Summary Nasa-Books Pdf

Summary NASA
27 Dec 2019 | 94 views | 0 downloads | 34 Pages | 2.61 MB

Share Pdf : Summary Nasa

Download and Preview : Summary Nasa

Report CopyRight/DMCA Form For : Summary Nasa



Transcription

National Aeronautics and Space Administration, Core Noise Implications of Emerging N 3. Designs Acoustic Technology Needs, Lennart S Hultgren. NASA Glenn Research Center, Subsonic Fixed Wing Project. Acoustics Technical Working Group, Cleveland OH April 21 22 2011. www nasa gov www nasa gov, National Aeronautics and Space Administration.
Current trends, N 1 5 time frame, NASA N 3 concepts. implications for core noise, Core noise roadmap, under development early days yet. L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 1. National Aeronautics and Space Administration, Current Trends N 1 5. Overall cycle changes, BPR FPR N1, Non core propulsion noise components will be reduced at all power levels. High power density low emission cores, COMBUSTOR TURBINE LPT.
Blade Counts, Blade Loading, Temperature, Stage Spacing. Core noise components will be increased at all power levels. L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 2. National Aeronautics and Space Administration, NASA N 3 Aircraft Concepts. Advanced Tube and Wing, MIT Double Bubble D8 5, SFW primary concepts. Boeing GE SUGAR Volt, Northrop Grumman SELECT, NASA Truss Braced Wing. Evolution of Hybrid Wing Body, Boeing GE SUGAR Ray.
NASA Turbo Electric, Emerging core designs appear game changing. L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 3. National Aeronautics and Space Administration, MIT P W Double Bubble D8 5. Natural progression for B737 A320 mission, three rear mounted UHB geared turbofans BPR 20. small high power density cores OPR 50, advanced lean direct injection LDI combustor. multi segment rearward acoustic liners, Noise from high power density low emissions core ignored.
L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 4. National Aeronautics and Space Administration, MIT D8 Noise Assessment. D8 1 CFM56 class, 12 000 lbf engine, D8 5 UHB geared. 8 500 lbf engine, D8 shielding treatment, UHB reduces fan jet. Observer further away, L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 5. National Aeronautics and Space Administration, MIT D8 Series Challenges.
NRA Conclusions, Small core size engine technology. Boundary layer ingesting BLI propulsion, Propulsion airframe integration exhaust system. BPR wF wc Axial Mixed NA C or Centrifugal HPC, MIT Team Final Review Presentation 2010 04 23 modified. wc means radial, size possible, Traditionally high. power density implied, reduced axial size, L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 6.
National Aeronautics and Space Administration, BPR Historical Trend MIT. MIT Team Final Review Presentation 2010 04 23, NASA CR 2010 216794 VOL I 2010. Technology change, high BPR turbofans, L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 7. National Aeronautics and Space Administration, OPR Historical Trend MIT. MIT Team Final Review Presentation 2010 04 23, NASA CR 2010 216794 VOL I 2010.
L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 8. National Aeronautics and Space Administration, T41 Historical Trend MIT. NASA CR 2010 216794 VOL I 2010, Source Cumpsty N Jet Propulsion A simple guide to the aerodynamic and thermodynamic design and performance of jet engines. Cambridge University Press 2003, L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 9. National Aeronautics and Space Administration, MIT P W D8 5 Core Noise Issues. Small core size engine, technology challenge, unknown impact on.
noise from solutions, high OPR noise increase, advanced LDI combustor. From MIT Team NASA FAP Technical Conference Presentation 2011 03 15. Turbine Compressor, axial radial design implications on noise. well outside of empirical data base small size high power density. reduced axial length means less real estate for acoustic liners. Moderate T41, improves prospect for using advanced acoustic liners. L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 10. National Aeronautics and Space Administration, Boeing GE SUGAR Volt hFan. B737 A320 mission, two UHB hybrid gas turbine electric engines BPR 18.
high power density cores OPR 59 with advanced combustor. strut braced low weight high wing, advanced passive core nozzle acoustic treatment. aggressive active noise suppression in combustor, Lack of information about noise analysis and goal not met. L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 11. National Aeronautics and Space Administration, SUGAR Volt Characteristics. Laminar flow maximized, Larger fan by addition of, electric motor. Removable batteries, Laminar flow in blue, added battery weight.
depends on mission, Noise reduction of, relative to SUGAR Free. SUGAR High based, electric drive effects, ignored pros cons Removable modular battery pack. SUGAR Volt is a derivative of SUGAR High Concept, L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 12. National Aeronautics and Space Administration, Boeing GE SUGAR Acoustic Assessment. SUGAR Refined SUGAR SUGAR, Configuration Refined, Free SUGAR High Volt.
Propulsion CFM56 gFan gFan gFan hFan, Potentially, EPNL dB 0 16 22 22 lower than. reference case proprietary value Ultra high PR Advanced. B737NG Certification 8 dB core compressor electric motor. ENGINE CORE ACOUSTIC TECH VAN, adv passive noise suppression. acoustic treatments, blade and OGV optimization Highly. loaded LPT, adv active noise suppression, low noise combustor Advanced combustor Moderate T41. flow control GT Electric Hybrid GE hFan, L S Hultgren Core Noise Acoustics Technical Working Group Apr 21 22 2011 www nasa gov 13.
Summary This presentation is a summary of the core noise implications of NASA s primary N 3 aircraft concepts These concepts are the MIT P amp W D8 5 Double Bubble design the Boeing GE SUGAR Volt hybrid gas turbine electric engine concept the NASA N3 X Turboelectric Distributed Propulsion aircraft and the NASA TBW XN Truss Braced Wing concept

