, and SaaS platforms. He is known for his dynamic presentations in CI/CD and application security integrated in software delivery lifecycle.
Gopinath Rebala
Gopinath Rebala is the CTO of OpsMx, where he has overall responsibility for the machine learning and data processing architectures for Secure Software Delivery. Gopi also has a strong connection with our customers, leading design and architecture for strategic implementations. Gopi is a frequent speaker and well-known leader in continuous delivery and integrating security into software delivery.
Observability Concepts EVERY Developer Should Know -- DeveloperWeek Europe.pdfPaige Cruz
Monitoring and observability aren’t traditionally found in software curriculums and many of us cobble this knowledge together from whatever vendor or ecosystem we were first introduced to and whatever is a part of your current company’s observability stack.
While the dev and ops silo continues to crumble….many organizations still relegate monitoring & observability as the purview of ops, infra and SRE teams. This is a mistake - achieving a highly observable system requires collaboration up and down the stack.
I, a former op, would like to extend an invitation to all application developers to join the observability party will share these foundational concepts to build on:
UiPath Test Automation using UiPath Test Suite series, part 4DianaGray10
Welcome to UiPath Test Automation using UiPath Test Suite series part 4. In this session, we will cover Test Manager overview along with SAP heatmap.
The UiPath Test Manager overview with SAP heatmap webinar offers a concise yet comprehensive exploration of the role of a Test Manager within SAP environments, coupled with the utilization of heatmaps for effective testing strategies.
Participants will gain insights into the responsibilities, challenges, and best practices associated with test management in SAP projects. Additionally, the webinar delves into the significance of heatmaps as a visual aid for identifying testing priorities, areas of risk, and resource allocation within SAP landscapes. Through this session, attendees can expect to enhance their understanding of test management principles while learning practical approaches to optimize testing processes in SAP environments using heatmap visualization techniques
What will you get from this session?
1. Insights into SAP testing best practices
2. Heatmap utilization for testing
3. Optimization of testing processes
4. Demo
Topics covered:
Execution from the test manager
Orchestrator execution result
Defect reporting
SAP heatmap example with demo
Speaker:
Deepak Rai, Automation Practice Lead, Boundaryless Group and UiPath MVP
Encryption in Microsoft 365 - ExpertsLive Netherlands 2024Albert Hoitingh
In this session I delve into the encryption technology used in Microsoft 365 and Microsoft Purview. Including the concepts of Customer Key and Double Key Encryption.
Generative AI Deep Dive: Advancing from Proof of Concept to ProductionAggregage
Join Maher Hanafi, VP of Engineering at Betterworks, in this new session where he'll share a practical framework to transform Gen AI prototypes into impactful products! He'll delve into the complexities of data collection and management, model selection and optimization, and ensuring security, scalability, and responsible use.
Essentials of Automations: Optimizing FME Workflows with ParametersSafe Software
Are you looking to streamline your workflows and boost your projects’ efficiency? Do you find yourself searching for ways to add flexibility and control over your FME workflows? If so, you’re in the right place.
Join us for an insightful dive into the world of FME parameters, a critical element in optimizing workflow efficiency. This webinar marks the beginning of our three-part “Essentials of Automation” series. This first webinar is designed to equip you with the knowledge and skills to utilize parameters effectively: enhancing the flexibility, maintainability, and user control of your FME projects.
Here’s what you’ll gain:
- Essentials of FME Parameters: Understand the pivotal role of parameters, including Reader/Writer, Transformer, User, and FME Flow categories. Discover how they are the key to unlocking automation and optimization within your workflows.
- Practical Applications in FME Form: Delve into key user parameter types including choice, connections, and file URLs. Allow users to control how a workflow runs, making your workflows more reusable. Learn to import values and deliver the best user experience for your workflows while enhancing accuracy.
- Optimization Strategies in FME Flow: Explore the creation and strategic deployment of parameters in FME Flow, including the use of deployment and geometry parameters, to maximize workflow efficiency.
- Pro Tips for Success: Gain insights on parameterizing connections and leveraging new features like Conditional Visibility for clarity and simplicity.
We’ll wrap up with a glimpse into future webinars, followed by a Q&A session to address your specific questions surrounding this topic.
Don’t miss this opportunity to elevate your FME expertise and drive your projects to new heights of efficiency.
