Advanced Propulsion System Design: Applications of CFD
|
|
- Ariel Martin
- 5 years ago
- Views:
Transcription
1 Advanced Propulsion System Design: Applications of CFD J. J. Isaac Head, Propulsion Division National Aerospace Laboratories Foundation Day Lecture: C- MMACS 15 TH September, 2006
2 Propulsion Trends Scramjet Ramjet Afterburning Turbojet Low Bypass Turbofan with Afterburner Low Bypass Turbofan High Bypass Turbofan Prop-fan Turboprop Piston-prop Propulsion innovations have been the fundamental drivers to progress in air transportation Mach Number
3 Propulsion Division R&D Activities Hypersonic Air Breathing Propulsion (Ramjet & Scramjet Combustor Technology) Advanced Gas Turbine Technology
4 Anderson s three dimensions of modern fluid dynamics Pure Experiment Pure Theory Computational Fluid Dynamics (CFD) Prandtl was able to see the solutions of the differential equations without calculating them ---- Werner Heisenberg Prandtl s rule Clean Aerodynamics Everyone believes experimental results except the person who performed the experiment and no one believes the numerical results except the person who performed the prediction!
5 C F D Advantages CFD can be used as a design tool CFD can be used as a research tool Provide virtual solutions for easy review / investigation Provide valuable flow visualization to explain experimental observations Excellent complementary tool to testing Issues: Prediction of transition from laminar to turbulent flow Calculation of separated flow and unsteady wakes Turbulence modeling Chemical Kinetics Grid Generation
6 Turbomachinery: Propulsion Technology Challenges - Fan, compressor, high-pressure turbine, low pressure turbine efficiency improvements through CFD and experimentation -Inlet, engine, control system compatibility; operability - Turbine life and cooling - Component reaibility Combustor - Development of a viable commercial design; new fuel injection, mixing, variable geometry, and high temperature walls with new ceramic matrix composite (CMC) materials -Validation of technology readiness - Combustor reliability and life Jet nozzle performance, acoustic, durability Materials Advanced digital controls Weight Manufacturing technology (Ref: Aeronautical Technologies for the 21 st Century: Committee on Aeronautical Technologies, Aeronautics and Space Engineering Board, National Research Council, USA)
7 High-Speed Computation for Propulsion! CFD and high-speed computation in general will be essential for new engine development in the coming decades, in order to shorten the time for development and to discover new design optima! For the foreseeable future in Propulsion, both CFD and experiments will be needed to efficiently apply results to meet design goals! Analysis codes are necessary to provide the basic predictive ability, at the finest level of detail, for the physics and chemistry underlying propulsion! Design codes are the essential direct tools for engine development; they should embody the best capabilities of analysis codes but, because of their different purpose, be far faster, easier to apply and therefore, necessarily less comprehensive and precise! Technical challenges for high-speed computation include " multistage turbomachinery flows with mixing and shock losses; " combustor design for low emissions, using codes that integrate chemical kinetics, fluid mechanics, heat transfer, materials and structures; " unsteady phenomenon fully represented in codes pertaining to new ideas about the stability and control of propulsion systems; and " acoustics and noise, which must- through CFD - be featured in the primary design process (Ref: Aeronautical Technologies for the 21 st Century: Committee on Aeronautical Technologies, Aeronautics and Space Engineering Board, National Research Council, USA)
8 Kaveri Engine for the LCA
9 Ignition and Combustion in an Afterburner and Main Combustor The problem of flame stabilization Flow velocities >> Flame propagation velocities of conventional fuels (kerosene, hydrogen) In a scramjet through flow velocities are over a 1 km/s, akin to lighting a match inside a tornado and somehow keeping it alight Fuel / air ratio Sheltered zone Heat loss
10 Hardware Quasi-morphological study CFD Study -Temperature contour at X/L = 0.36 plane (CFD ACE +) Kaveri ring-radial afterburner
11 Kaveri Full-Scale Afterburner Tests Full Scale AB Test Rig Flame Stabilizer & fuel ring assembly AB end-on view AB side view
12 CFD ANALYSIS OF GAS TURBINE COMBUSTOR : A CAD TO MESH TO CFD APPROACH Complete Sector View of Combustor
13 Animation of Velocity Vectors
14 Animation of Temperature Contours Axial Direction
15 Total Pressure Loss ( % ) PHOENICS Expt. CFD-ACE Pre Diff. Exit Outer Annulus Dump Diff Inner Annulus Dump Diff Exit Mass Flow Analysis ( % ) PHOENICS EXPT. Cold Flow (CFD-ACE) Hot Flow (CFD-ACE) Outer Inner Annulus Core
16 CFD as a Combustor Design Tool
17 K4 COMBUSTOR K9 MODIFIED COMBUSTOR
18 Enlarged Velocity Vectors near Primary Zone K4 Combustor K9 Modified
19 AVAILABLE CODES FOR TURBOMACHINERY FLOW ( 3D VISCOUS FLOW IN TURBOMACHINERY) DAWES CODE: un_b3d_ke Unsteady/Steady Flow, Structured H-Grid, Multistage, Options for Mixing Plane Treatment GENERAL PURPOSE CFD CODE: CFD-ACE+ - 3-D Navier-Stokes general purpose CFD code
20 3-Stage LP Compressor of a Gas-Turbine Engine Grid: 33(radial)x331(axial)x33(tangential) Fan axis Fig 2.0.1b Grid for 3-stage compressor Design Pressure Ratio=3.4
