Add to ORKGPerformance data were obtained experimentally for a 0.4 linear scale version of the LF460 lift fan turbine for a range of scroll inlet total to diffuser exit static pressure ratios at design equivalent speed with simulated fan leakage air. Tests were conducted for full and partial admission operation with three separate combinations of rotor inlet and rotor exit leakage air. Data were compared to the results obtained from previous investigations in which no leakage air was present. Results are presented in terms of mass flow, torque, and efficiency
A solid blade version of a single-stage, axial-flow turbine was investigated to determine its perfor...
Cold air study of high temperature gas turbine - blade feature effects on stator performanc
A 25.4-cm (10-in) tip diameter turbine was tested to determine the effect of rotor radial tip cleara...
Partial admission performance was obtained for a 0.4 linear scale version of the LF460 lift fan turb...
Performance was obtained over a range of speeds and pressure ratios for a 0.4 linear scale version o...
A single-stage axial-flow turbine was investigated to determine the effect of increased stator throa...
An air cooled version of a single-stage, axial-flow turbine was investigated to determine aerodynami...
Two tip clearance configurations, one with a recess in the casing and the other with a reduced rotor...
The turbine developed design specific work output at design speed at a total pressure ratio of 6.745...
The aerodynamic performance of the inlet manifold and stator assembly of the compressor drive turbin...
The stage group performance of a 4 1/2 stage turbine with an average stage loading factor of 4.66 an...
The stage work distribution among the three stages was very close to the design value. The specific ...
A tip-turbine-driven fan of the type currently being used in wind tunnel tests of VTOL lift fan mode...
An effective method to improve gas turbine propulsive efficiency is to increase the bypass ratio. Wi...
A low speed wind tunnel test of a fixed lip inlet with engine, was performed. The inlet was close co...
A solid blade version of a single-stage, axial-flow turbine was investigated to determine its perfor...
Cold air study of high temperature gas turbine - blade feature effects on stator performanc
A 25.4-cm (10-in) tip diameter turbine was tested to determine the effect of rotor radial tip cleara...
Partial admission performance was obtained for a 0.4 linear scale version of the LF460 lift fan turb...
Performance was obtained over a range of speeds and pressure ratios for a 0.4 linear scale version o...
A single-stage axial-flow turbine was investigated to determine the effect of increased stator throa...
An air cooled version of a single-stage, axial-flow turbine was investigated to determine aerodynami...
Two tip clearance configurations, one with a recess in the casing and the other with a reduced rotor...
The turbine developed design specific work output at design speed at a total pressure ratio of 6.745...
The aerodynamic performance of the inlet manifold and stator assembly of the compressor drive turbin...
The stage group performance of a 4 1/2 stage turbine with an average stage loading factor of 4.66 an...
The stage work distribution among the three stages was very close to the design value. The specific ...
A tip-turbine-driven fan of the type currently being used in wind tunnel tests of VTOL lift fan mode...
An effective method to improve gas turbine propulsive efficiency is to increase the bypass ratio. Wi...
A low speed wind tunnel test of a fixed lip inlet with engine, was performed. The inlet was close co...
A solid blade version of a single-stage, axial-flow turbine was investigated to determine its perfor...
Cold air study of high temperature gas turbine - blade feature effects on stator performanc
A 25.4-cm (10-in) tip diameter turbine was tested to determine the effect of rotor radial tip cleara...