Key Trends Shaping the Future of Infrastructure.pdfCheryl Hung
Keynote at DIGIT West Expo, Glasgow on 29 May 2024.
Cheryl Hung, ochery.com
Sr Director, Infrastructure Ecosystem, Arm.
The key trends across hardware, cloud and open-source; exploring how these areas are likely to mature and develop over the short and long-term, and then considering how organisations can position themselves to adapt and thrive.
The Art of the Pitch: WordPress Relationships and SalesLaura Byrne
Clients don’t know what they don’t know. What web solutions are right for them? How does WordPress come into the picture? How do you make sure you understand scope and timeline? What do you do if sometime changes?
All these questions and more will be explored as we talk about matching clients’ needs with what your agency offers without pulling teeth or pulling your hair out. Practical tips, and strategies for successful relationship building that leads to closing the deal.
A tale of scale & speed: How the US Navy is enabling software delivery from l...sonjaschweigert1
Rapid and secure feature delivery is a goal across every application team and every branch of the DoD. The Navy’s DevSecOps platform, Party Barge, has achieved:
- Reduction in onboarding time from 5 weeks to 1 day
- Improved developer experience and productivity through actionable findings and reduction of false positives
- Maintenance of superior security standards and inherent policy enforcement with Authorization to Operate (ATO)
Development teams can ship efficiently and ensure applications are cyber ready for Navy Authorizing Officials (AOs). In this webinar, Sigma Defense and Anchore will give attendees a look behind the scenes and demo secure pipeline automation and security artifacts that speed up application ATO and time to production.
We will cover:
- How to remove silos in DevSecOps
- How to build efficient development pipeline roles and component templates
- How to deliver security artifacts that matter for ATO’s (SBOMs, vulnerability reports, and policy evidence)
- How to streamline operations with automated policy checks on container images
GraphRAG is All You need? LLM & Knowledge GraphGuy Korland
Guy Korland, CEO and Co-founder of FalkorDB, will review two articles on the integration of language models with knowledge graphs.
1. Unifying Large Language Models and Knowledge Graphs: A Roadmap.
https://arxiv.org/abs/2306.08302
2. Microsoft Research's GraphRAG paper and a review paper on various uses of knowledge graphs:
https://www.microsoft.com/en-us/research/blog/graphrag-unlocking-llm-discovery-on-narrative-private-data/
Quantum Computing: Current Landscape and the Future Role of APIs
Kaveri engine- Kaveri Engine DRDO
1. BULLETIN OF DEFENCE RESEARCH AND
DEVELOPMENT ORGANISATION
ISSN : 0971-4413
Technology
Vol. 17 No. 5 October 2009
Technology
GAS TURBINE RESEARCH
AS TURBINES have become essential power plants of
powerful military equipment like
aircraft, naval ships and tanks.GThe required precision manu-
facturing for components
and temperature-resistant
alloys necessary for high
efficiency often makes the
construction of a simple
turbine more complicated
t h a n p i s t o n e n g i n e s .
Defence Research and Develop-
ment Organisation (DRDO) is pioneering the
design and development of aero and marine gas
turbine engines for indigenous defence applications
besides research work in the areas of aero engine sub-
systems. DRDO has also established the requisite state-of-the-
art testing and prototype manufacturing facilities for components
andfull-scaleengines.
Gas Turbine Research Establishment (GTRE), Bengaluru, a constituent laboratory of DRDO, is entrusted with the
design and development of Kaveri engine which is an augmented low bypass twin spool turbofan engine of 80 kN thrust
class. The engine cycle is based on a detailed system analysis culminating into a potential power plant for the Indian Light
Combat Aircraft Tejas. The engine incorporates flat-rated characteristics to pre-empt and mitigate the thrust drop due to
high ambient intake temperature and/or high forward speed. Twin-lane full authority digital engine control with an
adequatemanualbackupisasalientdesignfeatureofKaveriengine.
Kaveri engines have been tested both in normally aspirated and with limited high pressure/temperature entry
conditionsformorethan1800h.Stringentstructural(safetyandlife)andaerodynamictestshavetakenupasapreludeto
officialaltitudetest,flyingtestbedtrialsandacceleratedmissiontestsleadingtoenginecertificationforairworthiness.