21 M At mid-pitch At mid-height Case A2 Fig Mach number contours on some planes.
22 3.5 LPC perfermance map Pressure ratio: Design speed 95% speed 90% speed A2 Design speed: rpm Pr. ratio mass flow in kg/s Pressure ratio Vs. Mass flow Efficiency Vs. Mass flow 90 LPC performance map efficiency Design speed 95% speed 90% speed Performance map for 3-stage compressor configuration mass flow in kg/s
23 AFCR(NAL) COMPRESSOR Rotor Stator AFCR(NAL) COMPRESSOR Pressure ratio 1.35 Design speed rpm Nominal tip clearance 0.8mm Number of blades (R/S) 21/18 Grid size # 33 x 246 x 33 Without Tip clearance ( 2,67,894 Cells) # 33 x 246 x 37 With Tip clearance (3,00,366 Cells) #9 Grids within the tip clearance Transonic AFCR compressor stage and grid
24 With 0.0mm TC With 0.8mm TC Velocity vectors on blade to blade plane near casing Comparison of Experimental and Predicted Performance for Transonic Axial Flow Compressor
25 CDNAL BLADE CASCADE CALCULATIONS Blade-to-blade Hub-to-tip Grid 31x91x31 Surface Mach number, M P-A(1.21)-I(43.7) S-A(1.21)-I(43.7) P-A(1.26)-I(43.7) S-A(1.26)-I(43.7) P-A(1.30)-I(43.7) S-A(1.30)-I(43.7) TCT-P-A(1.26)-I(43.7) TCT-S-A(1.26)-I(43.7) X/Cax Fig. Comparison of surface Mach number for CDNAL blade (AVDR=1.21,1.26,1.30; Grid=31x91x31)
26 DESIGN OF CDA PROFILE SECTION Section 1 MCA CDA d3 MCA and CDA-3 profiles 25 Y CDA Design MCAD3S1.GRF X 1.2 sec1 1 CDA-3 MCA 0.8 Surface Mach number distribution Mach no x/c
27 LP Compressor performance* with CD design for stator 3 90 Kaveri LPC efficiency MCA CDA-2 CDA-3 Efficiency Vs Mass flow Mass flow in kg/sec 4 Kaveri LPC Pressure ratio MCA CDA-2 CDA-3 Pressure ratio Vs Mass flow Mass flow in kg/sec * GTRE Results
28 1.4 GTRE KAVERI ENGINE FAN - MCA PROFILE OF IIIrd STATOR Surface Mach Number Distribution M1 = 0.76, M2 = & Beta1 = 43 Deg Mach Number CFD - Dawes Code TCT - EXPT X / Cax
29 NAL TRANSONIC CASCADE TUNNEL OIL FLOW VISUALISATION MCA Profile Separation Bubble Inlet
30 LOX First Rotor Cascade Assembly In TCT LOX First Rotor Cascade Assembly
31 1.8 LPSC - LOX FIRST ROTOR Surface Mach Number Distribution M1 = & M2 = & Beta1 = 68 Deg Mach Number CFD - Dawes Code Points - EXPT X / Cax
32 CODE Three dimensional viscous flow code CFD- ACE+ Pressure-based method SIMPLEC (Semi-Implicit Method for Pressure Linked Equations Consistent). Turbulence model k-ε Mass imbalance as low as %. Total - to-total Adiabatic Efficiency(%) Stagnation Pressure Ratio (P 02 /P 01 ) Without Tip Clearance (0mm) With 3% Tip Clearance (0.291mm) With 4.8% Tip Clearance (0.500mm) With 7.0% Tip Clearance (0.721mm) Where, D = Design point *Constant Tip Clearance (TYPE - I) Where, C = Choke point D = Design point S = Surge point 2 Without Tip Clearance (0mm) 1.5 With 3% Tip Clearance (0.291mm) With 4.8% Tip Clearance (0.500mm) 1 With 7.0% Tip Clearance (0.721mm) Surge Line for 4.8% Designed Tip Clearance 0.5 *Tip clearance is indicated as percent of blade height at exit. *Constant Tip Clearance (TYPE - I) S D D m θ0 ( δ )( kg s) Corrected Mass Flow Rate / C m θ 0 ( δ )( kg s) Corrected Mass Flow Rate / Tip Clearance or Gap TYPE I Constant Tip Gap Drop in Peak Efficiency ( η ) (%) TYPE - I TYPE - II Tip Clearance or Gap ( ) ( ) TYPE II Variable tip gap η= η without tip clearance η with tip clearance Tip Clearance (% of Blade Height at Exit) Constant tip clearance provides better performance compared to variable tip clearance
33
34
35 Supersonic Combustion ABLV Solid Model of Dual-mode Ramjet/Scramjet Combustor Intake Combustor Isolator Nozzle M=2 Strut base Kerosene / Hydrogen Flame Anchoring in cavity flame stabilizer Schlieren of cavity flame stabilizer Dual Mode Ramjet / Scramjet Combustor & Test rig Kerosene / hydrogen supersonic flame
36 Computation of supersonic cold cavity flow for scramjet velocity profile at different sections (xc measured from end of step; U/U1 scale for xc=10mm profile) y (m) U/U1 xc=10mm xc=20 xc=30 xc=40 xc=50 xc=60 xc=70 xc=80 xc=90 xc=100 xc=110 xc=120 xc=130 xc=140
37 Velocity Plot at different sections of slant wall distance from slant wall (m) V/Vinf x=85mm x=88mm x=91mm x=94mm x=97mm Static Pressure Profile at different sections of slant wall Distance from slant wall (m) P/Pin_air X=85mm X=88mm X=91mm X=94mm X=97mm Computation of supersonic combustion slant cavity flow for Scramjet Exit pressure profile Exit temperature profile
38 Small Gas Turbine Tomahawk Cruise Missile Distributed Vectored Propulsion
39 Hybrid Bearing Alternator Compressor FUEL Starting Motor SPECIFICATIONS: Power output-10kw Fuel-Natural Gas/LPG Rotational speed rpm Mass flow rate-0.13kg/s Compressor pressure ratio-3 Turbine inlet temperature-900c Compressor tip Dia-85mm Turbine tip Dia-110 Recuperator Effectiveness-85% Thermal efficiency-30% MGT Turbine Recuperator Gas Generator
40 Reverse Flow Annular Combustor for 10kW Micro Gas Turbine Application: Stationary Power Unit Specifications: Power output:10kw Fuel: Kerosene/LPG Mass flow rate: 0.13kg/s Compressor pressure ratio: 3 Turbine inlet temperature: 900 C Challenges: Getting satisfactory recirculation patterns Containing the flame inside the flame tube INLET EXIT CAD Model - Cut section Fuel injection Temperature contours Temperature contour just (45 degree segment downstream of atomisers Micro Gas Turbine Combustor
