The application of new technology for performance improvement and noise reduction of supersonic transport aircraft

1977 ◽  
Author(s):  
P. CALDER ◽  
P. GUPTA
Keyword(s):  
Noise Reduction ◽  
Performance Improvement ◽  
New Technology ◽  
Transport Aircraft ◽  
Supersonic Transport

scholarly journals Influence of the use of spring vibration isolators in the construction of track pavement for damping vibrations from the track

2018 ◽  
Vol 2018 (5) ◽  
pp. 1-9
Author(s):  
Ewelina Kwiatkowska ◽  
Wiesław Fiebig
Keyword(s):  
Noise Reduction ◽  
Vibration Isolation ◽  
New Technology ◽  
Track Structure ◽  
Vibration Isolators ◽  
Isolation Systems ◽  
Tuning Frequency ◽  
Mass Spring ◽  
Lower Frequencies

The paper presents tuned track bed vibration isolation systems used for the railway and tramway lines. The presented solution based on mass spring systems and is effective especially at lower frequencies. The tuning frequency of such systems is mostly in the range 5 to 8 Hz. With measures based on spring elements elaborated by GERB company the significant vibration and noise reduction coming from the railways and tramways can be achieved. This new technology in Poland can be used during the track structure modernization as well as in the new projects, in which the track bed vibration isolation is required.

Thrust Nozzles for Supersonic Transport Aircraft

1964 ◽  
Vol 86 (2) ◽  
pp. 97-104 ◽  
Author(s):  
David Migdal ◽  
John J. Horgan
Keyword(s):  
External Flow ◽  
Operating Costs ◽  
Jet Engine ◽  
Transport Aircraft ◽  
Supersonic Transport ◽  
The Past ◽  
Engine Thrust ◽  
Performance Trends ◽  
Flow Effects ◽  
Plug Nozzles

Supersonic transports will require jet-engine thrust nozzles that are highly efficient from take-off to supersonic cruise in order to minimize the direct operating costs. Variable-area ejectors, plug nozzles, and modifications of these basic types have been tested extensively during the past several years. Performance trends for these nozzles are presented with the emphasis on external flow effects. A new ejector which utilizes aerodynamically actuated doors to admit external air into the ejector shroud is discussed.

Propelling Nozzle Research

1964 ◽  
Vol 68 (647) ◽  
pp. 717-727 ◽  
Author(s):  
W. G. E. Lewis
Keyword(s):  
High Speed ◽  
High Performance ◽  
Research Programme ◽  
Static Tests ◽  
Transport Aircraft ◽  
Supersonic Transport ◽  
Design Behaviour ◽  
Base Bleed ◽  
Critical Phases ◽  
The Ideal

SummaryThe current interest in supersonic transport aircraft makes it appropriate to consider the problems of propulsion nozzle systems for high speed flight. The discussion will be confined mainly to this field of activity.In the absence of external drag and weight factors, the ideal configuration to maintain optimum thrust at all flight speeds would employ a mechanically variable area ratio nozzle. By such means the jet flow could be fully and properly expanded at all times.A practical design to accommodate such variations is inherently complex, and so an alternative solution using aerodynamic techniques has been sought. It is necessary to remember that the success of whatever method is eventually chosen must rest on its ability to combine a high performance at cruise with very small loss during other critical phases of the flight plan.This paper describes some of the results of a nozzle research programme aimed primarily at solving the above problem, with an attempt to explain the philosophy behind the aerodynamic techniques tried. Some discussion is given of the experimental difficulties in establishing a sufficiently accurate standard of measurement for design point performance. In a few chosen configurations experimental results have been extensively backed by theoretical studies.The need to demonstrate off-design behaviour in the presence of an external flow field is stressed, with special reference to the misleading results often obtained from static tests.Finally, some attention is given to the question of base bleed, with its repercussions on the installation of the propulsion nozzle in an aircraft.

scholarly journals Future Trends in Subsonic Transport Energy Efficient Turbofan Engines

1980 ◽  
Author(s):  
R. P. Johnston ◽  
P. Ortiz
Keyword(s):  
Performance Improvement ◽  
Energy Efficient ◽  
Electric Energy ◽  
Advanced Technology ◽  
Fuel Saving ◽  
Technology Program ◽  
Transport Aircraft ◽  
Turbofan Engines ◽  
Aircraft System ◽  
Selection Of

Details of the NASA sponsored General Electric Energy Efficient Engine (E3) technology program are presented along with a description of the engine, cycle and aircraft system benefits. Opportunities for further performance improvement beyond E3 are examined. Studies leading to the selection of the E3 cycle and configuration are summarized. The advanced technology features, cycle and component performance levels are also presented. An evaluation of the benefits of the fully developed Flight Propulsion System (FPS) is made relative to the NASA program goals by comparing the FPS with the CF6-50C where both are installed in advanced subsonic transport aircraft. Results indicate that a mission fuel saving from 15 to 23 percent is possible depending on mission length.

Separation Standards and Aircraft Wander

1966 ◽  
Vol 19 (2) ◽  
pp. 198-208
Author(s):  
R. N. Lord
Keyword(s):  
Block Size ◽  
Physical Size ◽  
Transport Aircraft ◽  
Supersonic Transport ◽  
Sources Of Error ◽  
Forward Prediction ◽  
Basic Parameters ◽  
Corrective Control ◽  
Separation Standards ◽  
Along Track

The basic parameters leading to aircraft navigational error are combined statistically and are used to evaluate the uncorrected deviation (wander) to be expected in both subsonic and supersonic transport aircraft operating in a typical trans-oceanic environment. The size of the across-track and along-track wander before any form of corrective control is applied indicates the physical size of the A.T.C. block of airspace necessary to contain the aircraft. The variation of block size with the forward prediction period used by A.T.C. is presented graphically. The effect of improvement in the basic sources of error is demonstrated and it is seen that for the S.S.T. era attention must be turned to effecting improvements in aircraft heading and airspeed holding capabilities.

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