2. Technology
02
October09
KAVERI ENGINE COMPONENTS
Low Pressure and High Pressure Compressors
Annular Combustor
High Pressure and Low Pressure Turbines
Three-stage axial flow low
pressure (LP) compressor has
been designed with a mass
flow rate of 78 kg/s; pressure
ratio of 3.4; isentropic
efficiency of 85 per cent; and
surge margin in excess of
20 per cent. Design validation
of LP compressor has been
done for aerodynamic and
structural tests for life and
safety and the first rotor for bird
impactcharacterisation.
Six-stage axial flow high pressure (HP) compressor has been designed for a mass flow rate of 66 kg/s; pressure ratio
of6.4;isentropicefficiencyof85percent;andsurgemargininexcessof23percent.Designmethodologyisbasedon3-D
Navier Stokes code. Design validation of the HP compressor has been done for aerodynamic and structural tests for life
andsafety.
High intensity annular combustor has been designed for combustion
efficiency greater than 99 per cent, circumferential pattern factor of
0.35andradialpatternfactorof 0.14.Designanddevelopmentisbased
on computational fluid dynamics (CFD), empirical relations, water
analogy,andaero-thermaltestsathighpressure,hightemperatureand
altitudeconditionsbesidesextensivestructuralanalysis.
Single-stage cooled high pressure turbine has been designed for an
isentropic efficiency of 85 per cent and a maximum turbine entry
temperature (TET) of 1700 K. Navier Stokes codes such as TASC flow and
NUMECAhavebeenusedfordesignandanalysis.TheLPturbinerotorstage
isunshroudedwithanisentropicefficiencyof85percent.
HP compressor rotor assembly
Annular combustor
HP turbine rotor assembly
LP compressor rotor assembly
3. AfterburnerSystem
EngineGearbox
Electro-Hydro Mechanical Control Systems
The afterburner system (an additional component
added to some jet engines, primarily those on military
supersonic aircraft) provides a thrust boost of 60 per cent
over and above maximum dry thrust at an efficiency of
90 per cent, consistent light up from sea level to 11 km
altitude and stability besides buzz and screech free
operation. The burner has been designed using CFD tools
suchasFLUENTandStar-CD.
Engine gearbox (EGB) with a power rating of about
700 HP provides drive to 12 accessories of aircraft and
engineinthespeedrangeof5600-30000rpm.Castoutof
aluminium alloy, the EGB weighs less than 57 kg. It has
been tested for endurance and performance under
vibration, 'g' loads, attitude, and high and low
environmentaltemperatureconditions.
Integrated nozzle actuating system (INAS)
is used for actuation and control of the fully
variable convergent-divergent (CD) exhaust
nozzle to achieve optimum engine
performance (thrust and specific fuel
consumption) throughout the flight envelope.
INAS comprises four mechanically
synchronised hydraulic actuators (each
actuator with a load carrying capacity of 50 kN)
driven by engine gearbox-mounted integrated
hydraulicpowerpack.
October09
03
Afterburner system
Engine jet pipe with INAS and CD nozzle
Engine gearbox
4. Technology
Variable Geometry (VG)
Actuating System has been
used for varying the inlet guide
vanes (IGV) and the first two
stator blade angles, which
control the air flow direction
through the high pressure
compressor for optimising the
engine performance and
enhancingtheoperability.
Main engine control unit
and re-heat control unit supply
the fuel to the main and re-heat
combustion systems at the
desiredpressureandflowwhileensuringsmoothlightupandaccelerationof theengine.
All the electro-hydro mechanical control systems are interfaced with Kaveri digital engine control unit (KADECU) for
properclosedloopcontroloftheenginethroughouttheflightenvelope.
Kaveri Digital Engine Control Unit
(KADECU) is a microprocessor-based
real-time embedded full authority
digital control system to execute the
engine control to get optimum thrust
within safety limits. Two such units have
been mounted on the Kaveri with one
under control and the other in hot
standby mode. KADECU performs
extensive built-in test and sensor data
validation to detect failure and record
off-line analysis. Real-time monitoring
allows acquisition of data from the
control units and enables the study of
the control system performance vis-à-vis
theenginebehaviour.
GTRE has set up extensive structural test facilities for structural integrity and life evaluation of various components
and sub-systems such as fan/compressor/turbine rotor discs and blades, transmission shafts, casings, piping, engine
gearbox,etc.
KaveriDigitalEngineControlUnit
STRUCTURAL TEST FACILITIES
04
October09
Kaveri engine control unitdigital
5. Cyclicspintestfacilityisusedfor
low-cycle fatigue life evaluation of
engine rotor discs and incorporates
fully automated motor-driven
system capable of providing
variable speeds. This facility
simulates various combinations of
speedandtemperature.