41 MICRO GAS TURBINE
42 SMALL GAS TURBINE ENGINE (Straight Jet) (Thrust = 2.25 kn, SFC =1.1 kg/hr/kg) 340 mm diameter* 670 mm length
43 Cavity Combustor Discrete fuel injection Temperature contours Continuous fuel injection Proposed New Concept: Annular Atomiser Velocity vectors near cavity CAD Model 2D - Cavity Combustor Flame from exit section * Circumferentially uniform Temp. distribution * Compact Combustor * Reduced hot spots
44 Aerodynamic Cavity Velocity contour animation Velocity vector animation
45 Cavity Combustor Experiment - Video
46 Annular Cavity Combustor Proposed Small Gas Turbine Engine CAD Model Test rig assembly CAD Model Annular Cavity Combustor Fabricated part cavity ring Applications: Small Gas Turbine Combustor Un-manned Air Vehicles Cruise Missiles
47 Concluding Remarks An overview of the state of practice of current CFD tools used for advanced propulsion system design and analysis at NAL has been presented. This included the validation requirements of CFD codes applicable to such advanced propulsion systems. The computational facilities made available by C-MMACS have been invaluable for these studies. Acknowledgements: C-MMACS; special mention Dr. Gangan Pratap, Mr. R. P. Thangavelu, This presentation has been based on the work carried out by the Scientists of the Propulsion Division; special mention Dr. T. R. Shebharkar, Mr. H. S. Muralidhara, Mr. Ashfaque Khan, Mr. Pratap Nayaka, Mr. BBC Kumar, Dr. S. Ramamurthy, Mr. KMM Swamy, Mr. Senthil Kumar, Mr. Dilip Kumar Alone, Mrs. M. T. Shobhavathy, Mr. P. Manjunath, Mr. C. Rajashekar, Mr. Jagannatha Rao, Mr. S. Venkatesh, Mr. V.S. Krishnakumar, Mr. Sathiyamurthy, Mr. Venu, Mr. G.S. Sreenath, Mr. M. Baskaran, Mr. J. Srinivas, Mr. M. Satish Kumar and Mr. ATLN Murthy
Design and Test of Transonic Compressor Rotor with Tandem Cascade
Proceedings of the International Gas Turbine Congress 2003 Tokyo November 2-7, 2003 IGTC2003Tokyo TS-108 Design and Test of Transonic Compressor Rotor with Tandem Cascade Yusuke SAKAI, Akinori MATSUOKA,
More informationAPPLICATION OF STAR-CCM+ TO TURBOCHARGER MODELING AT BORGWARNER TURBO SYSTEMS
APPLICATION OF STAR-CCM+ TO TURBOCHARGER MODELING AT BORGWARNER TURBO SYSTEMS BorgWarner: David Grabowska 9th November 2010 CD-adapco: Dean Palfreyman Bob Reynolds Introduction This presentation will focus
More informationEngine Performance Analysis
Engine Performance Analysis Introduction The basics of engine performance analysis The parameters and tools used in engine performance analysis Introduction Parametric cycle analysis: Independently selected
More informationIntroduction to Gas Turbine Engines
Introduction to Gas Turbine Engines Introduction Gas Turbine Engine - Configurations Gas Turbine Engine Gas Generator Compressor is driven by the turbine through an interconnecting shaft Turbine is driven
More informationExperimental Testing of a Rotating Detonation Engine Coupled to Nozzles at Conditions Approaching Flight
25 th ICDERS August 2 7, 205 Leeds, UK Experimental Testing of a Rotating Detonation Engine Coupled to Nozzles at Conditions Approaching Flight Matthew L. Fotia*, Fred Schauer Air Force Research Laboratory
More informationNumerical Simulation on the Pattern Factor of the Annular Combustor
Numerical Simulation on the Pattern Factor of the Annular Combustor Balakrishnan B.M 1, Mohana Priya G 2, Revathi M 3 Department of Mechanical Engineering, Mahendra Engineering College, Salem, India 1
More informationFLUIDIC THRUST VECTORING NOZZLES
FLUIDIC THRUST VECTORING NOZZLES J.J. Isaac and C. Rajashekar Propulsion Division National Aerospace Laboratories (Council of Scientific & Industrial Research) Bangalore 560017, India April 2014 SUMMARY
More informationDesign Rules and Issues with Respect to Rocket Based Combined Cycles
Respect to Rocket Based Combined Cycles Tetsuo HIRAIWA hiraiwa.tetsuo@jaxa.jp ABSTRACT JAXA Kakuda space center has been studying rocket based combined cycle engine for the future space transportation
More informationIn this lecture... Fixed and variable geometry nozzles Functions of nozzles Thrust vector control Thrust reversal Noise control
1 In this lecture... Nozzle: Fixed and variable geometry nozzles Functions of nozzles Thrust vector control Thrust reversal Noise control 2 Exhaust nozzles Nozzles form the exhaust system of gas turbine
More informationAnalysis of Scramjet Engine With And Without Strut
Analysis of Scramjet Engine With And Without Strut S. Ramkumar 1, M. S. Vijay Amal Raj 2, Rahul Mahendra Vaity 3 1.Assistant Professor NIT Coimbatore, 2. U.G.Student, NIT Coimbatore 3.U.G.Student MVJ College
More informationWelcome to Aerospace Engineering
Welcome to Aerospace Engineering DESIGN-CENTERED INTRODUCTION TO AEROSPACE ENGINEERING Notes 5 Topics 1. Course Organization 2. Today's Dreams in Various Speed Ranges 3. Designing a Flight Vehicle: Route
More informationProf. João Melo de Sousa Instituto Superior Técnico Aerospace & Applied Mechanics. Part B Acoustic Emissions 4 Airplane Noise Sources
Prof. João Melo de Sousa Instituto Superior Técnico Aerospace & Applied Mechanics Part B Acoustic Emissions 4 Airplane Noise Sources The primary source of noise from an airplane is its propulsion system.