Related Books

HOST Turbine Heat Transfer Program Summary ntrs nasa gov

HOST Turbine Heat Transfer Program Summary ntrs nasa gov

HOST TURBINE HEAT TRANSFER PROGRAM SUMMARY flow and heat transfer in high temperature gas turbines board improvement in turbine heat transfer technology

Final Benchmark v14a 9 30 08 nasa gov

Final Benchmark v14a 9 30 08 nasa gov

i Executive Summary Many challenges in Earth system science require integrating complex physical processes into sys tem models and coupling environmental

Research Start to Finish Writing NASA Proposals

Research Start to Finish Writing NASA Proposals

PI creates a webpage for proposal on NSPIRES cite Sections for Proposal Summary 4000 characters Business Data Sponsoring org start end dates environmental impact point of contact Budget Program Speci c Data and Proposal Team PI Co Is Collaborators Staff Students Budget pages here MUST match budget page within proposal NASA

Applied Aerodynamics Challenges and Expectations

Applied Aerodynamics Challenges and Expectations

APPLIED AERODYNAMICS CHALLENGES AND EXPECTATIONS Victor L Peterson and Charles A Smith NASA Ames Research Center Moffett Field California Summary Aerospace is the leading positive contributor to this country s balance of trade derived largely from the sale of U S commercial aircraft around the world This power

Human Research Program Space Radiation Standing Review

Human Research Program Space Radiation Standing Review

Human Research Program Space Radiation Standing Review Panel SRP Final Report February 2010 I Executive Summary amp Overall Evaluation The Space Radiation Standing Review Panel SRP met at the NASA Johnson Space Center JSC on December 9 11 2009 to discuss the areas of current and future research targeted by the Space Radiation Program Element SRPE of the Human Research Program HRP

SUMMARY OF NASA RESEARCH ON THERMAL BARRIER COATINGS by H

SUMMARY OF NASA RESEARCH ON THERMAL BARRIER COATINGS by H

sively degraded by the presence of the coating A two layer thermal barrier coating consisting of a stabilized zirconia coating over a metal bon d coating which potentially has these desirable features has been developed at the NASA Lewis Research Center Stepka Liebert and is under investigation and Stecura

Ngo es62s NASA

Ngo es62s NASA

Ngo es62s CAGE STABILITY ANALYSIS FOR SSME HPOTP BEARINGS T L Merriman and J W Kannel Battelle Columbus Division i i p Ij lt SUMMARY A numerical model of cage motion CAGEDYN has been used to analyze the stability of bearing cages in the Space Shuttle main engine SSME high pressure oxygen turbopump HPOTP The stability of existing bearing geometries as well as perturbations of these

REPORT No 741 NASA

REPORT No 741 NASA

REPORT No 741 FLUTTER CALCULATIONS IN THREE DEGREES OF FREEDOM By TIIEODORF THEODORSEN and I E GARRICK SUMMARY The prc ent paper i a c ntinuation of the general tudy

MODELING SYSTEM USING A CAD CAM SYSTEM SUMMARY CAM NASA

MODELING SYSTEM USING A CAD CAM SYSTEM SUMMARY CAM NASA

IFEMS AN INTERACTIVE FINITE ELEMENT MODELING SYSTEM USING A CAD CAM SYSTEM Spencer McKellip Todd Schuman and Spencer Lauer Sikorsky Aircraft Division of United

INFLUENCE OF COMBUSTION NASA

INFLUENCE OF COMBUSTION NASA

INFLUENCE OF COMBUSTION PROCESS ON STABILITY by Richard J Priem Lewis Research Center SUMMARY The relative importance of various steps in the combustion process on combustion instability was compared theoretically by assuming that individual steps controlled the growth of a disturbance The combustion steps involved the time dependence of 1 pro

Tethers in Space Handbook NASA

Tethers in Space Handbook NASA

The Tethers in Space Handbook is designed to serve as a reference manual for policy makers program managers and engineers alike It documents all known tether applications for space uses ranging from near term approved missions such as the Tethered Satellite System to far term planetary exploration missions A brief summary of each application is presented as well as a listing of principal

AERODYNAMIC CHARACTERISTICS NASA

AERODYNAMIC CHARACTERISTICS NASA

AERODYNAMIC CHARACTERISTICS OF A FIVE JET VTOL CONFIGURATION IN THE TRANSITION SPEED RANGE By Richard J Margason and Gar1 L Gentry Jr Langley Research Center SUMMARY A wind tunnel investigation of a powered model of a VTOL fighter airplane config uration having three lift engines in the forward fuselage and two deflected lift cruise engines in the aft fuselage has been conducted to