Torsional test facility is used to
evaluate fatigue life of rotor shafts
under simulated torsion, axial, and temperature load conditions. The facility is capable of applying desired load profile
alongwithminorcyclessuperimposed.
Dynamic foreign body
impact test facility is used for
impact tests with simulated
bird models fired at various
speeds on rotor blades, disc
and casings. It comprises a
compressor air operated bird
g u n a n d h i g h - s p e e d
photography cameras for
monitoring the tests, both
under static and dynamic
conditions.
Full-scalepowerabsorptiontestfacilityisusedforperformanceandendurancetestingofengineaccessory gearbox
alongwithvarious LineReplaceableUnits(accessories)mountedanddulyloadedusingwaterbrakedynamometer.
Attitude testing is performed to
validate the design of Kaveri's
gearbox under attitude conditions
experienced during the flight,
including inverted flights also.
Gearbox internals experience both oil
starvation and oil flooding depend-
ing on attitudes. Performance
evaluation of the lubrication system
is the point of focus during the
subjecttest.
The casing structural test facility equipped with fatigue-rated actuators is used for structural integrity assessment of
engine frames, rotor-support structures, and engine-mount points. The system facilitates programming of desired load
spectrum,executionandmonitoringofthetestsinbothstaticanddynamicmodes.
October09
05
Dynamic foreign body impact test facility Full-scale power absorption test facility
Cyclic spin test facility Torsional test facility
Attitude test facility Casing structural test facility
6. Technology
06
October09
AERODYNAMIC TEST FACILITIES
GTRE has established in-house facilities for aero-thermodynamic performance evaluation of critical modules such
as fan, compressor, turbine, combustor, and afterburner. These facilities are equipped with extensive instrumentation
anddataacquisitionsystemsforonlinemonitoringaswellasanalysis.
Compressortestfacilityisusedtoevaluatetheperformanceoffanandcompressormodules,both underdesignand
off-designconditions.
Combustor test facility is used for evaluation of combustor system performance, both under design and off-design
conditionsofpressure,temperature andairflow.
Cold turbine test facility is used for evaluation of turbine module performance, both under design and off-design
conditions of pressure, temperature and air flow. It employs an electro-hydraulic dynamometer for power
absorption.
Afterburner test rig is used for test and evaluation of scaled-down model of engine afterburner, both under
simulatedscreechandbuzzconditionswithseveralpilotignitionsystemconfigurations.
Compressor test facility Combustor test facility
Cold turbine test facility Afterburner test facility
7. ENGINE TEST FACILITIES
SIMULATION AND ANALYSIS FACILITIES
GTRE has set up four engine
test cells for normally aspirated
condition and one test cell
capable of simulating inlet flight
conditions up to 0.4 Mach for
carryingoutperformancetests.
Test cells are designed for
normally aspirated testing
(thrust up to 20,000 kg) and
capable of carrying out engine
testing with afterburner system
(exhaust gas temperature of
>2000K).
SalientFeatures
Acoustically attenuated vertical intake and
exhaustsystems.
Roof-mounted thrust stand with off-line thrust
calibration.
Data Acquisition System (DAS) with provision of
1200channels.
Testcellsforenginebleedandpoweroff-take.
Customer bleed measuring facilities and
emergencyfuelsupply.
GTRE has also set up extensive simulation and analysis facilities to enable design evaluation, prototyping, digital
manufacturing, optimisation and assembly integration. These facilities consist of high-end hardware, and in-house and
commercialsoftwaretools.
GTRE has a computer-aided design and virtual reality laboratory for carrying out designing and validation tests. 3-D
CAD modelling of Kaveri for finite element analysis, mass property calculations, assembly integrity evaluations,
automated drafting, rapid prototyping and digital assembly manuals preparation, and enhanced visual feel of the
componentsandvirtualwalkthroughofassembliesweredoneatthislaboratory.
Computer-aidedDesignandVirtualRealityLaboratory
October09
07
Engine mounted in test cell
Engine test data acquisition system
8. Technology
08
October09
Computer-aidedEngineering
ComputationalFluidDynamics
Thecomputer-aidedengineeringfacilityisbeingusedforthefollowing:
Structural design analysis of gas
t u r b i n e c o m p o n e n t s u s i n g
NASTRAN, ANSYS, ABAQUS, LS-
DYNAandSAMCEFsoftware.