More informationCFD Analyses of the Experimental Setup of a Slinger Combustor
CFD Analyses of the Experimental Setup of a Slinger Combustor Somanath K Bellad 1, 1 M Tech Student, Siddaganga Institute of Technology (SIT), Tumakuru, Karnataka Abstract: An annular combustor with rotating
More informationChapter 4 Lecture 16. Engine characteristics 4. Topics. Chapter IV
Chapter 4 Lecture 16 Engine characteristics 4 Topics 4.3.3 Characteristics of a typical turboprop engine 4.3.4 Characteristics of a typical turbofan engine 4.3.5 Characteristics of a typical turbojet engines
More informationIntroduction to Aerospace Engineering
Introduction to Aerospace Engineering Lecture slides Challenge the future 1 18-9-2011 Introduction to Aerospace Engineering AE1101ab - Propulsion Delft University of Technology Prof.dr.ir. Challenge JaccotheHoekstra
More informationInnovative Centrifugal Compressor Design
Innovative Centrifugal Compressor Design L. Tarnowski TURBOMECA groupe SAFRAN INTRODUCTION SP2 : IRA (Intercooled Recuperative Aero-engine) Task 2.2.5 HP Centrifugal Compressor Design The challenge is
More informationTHE EFFECT OF BLADE LEAN ON AN AXIAL TURBINE STATOR FLOW HAVING VARIOUS HUB TIP RATIOS. Dr. Edward M Bennett
THE EFFECT OF BLADE LEAN ON AN AXIAL TURBINE STATOR FLOW HAVING VARIOUS HUB TIP RATIOS Dr. Edward M Bennett ABSTRACT The effect of simple lean on an axial turbine stator was examined using a threedimensional
More informationJET AIRCRAFT PROPULSION
1 JET AIRCRAFT PROPULSION a NPTEL-II Video Course for Aerospace Engineering Students Bhaskar Roy and A M Pradeep Aerospace Engineering Department I.I.T., Bombay 2 Brief outline of the syllabus Introduction
More informationPower Cycles. Ideal Cycles, Internal Combustion
Gas Power Cycles Power Cycles Ideal Cycles, Internal Combustion Otto cycle, spark ignition Diesel cycle, compression ignition Sterling & Ericsson cycles Brayton cycles Jet-propulsion cycle Ideal Cycles,
More informationEffects of Dilution Flow Balance and Double-wall Liner on NOx Emission in Aircraft Gas Turbine Engine Combustors
Effects of Dilution Flow Balance and Double-wall Liner on NOx Emission in Aircraft Gas Turbine Engine Combustors 9 HIDEKI MORIAI *1 Environmental regulations on aircraft, including NOx emissions, have
More informationEngineering Success by Application of STAR-CCM+ for Modern Gas Turbine Design
STAR Japanese Conference 2013 December 3, Yokohama, Japan Engineering Success by Application of STAR-CCM+ for Modern Gas Turbine Design Norbert Moritz, Karsten Kusterer, René Braun, Anis Haj Ayed B&B-AGEMA
More informationPlasma Assisted Combustion in Complex Flow Environments
High Fidelity Modeling and Simulation of Plasma Assisted Combustion in Complex Flow Environments Vigor Yang Daniel Guggenheim School of Aerospace Engineering Georgia Institute of Technology Atlanta, Georgia
More informationAircraft Propulsion Technology
Unit 90: Aircraft Propulsion Technology Unit code: L/601/7249 QCF level: 4 Credit value: 15 Aim This unit aims to develop learners understanding of the principles and laws of aircraft propulsion and their
More informationAE 452 Aeronautical Engineering Design II Installed Engine Performance. Prof. Dr. Serkan Özgen Dept. Aerospace Engineering March 2016
AE 452 Aeronautical Engineering Design II Installed Engine Performance Prof. Dr. Serkan Özgen Dept. Aerospace Engineering March 2016 Propulsion 2 Propulsion F = ma = m V = ρv o S V V o ; thrust, P t =
More informationResearch in Internal and External Aerodynamics for the Next Generation of Effcient Aircraft
Research in Internal and External Aerodynamics for the Next Generation of Effcient Aircraft Huu Duc Vo Associate Professor Department of Mechanical Engineering École Polytechnique de Montréal 2017 National
More informationNumerical simulation of detonation inception in Hydrogen / air mixtures
Numerical simulation of detonation inception in Hydrogen / air mixtures Ionut PORUMBEL COMOTI Non CO2 Technology Workshop, Berlin, Germany, 08.03.2017 09.03.2017 Introduction Objective: Development of
More informationINSTITUTO TECNOLÓGICO DE AERONÁUTICA CENTER FOR REFERENCE ON GAS TURBINES GAS TURBINE GROUP
GAS TURBINE GROUP 2012 Background The Campus Engineering Departments Laboratories Center for Reference on Gas Turbines The Campus INSTITUTO TECNOLÓGICO DE AERONÁUTICA The Campus INSTITUTO TECNOLÓGICO DE
More informationNumerical Simulation of Gas Turbine Can Combustor Engine
Numerical Simulation of Gas Turbine Can Combustor Engine CH UMAMAHESHWAR PRAVEEN 1*, A HEMANTH KUMAR YADAV 2 1. Engineer, CDG BOEING Company, Chennai, India. 2. B.Tech Aeronautical Engineer 2012 passout,
More informationAE Aircraft Performance and Flight Mechanics
AE 429 - Aircraft Performance and Flight Mechanics Propulsion Characteristics Types of Aircraft Propulsion Mechanics Reciprocating engine/propeller Turbojet Turbofan Turboprop Important Characteristics:
More informationChapter 4 Estimation of wing loading and thrust loading - 10 Lecture 18 Topics
Chapter 4 Estimation of wing loading and thrust loading - 10 Lecture 18 Topics 4.15.3 Characteristics of a typical turboprop engine 4.15.4 Characteristics of a typical turbofan engine 4.15.5 Characteristics
More informationin ultra-low NOx lean combustion grid plate
CFD predictions of aerodynamics and mixing in ultra-low NOx lean combustion grid plate flame stabilizer JOSÉ RAMÓN QUIÑONEZ ARCE, DR. ALAN BURNS, PROF. GORDON E. ANDREW S. SCHOOL OF CHEMICAL AND PROCESS
More informationInvestigation of converging slot-hole geometry for film cooling of gas turbine blades
Project Report 2010 MVK160 Heat and Mass Transport May 12, 2010, Lund, Sweden Investigation of converging slot-hole geometry for film cooling of gas turbine blades Tobias Pihlstrand Dept. of Energy Sciences,
More informationCOMPUTATIONAL ANALYSIS OF SUPERSONIC COMBUSTION USING CAVITY BASED FUEL INJECTION WITH SPECIES TRANSPORT MODEL AT MACH NUMBER 4.
