3 edition of The supersonic through-flow turbofan for high mach propulsion found in the catalog.
The supersonic through-flow turbofan for high mach propulsion
by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va
Written in English
|Statement||Leo C. Franciscus.|
|Series||NASA technical memorandum -- 100114.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
A baseline supersonic throughflow fan has been designed and tested at the NASA Lewis Research Center in order to demonstrate proof-of-concept and provide an experi mental data base for this unique type of turbomachine. The aerodynamics of the rotor, which was tested in both an isolated and a stage configuration, is discussed in somewhat. Military Supersonic Turbofan Engine 3D Model 3d model of Pratt & Whitney F afterburning turbofan engine with Interior parts. Turbofan Turboprop Supersonic Afterburning Aircraft .
The turbofan or fanjet is a type of airbreathing jet engine that is widely used in aircraft word "turbofan" is a portmanteau of "turbine" and "fan": the turbo portion refers to a gas turbine engine which achieves mechanical energy from combustion, and the fan, a ducted fan that uses the mechanical energy from the gas turbine to accelerate air rearwards. The supersonic through-flow turbofan for high mach propulsion [microform] / Leo C. Franciscus Preliminary design of a supersonic cruise aircraft high-pressure turbine [microform]: final report / [p.
Classification of Mach regimes. Although "subsonic" and "supersonic" usually refer to speeds below and above the local speed of sound respectively, aerodynamicists often use these terms to refer to particular ranges of Mach values. This occurs because a "transonic regime" exists around M=1 where approximations of the Navier–Stokes equations used for subsonic design no longer apply, partly. From Mach cruise propulsion systems, preliminary design studies for two supersonic through-flow fan primary inlets and a single core inlet were undertaken. Method of characteristics and one dimensional performance techniques were applied to assess the potential improvements supersonic through-flow fan technology has over more conventional.
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CRITIC THEORY NOW
THE SUPERSONIC THROUGH-FLOW TURBOFAN FOR HIGH MACH PROPULSION by Leo C. Franciscus National Aeronautics and Space Administration Lewls Research Center Brookpark Road Cleveland, Ohio ABSTRACT A study was made to evaluate the potential improvements in aircraft turbine engine perfor- mance by incorporating unique supersonic through File Size: KB.
The supersonic through-flow turbofan for high Mach propulsion. LEO FRANCISCUS; LEO FRANCISCUS. NASA, Lewis Research Center, Cleveland, OH. Search for more papers by this author Turbojet and turbofan engines for a mach 3 supersonic transport. 1st Annual Meeting August Get this from a library.
The supersonic through-flow turbofan for high mach propulsion. [Leo C Franciscus; United States. National Aeronautics and Space Administration.]. The supersonic through-flow turbofan for high Mach propulsion.
By Leo C. Franciscus. Abstract. A study was done to evaluate the potential improvements in aircraft turbine engine performance by incorporating unique supersonic through-flow fans.
Engine performance, weight, and mission studies were carried out for conventional turbofan engines Author: Leo C. Franciscus. Parametric Study of a Mach Transport Engine with Supersonic Through-Flow Rotor and Supersonic Counter-Rotating Diffuser [Donald H.
Tran, Nasa Technical Reports Server (Ntrs)] on *FREE* shipping on qualifying offers. A parametric study is conducted to evaluate a mixed-flow turbofan equipped with a supersonic through-flow rotor and a supersonic counter-rotating diffuser (SSTR Author: Donald H.
Tran. Supersonic propulsion - to The supersonic through-flow turbofan for high Mach propulsion. LEO FRANCISCUS; Research on TBCC Propulsion for a Mach Supersonic Cruise Airliner. Martin Sippel; 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference June 13th Propulsion Conference.
11 July - Payoffs for supersonic through flow fan engines in high Mach transports and fighters. The supersonic through-flow turbofan for high Mach propulsion. LEO FRANCISCUS; Turbojet and turbofan engines for a mach 3 supersonic transport.
1st Annual Meeting August Ideal Turbojet in Supersonic Cruise in The Stratosphere. Ideal Ramjet in High Supersonic Cruise in The Stratosphere. Ideal Turbofan in Maximum Power Take-Off. Ideal Turbofan in High Subsonic Cruise in The Stratosphere.
Ideal Internal Turbofan in Supersonic Cruise in The Stratosphere. Real Engine Operations. Book Edition: 1. NASA research in supersonic propulsion - A decade of progress. The supersonic through-flow turbofan for high Mach propulsion.
