A design modification of Rotor 67 is carried out with a full 3D inverse method. The blade camber surface is modified to produce a prescribed pressure loading distribution, with the blade tangential thickness distribution and the blade stacking line at midchord kept the same as the original Rotor 67 design. Because of the inviscid-flow assumption used in the current version of the method, Rotor 67 geometry is modified for use at a design point different from the original design value. In the subsonic section, smooth pressure loading shapes generally produce blades with well-behaved blade surface pressure distributions. In the supersonic section, this study shows that the strength and position of the passage shock correlate with the characteristics of the blade pressure loading shape. In general, `smooth' prescribed blade pressure loading distributions generate blade designs with reverse cambers which have the effect of weakening the passage shock.
|Original language||English (US)|
|Journal||American Society of Mechanical Engineers (Paper)|
|State||Published - Dec 1 1997|
|Event||Proceedings of the 1997 International Gas Turbine & Aeroengine Congress & Exposition - Orlando, FL, USA|
Duration: Jun 2 1997 → Jun 5 1997
ASJC Scopus subject areas
- Mechanical Engineering