International Journal of Science, Environment and Technology, Vol. 3, No 3, 2014, 923 930 ISSN 2278-3687 (O) COMPUTATIONAL ANALYSIS OF SUPERSONIC COMBUSTION USING CAVITY BASED FUEL INJECTION WITH SPECIES
More informationANALYSIS OF BLADES OF AXIAL FLOW FAN USING ANSYS. Mahajan Vandana N.,* Shekhawat Sanjay P.
Research Article ANALYSIS OF BLADES OF AXIAL FLOW FAN USING ANSYS. Mahajan Vandana N.,* Shekhawat Sanjay P. Address for Correspondence Department of Mechanical Engg. S.S.B.T s College of Engg. and Technology,
More informationComputational Fluid Dynamics in Torque Converters: Validation and Application
Rotating Machinery, 9: 411 418, 2003 Copyright c Taylor & Francis Inc. ISSN: 1023-621X print DOI: 10.1080/10236210390241646 Computational Fluid Dynamics in Torque Converters: Validation and Application
More informationAerospace Propulsion Systems
Brochure More information from http://www.researchandmarkets.com/reports/1288672/ Aerospace Propulsion Systems Description: Aerospace Propulsion Systems is a unique book focusing on each type of propulsion
More informationEFFECT OF SURFACE ROUGHNESS ON PERFORMANCE OF WIND TURBINE
Chapter-5 EFFECT OF SURFACE ROUGHNESS ON PERFORMANCE OF WIND TURBINE 5.1 Introduction The development of modern airfoil, for their use in wind turbines was initiated in the year 1980. The requirements
More informationFoundations of Thermodynamics and Chemistry. 1 Introduction Preface Model-Building Simulation... 5 References...
Contents Part I Foundations of Thermodynamics and Chemistry 1 Introduction... 3 1.1 Preface.... 3 1.2 Model-Building... 3 1.3 Simulation... 5 References..... 8 2 Reciprocating Engines... 9 2.1 Energy Conversion...
More information17/11/2016. Turbomachinery & Heat Transfer Laboratory Faculty of Aerospace Engineering Technion Israel Institute of Technology, Israel
17/11/2016 Turbomachinery & Heat Transfer Laboratory Faculty of Aerospace Engineering Technion Israel Institute of Technology, Israel 1 Motivation New challenges rise due to increase in demands from small
More informationIn this lecture... Components of ramjets and pulsejets Ramjet combustors Types of pulsejets: valved and valveless, Pulse detonation engines
In this lecture... Components of ramjets and pulsejets Ramjet combustors Types of pulsejets: valved and valveless, ulse detonation engines Ramjet engines Ramjet engines consist of intakes, combustors and
More informationLEAP-X Program Update
LEAP-X Program Update 29 Oct 09 NYC CFM International Proprietary Information The information in this document is CFM Proprietary Information and is disclosed in confidence. It is the property of CFM International
More informationStudy on Flow Fields in Variable Area Nozzles for Radial Turbines
Vol. 4 No. 2 August 27 Study on Fields in Variable Area Nozzles for Radial Turbines TAMAKI Hideaki : Doctor of Engineering, P. E. Jp, Manager, Turbo Machinery Department, Product Development Center, Corporate
More informationDual Fuel Engine Charge Motion & Combustion Study
Dual Fuel Engine Charge Motion & Combustion Study STAR-Global-Conference March 06-08, 2017 Berlin Kamlesh Ghael, Prof. Dr. Sebastian Kaiser (IVG-RF), M. Sc. Felix Rosenthal (IFKM-KIT) Introduction: Operation
More informationScramjet Engine Research of KARI : Ground Tests of Engines and Components
23 rd ICDERS July 24-29, 211 Irvine, USA Scramjet Engine Research of KARI : Ground Tests of Engines and Components Soo Seok Yang, Sang Hun Kang, Yang Ji Lee Aero Propulsion System Department, Korea Aerospace
More informationUNCLASSIFIED FY 2016 OCO. FY 2016 Base
Exhibit R-2, RDT&E Budget Item Justification: PB 2016 Air Force Date: February 2015 3600: Research, Development, Test & Evaluation, Air Force / BA 3: Advanced Technology Development (ATD) COST ($ in Millions)
More informationComparison of Swirl, Turbulence Generating Devices in Compression ignition Engine
Available online atwww.scholarsresearchlibrary.com Archives of Applied Science Research, 2016, 8 (7):31-40 (http://scholarsresearchlibrary.com/archive.html) ISSN 0975-508X CODEN (USA) AASRC9 Comparison
More informationCFD ANALYSIS TO INVESTIGATE THE EFFECT OF LEANED ROTOR ON THE PERFORMANCE OF TRANSONIC AXIAL FLOW COMPRESSOR STAGE
20th Annual CFD Symposium August09-0, 208, Bangalore, Karnataka, India CFD ANALYSIS TO INVESTIGATE THE EFFECT OF LEANED ROTOR ON THE PERFORMANCE OF TRANSONIC AXIAL FLOW COMPRESSOR STAGE AKASH M M Tech
More informationAdvanced Aerodynamic Design Technologies for High Performance Turbochargers
67 Advanced Aerodynamic Design Technologies for High Performance Turbochargers TAKAO YOKOYAMA *1 KENICHIRO IWAKIRI *2 TOYOTAKA YOSHIDA *2 TORU HOSHI *3 TADASHI KANZAKA *2 SEIICHI IBARAKI *1 In recent years,
More informationCOMPUTATIONAL ANALYSIS DIAMOND-SHAPED STRUT INJECTOR FOR SCRAMJET COMBUSTOR AT MACH 4.3 S. Roga1,K.M. Pandey2 and A.P.Singh3 1
ISSN: 2395-3594 IJAET International Journal of Application of Engineering and Technology Vol-2 No.-2 COMPUTATIONAL ANALYSIS DIAMOND-SHAPED STRUT INJECTOR FOR SCRAMJET COMBUSTOR AT MACH 4.3 S. Roga1,K.M.
