and high temperature, the research object was expanded to a nonlinear dynamatics system of linear paramter uncertain in control maxtrix, the paper provided adaptive adjust function to compensate the influence from the unce...
Andrew Nahum’s excellent paper‘Two-Stroke or Turbine’ examines these engines in detail, but these were to be ‘sprint’ engines of very high power/weight ratio, with the added advantage of running on 87 octane fuel, at a time when it was uncertain how much 100 octane would be ...
The small cross section of the 292 series bearings have favourable speed, space and weight characteristics. Smaller and more cost-effective equipment can be designed for longer bearing service life or higher output as a result of the high com- bined load carrying capacity of SKF spherical roller...
3. The thruster assembly of claim 1 wherein an external shield is provided for the propellant structure and is constructed of a minimum weight low thermal conductivity metal in order to insulate the heated fuel passageways from a structure to which the thruster assembly is mounted, a part of ...
A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and
Additionally, to avoid flow separation in the nozzle, it was necessary to have a relatively low area ratio which led to a decrease in potential performance. The overall design requirements above were broken down into more specific requirements. This complete set of requirements was used as an ...
ratio; a combustion section in communication with the low pressure compressor and the high pressure compressor; a high pressure turbine coupled for rotation with a first spool to rotationally drive the high pressure compressor; a low pressure turbine coupled for rotation with a second spool to ...
Although these margins are clearly defined for static operating conditions, when the aeroengine undergoes harsh maneuvers, the compressor faces a fast increase in the pressure ratio with a quasi-constant mass flow [33]. Considering the causality of shaft speed, pressure and mass-flow, the ...
A design space exploration is then performed on the setup to investigate how the fan stage attributes influence the trade-off between engine weight and thrust specific fuel consumption in a representative aerodynamic design point. 2. Methodology The main objective of this paper is to demonstrate an...
A design space exploration is then performed on the setup to investigate how the fan stage attributes influence the trade-off between engine weight and thrust specific fuel consumption in a representative aerodynamic design point. 2. Methodology The main objective of this paper is to demonstrate an...