Detailed measured radial distributions of flow parameters for eight rotors with part-span dampers are used to study the effects of dampers on rotor performance and flow parameters at near design operation. All rotors had a blade tip diameter of about 20 in. and operated at a blade tip speed of about 1400 ft/sec. Several examples demonstrate that, when the local loss variations in the damper flow region are included in an aerodynamic design or analysis procedure, the computed spanwise distributions of flow parameters compare closely with measured distributions
A transonic compressor stage designed for a reduced loading in the tip region of the rotor blades wa...
An axial flow compressor rotor was tested at design speed with six different casing treatments acros...
International Gas Turbine Conference and Exhibit; 8-12 Jun. 1986; Dusseldorf; GermanyThe mid-span se...
The design-point losses caused by part-span dampers (PSD) were correlated for 21 transonic axial flo...
Experimental data from 10 transonic fan rotors were used to correlate losses created by part-span da...
A single rotating blade row was tested with two magnitudes of tip radial distortion and two magnitud...
The experimental performance of a 20-inch-diameter axial-flow transonic compressor rotor with small ...
The overall and blade-element performance of two configurations of a moderately high aspect ratio tr...
The performance of compressors and the sophistication of analysis tools have reached a level such th...
A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determ...
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1989.Ti...
The performance of a two stage, high pressure-ratio fan, having large, part-span vibration dampers o...
Presented at the International Gas Turbine and Aeroengine Congress and Exposition Orlando, FL June ...
Research results and progress on the performance of bladed systems is reported the different topics ...
The tip clearance flows of transonic compressor rotors have a significant impact on rotor and stage ...
A transonic compressor stage designed for a reduced loading in the tip region of the rotor blades wa...
An axial flow compressor rotor was tested at design speed with six different casing treatments acros...
International Gas Turbine Conference and Exhibit; 8-12 Jun. 1986; Dusseldorf; GermanyThe mid-span se...
The design-point losses caused by part-span dampers (PSD) were correlated for 21 transonic axial flo...
Experimental data from 10 transonic fan rotors were used to correlate losses created by part-span da...
A single rotating blade row was tested with two magnitudes of tip radial distortion and two magnitud...
The experimental performance of a 20-inch-diameter axial-flow transonic compressor rotor with small ...
The overall and blade-element performance of two configurations of a moderately high aspect ratio tr...
The performance of compressors and the sophistication of analysis tools have reached a level such th...
A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determ...
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1989.Ti...
The performance of a two stage, high pressure-ratio fan, having large, part-span vibration dampers o...
Presented at the International Gas Turbine and Aeroengine Congress and Exposition Orlando, FL June ...
Research results and progress on the performance of bladed systems is reported the different topics ...
The tip clearance flows of transonic compressor rotors have a significant impact on rotor and stage ...
A transonic compressor stage designed for a reduced loading in the tip region of the rotor blades wa...
An axial flow compressor rotor was tested at design speed with six different casing treatments acros...
International Gas Turbine Conference and Exhibit; 8-12 Jun. 1986; Dusseldorf; GermanyThe mid-span se...