More informationAnalysis of a turbine rim seal cavity via 3D-CFD using conjugated heat transfer approach
Analysis of a turbine rim seal cavity via 3D-CFD using conjugated heat transfer approach ZERELLI, N. - Heat Transfer Department MTU Aero Engines, 80995 Munich, Germany University: ISAE Institut Supérieur
More informationSupersonic Nozzle Design for 1µm Laser Sources
Supersonic Nozzle Design for 1µm Laser Sources Ali Khan Bill O Neill Innovative Manufacturing Research Centre (IMRC) Centre for Industrial Photonics Institute for Manufacturing, Department of Engineering,
More informationENGINE Demonstration Programmes in Clean Sky & Clean Sky 2
ENGINE Demonstration Programmes in Clean Sky & Clean Sky 2 Jean-François BROUCKAERT SAGE & ENGINES ITD Project Officer Aerodays 2015, London, 20-23 October 2015 Innovation Takes Off Outline 1. Open-Rotor
More informationSupersonic Combustion Experimental Investigation at T2 Hypersonic Shock Tunnel
Supersonic Combustion Experimental Investigation at T2 Hypersonic Shock Tunnel D. Romanelli Pinto, T.V.C. Marcos, R.L.M. Alcaide, A.C. Oliveira, J.B. Chanes Jr., P.G.P. Toro, and M.A.S. Minucci 1 Introduction
More informationSupersonic Combustion of Liquid Hydrogen using Slotted Shaped Pylon Injectors
Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 3, Number 3 (2013), pp. 131-136 Research India Publications http://www.ripublication.com/aasa.htm Supersonic Combustion of Liquid Hydrogen
More informationFlow Controlled Core Overview
Flow Controlled Core Overview Hanna Reiss, Snecma Safran Group Introduction High BPR and/or new architectures will require highly loaded, efficient and operable HPC (+20/25% vs. in-service compressor)
More informationNoise and Noise Reduction in Supersonic Jets
Noise and Noise Reduction in Supersonic Jets Philip J. Morris and Dennis K. McLaughlin The Pennsylvania State University Department of Aerospace Engineering Presented at FLINOVIA 2017 State College, PA
More informationCorso di Motori Aeronautici
Corso di Motori Aeronautici Mauro Valorani Laurea Magistrale in Ingegneria Aeronautica (MAER) Sapienza, Università di Roma Anno Accademico 2011-12 Sett. 13: Conclusioni 1 FP7 Aero Engine Scenario ERS Strategy
More informationUNCLASSIFIED FY 2017 OCO. FY 2017 Base
Exhibit R-2, RDT&E Budget Item Justification: PB 2017 Air Force Date: February 2016 3600: Research, Development, Test & Evaluation, Air Force / BA 3: Advanced Technology Development (ATD) COST ($ in Millions)
More informationDesign Rules and Issues with Respect to Rocket Based Combined Cycles
Respect to Rocket Based Combined Cycles Tetsuo HIRAIWA hiraiwa.tetsuo@jaxa.jp ABSTRACT JAXA Kakuda space center has been studying rocket based combined cycle engine for the future space transportation
More informationLecture 4 CFD for Bluff-Body Stabilized Flames
Lecture 4 CFD for Bluff-Body Stabilized Flames Bluff Body Stabilized flames with or without swirl are in many laboratory combustors Applications to ramjets, laboratory burners, afterburners premixed and
More informationThe Aircraft Engine Design Project Fundamentals of Engine Cycles
GE Aviation The Aircraft Engine Design Project Fundamentals of Engine Cycles 1 Spring 2008 Peter Rock Earl Will DeShazer Ken Gould GE Aviation Technical History I-A - First U.S. jet engine (Developed in
More informationCOMPRESSIBLE FLOW ANALYSIS IN A CLUTCH PISTON CHAMBER
COMPRESSIBLE FLOW ANALYSIS IN A CLUTCH PISTON CHAMBER Masaru SHIMADA*, Hideharu YAMAMOTO* * Hardware System Development Department, R&D Division JATCO Ltd 7-1, Imaizumi, Fuji City, Shizuoka, 417-8585 Japan
More informationDESIGN AND TESTING OF A DUAL-MODE SCRAMJET FOR OPTICAL MEASUREMENT TECHNIQUES
DESIGN AND TESTING OF A DUAL-MODE SCRAMJET FOR OPTICAL MEASUREMENT TECHNIQUES Author: Brian Advisor: Chris Goyne and Jim McDaniel University of Virginia Abstract The following research paper presents an
More informationExperimental Investigation of Hot Surface Ignition of Hydrocarbon-Air Mixtures
Paper # 2D-09 7th US National Technical Meeting of the Combustion Institute Georgia Institute of Technology, Atlanta, GA Mar 20-23, 2011. Topic: Laminar Flames Experimental Investigation of Hot Surface
More informationDave Bone. DREAM Project Coordinator
Validation of radical engine architecture systems the alternative solution for a cleaner future Dave Bone Rolls-Royce plc Dave Bone Rolls-Royce plc DREAM Project Coordinator DREAM Project Coordinator This
More informationAERONAUTICAL ENGINEERING
AERONAUTICAL ENGINEERING SHIBIN MOHAMED Asst. Professor Dept. of Mechanical Engineering Al Ameen Engineering College Al- Ameen Engg. College 1 Aerodynamics-Basics These fundamental basics first must be
More informationMSFI TECHNOLOGY AT SAFRAN AIRCRAFT
MSFI TECHNOLOGY AT SAFRAN AIRCRAFT ENGINES S. BOURGOIS 08/03/2017 Ce document et les informations qu il contient sont la propriété de Safran. Ils ne doivent pas être copiés ni communiqués à un tiers sans
More informationFUEL BURN REDUCTION. Fuel consumption improvement 20 % 5 % 20 to 30% 1 Direction Technique YD 20 juin first generation
Environmental Constraints and Future Engine Architectures 0 Direction Technique YD 20 juin 2008 Jacques Renvier Senior VP System Engineering FUEL BURN REDUCTION B737-200 / JT8D first generation 20 % offers
More informationAerodynamic Testing of the A400M at ARA. Ian Burns and Bryan Millard