LEO FRANCISCUS; 23rd Joint Propulsion Conference August Variable Stream Control Engine for Supersonic Propulsion. Richard W. Hines; Journal of Aircraft Vol.
15, No. 6 June Supersonic propulsion - to. potential propulsion concepts •. technology propulsion internal perform. target challenge concept core flow goal fuels atr 1urboramjet stoicil turbofan ss fan-atr ss fan-turbofan, remote aug. turbofan subsonic stoicil turbofan/jet supersonic base jpx.
ehc +6 fbc +26 4 concepts reviewed/updated throughout program. The supersonic through-flow turbofan for high Mach propulsion and mission studies were carried out for conventional turbofan engines using supersonic through-flow fans.
A Mach 3 commercial transport mission was considered. The advantages of the supersonic fan engines were evaluated in terms of mission range comparisons between the Author: Leo C.
Franciscus. turbofan engine. However, the turbofan engine equipped with a supersonic through-flow fan capable of accepting supersonic axial flow from the inlet has the potential of being very efficient at super- sonic cruise conditions.
In addition, the super- sonic through-flow fan has the potential of highCited by: Franciscus, L.C.: The Supersonic Through- Flow Turfofan for High Mach Propulsion, NASA TM, Phillips, J.E.: Supersonic Through-Flow Rotor With Supersonic Counter-Rotating Diffuser Engine For A Mach Transport, United Technologies Corporation Pratt & Whitney, West Palm Beach, Florida, September The purpose of the present study is to predict analytically the unsteady loading on vibrating blades of a supersonic through-flow fan and investigate the aerodynamic instability.
Study of Variable Cycle Engines Equipped With Supersonic Fans L. The Supersonic-Through Flow Turbofan for High Mach Propulsion. AIAA Paper, 87– Cited by: 1.
"The Supersonic Through-Flow Turbofan for High Mach Propulsion", NASA TM, AIAA, July, 4. Anderson, B. H., "Design of Supersonic Tnlets by a Computer Program Incorporating the Method of Characteristics", NASA TN-D-through-flow fan engine for supersonic cruise aircraft.
It included a mean-line analysis of fans designed to operate with in-flow velocities ranging from subsonic to high supersonic speeds.
used to estimate the performance of supersonic fan engines designed for four applications: a Mach supersonic transport, a Mach fighter, a Mach File Size: 4MB. viable supersonic propulsion system and the required specific propulsion technology programs are out-lined at the end of the report.
Key Words (Suggested by Author(s)) Distribution Statement Advanced Supersonic Transport Advanced Propulsion Systems Unclassified-Unlimited Reduced Noise and Emissions Augmented Turbofans and Turbojet Turbofan engines are mostly used in subsonic aircrafts. Introducing supersonic flow directly to the engine makes compressor to stall because they cannot handle the shock waves and back pressue created by shock waves.
Therefore, turbofan engines us. NASA 73 investigated six potential propulsion systems for use on supersonic civil aircraft: turbojet, turbine bypass, mixed flow turbofan, variable cycle, Flade (Fan-on-blade is a modified turbofan engine that introduces an additional airstream up front in the engine fan) and the inverting flow valve engine.
These were evaluated for performance, weight and size. Supersonic flow past a strut mounted on an endwall generates a complex vortical flow pattern near the strut/endwall intersection. Recent studies by Williams et al.
() and Williams and Gessner (), based on supersonic flow past diamond-shaped struts mounted between concentric cylinders, have shown that four distinct vortices are formed in the vicinity of each strut/endwall by: 1.
The speed limiter at Mach is related to propulsion and noise regulations: an aircraft needs to be fuel efficient at supersonic cruise yet quiet around airports. To be quiet, large-diameter engines with big fans (high bypass ratios, see Bypass ratio — Wikipedia) are desired.
Yet, the faster one cruises, the lower the desired bypass ratio.mixed-flow turbofan equipped with a supersonic through-flow rotor and a supersonic counter-rotating diffuser (SSTR/SSCRD) for a Mach civil transport.
Engine cycle, weight, and mission analyses are per-formed to obtain a minimum takeoff gross weight aircraft. With .From Mach cruise propulsion systems, preliminary design studies for two supersonic through-flow fan primary inlets and a single core inlet were undertaken.