Kinematic design analysis of variable
CD nozzle and compressor variable
guide vane linkage mechanisms for
aero-engine.
Development of whole engine
model, engine static, dynamics and
blade-offsimulation.
L i f e p r e d i c t i o n o f e n g i n e
components employing in-house
practices and material characteri-
sation.
Methodology for life extension of
agingenginecomponents.
Damagetoleranceanalysisofthegasturbinecomponents.Designanddevelopmentofcompositestructures.
Computational fluid dynamics
(CFD) codes have been used
extensively for the design and
analysis of aero and marine
versions of Kaveri engine
modelling, CAD grid generation
and high performance compu-
ting form integral features of the
CFD and conjugate heat transfer
(CHT)analyses.
The parellel CFD software like
CFX TASC Flow, FLUENT, NUMECA
have been used for designing and
analysis of the engine compo-
nents.
Structural analysis of various components
Combustion flow analysis Turbine flow analysis
10. Technology
10
October09
RAPID PROTOTYPING
This scaled engineering prototype of Kaveri engine has been prepared using rapid prototyping technologies of
stereolithography and fused deposition modelling using 3-D CAD model data. The entire sequence of prototyping
activitiesincludepre-processing,partbuilding,post-processing, assemblyandmounting.
KAVERI MARINE GAS TURBINE ENGINE
The Kaveri Marine Gas Turbine (KMGT) engine, a derivative of Kaveri aero engine, is also being developed as a power
plant for propelling Indian naval ships. The gas generator of KMGT is derived from Kaveri aero engine, and a two-stage
freepowerturbinehasbeendesignedtotranslatethegaspowerintomechanicaloutputtodrivetheshippropeller.
11. SalientFeatures
Output : 15MWatISA-SLS
Specificfuelconsumption : 0.27kg/kW-hatISA-SLS
Fuel : Lowsulphurhighspeeddiesel(LSHSD)
Powerturbinespeed : 5800rpm
TET : 1560K(max)
KMGT engine has successfully demonstrated output
power and SFC exceeding the specification. Spin test of
power turbine disc has been carried out using dummy
blades simulating the centrifugal load. Forty hours of test
has been successfully completed at maximum rated
speed of power turbine, thereby demonstrating the
mechanicalintegrityofpowerturbinediscassembly.
GTRE has implemented Product
Lifecycle Management (PLM) framework
for the design and development of Kaveri
and its derivatives. Team centre suite of
product was used for PLM implemen-
tation with customisation for product
design, configuration management,
change management, CAD management,
and programme management. High
performance computing facility (P 690)
and ESS800-based data centre from IBM
formsthecorehardwareinfrastructure.
PRODUCT LIFECYCLE MANAGEMENT
October09
11
High performance computing facility (P 690)
Spin test facility
12. Technology
Dr AL Moorthy, Director, DESIDOC, Metcalfe House, Delhi
Dr BR Gandhe, Director of Armaments, DRDO
Director of Materials, DRDO
Shri R Shankar, Director of CV&E, DRDO Bhavan, New Delhi
Director of Naval Research & Development
DRDO
Shri Ranjit Elias, SO to SA to RM, DRDO Bhavan, New Delhi
Coordinator
Members
Bhavan, New Delhi
Dr Sudarshan Kumar, Bhavan, New Delhi
Cmde PK Mishra,
Bhavan, New Delhi
lEikndh;eaMy Editorial Committee
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Editor-in-Chief Assoc. Editor-in-Chief Editors Editorial Assistant Printing Distribution
AL Moorthy Shashi Tyagi B Nityanand Dipti Arora SK Gupta RP Singh
Manoj Kumar Hans Kumar
Printed & published by Director, DESIDOC, on behalf of DRDO
Air mass flow : 78 kg/s
Kaveri Engine—Salient Features
By-pass ratio : 0.2-0.24
Overall pressure ratio : 21.5
Turbine entry temperature (flat-rated) : 1487-1700 K
Maximum thrust (dry)-IRA, SL : 52 kN
Maximum thrust with afterburner-IRA, SL : 81 kN
SFC (dry) : 0.78 kg/h/kg
Maximum SFC with afterburner : 2.03 kg/h/kg
Thrust/weight ratio : 7.8