Aerodynamic Testing of the A400M at ARA by Ian Burns and Bryan Millard Aircraft Research Association Bedford, England Independent non-profit distributing research and development organisation Set up in
More informationHighly transient gas engine operation from a turbocharging perspective
HERVÉ MARTIN, ABB TURBO SYSTEMS LTD Highly transient gas engine operation from a turbocharging perspective 10th CIMAC CASCADES, Kobe, 12 th October 2018 Overview Introduction Basics of load pick-up Modeling
More informationTURBOPROP ENGINE App. K AIAA AIRCRAFT ENGINE DESIGN
CORSO DI LAUREA SPECIALISTICA IN Ingegneria Aerospaziale PROPULSIONE AEROSPAZIALE I TURBOPROP ENGINE App. K AIAA AIRCRAFT ENGINE DESIGN www.amazon.com LA DISPENSA E E DISPONIBILE SU http://www.ingindustriale.unisalento.it/didattica/
More information1. Aero-Science B.Sc. Aero Science-I Total Mark: 100 Appendix A (Outlines of Tests) Aero-Engines : 100 Marks
1. Aero-Science B.Sc. Aero Science-I Total Mark: 100 Appendix A (Outlines of Tests) Aero-Engines : 100 Marks Note:- The questions will be set in each paper. Candidates are to attempt any five except in
More informationEuropean Workshop on New Aero Engine Concepts Munich, 30 June 1 July 2010
08 June 2010 1 Pulse Detonation Core Engine (from WP 2.3: Future Innovative Core Configuration A. Lundblahd, VOLVO Aero WP2.3.3: Innovative combustion F Giuliani, TU Graz) F. Giuliani, A. Lang, Graz University
More informationMarc ZELLAT, Driss ABOURI and Stefano DURANTI CD-adapco
17 th International Multidimensional Engine User s Meeting at the SAE Congress 2007,April,15,2007 Detroit, MI RECENT ADVANCES IN DIESEL COMBUSTION MODELING: THE ECFM- CLEH COMBUSTION MODEL: A NEW CAPABILITY
More informationA Micro Power Generation System with Gas Turbine Engine and Piezo Converter -- Modeling, Fabrication and Characterization --
A Micro Power Generation System with Gas Turbine Engine and Piezo Converter -- Modeling, Fabrication and Characterization -- X.C. Shan *1, Z.F. Wang 1, Y.F. Jin 1, C.K. Wong 1, J. Hua 2, M. Wu 2, F. Lu
More information(VTOL) Propulsion Systems Design
72-GT-73 $3.00 PER COPY $1.00 TO ASME MEMBERS The Society shall not be responsible for statements or opinions advanced in papers or in discussion at meetings of the Society or of its Divisions or Sections,
More informationNumerical Investigation of the Influence of different Valve Seat Geometries on the In-Cylinder Flow and Combustion in Spark Ignition Engines
Institute for Combustion and Gas Dynamics Fluid Dynamics Numerical Investigation of the Influence of different Valve Seat Geometries on the In-Cylinder Flow and Combustion in Spark Ignition Engines Peter
More informationOpportunities For Innovative Collaboration. Propulsion Directorate Propulsion & Power for the 21st Century Warfighter
Opportunities For Innovative Collaboration Propulsion Directorate Propulsion & Power for the 21st Century Warfighter Propulsion Directorate Our Mission Create and transition advanced air breathing and
More informationNumerical Simulation of the Flow through the Rotor of a Radial Inflow Turbine
THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS 345 E. 47th St.. New York, N.Y. 10017 97;GT-90 The Society shall not be responsible for statements or opinions advanced in papers or eascussion at meetings
More informationUNCLASSIFIED. R-1 Program Element (Number/Name) PE F / Aerospace Propulsion and Power Technology
Exhibit R-2, RDT&E Budget Item Justification: PB 2015 Air Force Date: March 2014 3600: Research, Development, Test & Evaluation, Air Force / BA 3: Advanced Technology Development (ATD) COST ($ in Millions)
More informationMultipulse Detonation Initiation by Spark Plugs and Flame Jets
Multipulse Detonation Initiation by Spark Plugs and Flame Jets S. M. Frolov, V. S. Aksenov N.N. Semenov Institute of Chemical Physics, Russian Academy of Sciences, Moscow, Russia Moscow Physical Engineering
More informationA Computational Study of Axial Compressor Rotor Casing Treatments and Stator Land Seals
Virginia Commonwealth University VCU Scholars Compass Theses and Dissertations Graduate School 2006 A Computational Study of Axial Compressor Rotor Casing Treatments and Stator Land Seals Charles C. Cates
More informationTurbostroje 2015 Návrh spojení vysokotlaké a nízkotlaké turbíny. Turbomachinery 2015, Design of HP and LP turbine connection
Turbostroje 2015 Turbostroje 2015 Návrh spojení vysokotlaké a nízkotlaké turbíny Turbomachinery 2015, Design of HP and LP turbine connection J. Hrabovský 1, J. Klíma 2, V. Prokop 3, M. Komárek 4 Abstract:
More informationJet Propulsion. Lecture-13. Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati
Lecture-13 Prepared under QIP-CD Cell Project Jet Propulsion Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati 1 GE J79 Turbojet 2 Features Highly used
More informationFuel Injection and Combustion Study for Mach Scramjet. Dora E. Musielak University of Texas at Arlington
Fuel Injection and Combustion Study for Mach 10-12 Scramjet Dora E. Musielak University of Texas at Arlington dmusielak@uta.edu ABSTRACT A research program to support the development of scramjet engine
More informationPredictions of Cooling From Dirt Purge Holes Along the Tip of a Turbine Blade
Proceedings of ASME Turbo Expo 2003 Power for Land, Sea, and Air June 16 19, 2003, Atlanta, Georgia, USA GT2003-38251 Predictions of Cooling From Dirt Purge Holes Along the Tip of a Turbine Blade E. M.
More informationPERFORMANCE ESTIMATION AND ANALYSIS OF PULSE DETONATION ENGINE WITH DIFFERENT BLOCKAGE RATIOS FOR HYDROGEN-AIR MIXTURE
PERFORMANCE ESTIMATION AND ANALYSIS OF PULSE DETONATION ENGINE WITH DIFFERENT BLOCKAGE RATIOS FOR HYDROGEN-AIR MIXTURE Nadella Karthik 1, Repaka Ramesh 2, N.V.V.K Chaitanya 3, Linsu Sebastian 4 1,2,3,4
More informationInternational Journal of Scientific & Engineering Research, Volume 5, Issue 7, July-2014 ISSN
ISSN 9-5518 970 College of Engineering Trivandrum Department of Mechanical Engineering arundanam@gmail.com, arjunjk91@gmail.com Abstract This paper investigates the performance of a shock tube with air
More informationUniversity of Huddersfield Repository
University of Huddersfield Repository Colley, Gareth, Mishra, Rakesh, Rao, H.V. and Woolhead, R. Performance evaluation of three cross flow vertical axis wind turbine configurations. Original Citation
More informationIntroduction to Aerospace Propulsion
Introduction to Aerospace Propulsion Introduction Newton s 3 rd Law of Motion as the cornerstone of propulsion Different types of aerospace propulsion systems Development of jet engines Newton s Third
More informationIJESRT: 7(10), October, 2018 ISSN:
IJESRT: 7(10), October, 2018 ISSN: 2277-9655 International Journal of Engineering Sciences & Research Technology (A Peer Reviewed Online Journal) Impact Factor: 5.164 IJESRT Chief Editor Dr. J.B. Helonde
More informationExperimental Investigation on Modification of Inlet poppet valve of single cylinder Direct Ignition Four stroke Diesel Engine
Experimental Investigation on Modification of Inlet poppet valve of single cylinder Direct Ignition Four stroke Diesel Engine Dr. Hiregoudar Yerrennagoudaru 1, Shiva prasad Desai 2, Mallikarjuna. A 3 1
More informationWhat does the future bring?
Gebhardt Lecture Georgia Institute of Technology January 23, 2014 Dr. M.J. Benzakein Director, Propulsion and Power Center What does the future bring? A look at Technologies for Commercial Aircraft in
More informationSTUDIO NUMERICO SPERIMENTALE DI TuRBomacchine di piccola potenza
Giornata di Studio sulle TURBOMACCHINE Bergamo 15 luglio 2016 STUDIO NUMERICO SPERIMENTALE DI TuRBomacchine di piccola potenza Rodolfo Bontempo Marcello Manna Raffaele Tuccillo Dipartimento di Ingegeria
More informationCFD Analysis on a Different Advanced Rocket Nozzles
International Journal of Engineering and Advanced Technology (IJEAT) CFD Analysis on a Different Advanced Rocket Nozzles Munipally Prathibha, M. Satyanarayana Gupta, Simhachalam Naidu Abstract The reduction
More informationEffect of Stator Shape on the Performance of Torque Converter
16 th International Conference on AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 May 26-28, 2015, E-Mail: asat@mtc.edu.eg Military Technical College, Kobry Elkobbah, Cairo, Egypt Tel : +(202) 24025292
More informationIdealizations Help Manage Analysis of Complex Processes
8 CHAPTER Gas Power Cycles 8-1 Idealizations Help Manage Analysis of Complex Processes The analysis of many complex processes can be reduced to a manageable level by utilizing some idealizations (fig.
More informationComputational Analysis of Hydrogen-Fueled Scramjet Combustor with Diamond-Shaped Strut Injector at Mach 4
Computational Analysis of Hydrogen-Fueled Scramjet Combustor with Diamond-Shaped Strut Injector at Mach 4 Dr. Sukanta Roga 1, Dr. K.M. Pandey 2 1 Associate Professor, Department of Mechanical Engineering,
More informationTraining Title GAS TURBINE AND COMPRESSOR OPERATION, MAINTENANCE AND TROUBLESHOOTING
Training Title GAS TURBINE AND COMPRESSOR OPERATION, MAINTENANCE AND TROUBLESHOOTING Training Duration 5 days Training Venue and Dates Gas Turbine and Compressor Operation, Maintenance and Troubleshooting
More informationMarc ZELLAT, Driss ABOURI, Thierry CONTE and Riyad HECHAICHI CD-adapco
16 th International Multidimensional Engine User s Meeting at the SAE Congress 2006,April,06,2006 Detroit, MI RECENT ADVANCES IN SI ENGINE MODELING: A NEW MODEL FOR SPARK AND KNOCK USING A DETAILED CHEMISTRY
More information