Add to ORKGA 25.4-cm (10-in) tip diameter turbine was tested to determine the effect of rotor radial tip clearance on turbine overall performance. The test turbine was a half-scale model of a 50.8-cm-(20-in.-) diameter research turbine designed for high-temperature core engine application. The test turbine was fabricated with solid vanes and blades with no provision for cooling air and tested at much reduced inlet conditions. The tests were run at design speed over a range of pressure ratios for three different rotor clearances ranging from 2.3 to 6.7 percent of the annular blade passage height. The results obtained are compared to the results obtained with three other turbines of varying amounts of reaction
Modifying the original turbine by closing down the first-rotor throat area and shrouding the first a...
The aerodynamic design, the performance, and an internal loss breakdown were examined for a 15.04 cm...
The efficiency of aircraft gas turbine engines is sensitive to the distance between the tips of its ...
A solid, half-scale model of a 50.8-cm (20-in) research turbine designed for a high temperature core...
Two tip clearance configurations, one with a recess in the casing and the other with a reduced rotor...
Performance of two-stage axial flow turbine operating at different rotor tip clearanc
Effect of rotor tip clearance on performance of 5-inch single-stage axial flow turbin
The effects of high pressure turbine clearance changes on engine and module performance was evaluate...
Total turbine blade performance was investigated while changing the blade tip clearance in three way...
An air cooled version of a single-stage, axial-flow turbine was investigated to determine aerodynami...
System studies have shown the benefits of reducing blade tip clearances in modern turbine engines. M...
Cold air study of high temperature gas turbine - blade feature effects on stator performanc
The rotor tip clearance was obtained by use of a recess in the casing above the rotor blades and als...
Performance was obtained over a range of speeds and pressure ratios for a 0.4 linear scale version o...
Gas turbine compressor and turbine blade tip clearance (i.e., the radial distance between the blade ...
Modifying the original turbine by closing down the first-rotor throat area and shrouding the first a...
The aerodynamic design, the performance, and an internal loss breakdown were examined for a 15.04 cm...
The efficiency of aircraft gas turbine engines is sensitive to the distance between the tips of its ...
A solid, half-scale model of a 50.8-cm (20-in) research turbine designed for a high temperature core...
Two tip clearance configurations, one with a recess in the casing and the other with a reduced rotor...
Performance of two-stage axial flow turbine operating at different rotor tip clearanc
Effect of rotor tip clearance on performance of 5-inch single-stage axial flow turbin
The effects of high pressure turbine clearance changes on engine and module performance was evaluate...
Total turbine blade performance was investigated while changing the blade tip clearance in three way...
An air cooled version of a single-stage, axial-flow turbine was investigated to determine aerodynami...
System studies have shown the benefits of reducing blade tip clearances in modern turbine engines. M...
Cold air study of high temperature gas turbine - blade feature effects on stator performanc
The rotor tip clearance was obtained by use of a recess in the casing above the rotor blades and als...
Performance was obtained over a range of speeds and pressure ratios for a 0.4 linear scale version o...
Gas turbine compressor and turbine blade tip clearance (i.e., the radial distance between the blade ...
Modifying the original turbine by closing down the first-rotor throat area and shrouding the first a...
The aerodynamic design, the performance, and an internal loss breakdown were examined for a 15.04 cm...
The efficiency of aircraft gas turbine engines is sensitive to the distance between the tips of its ...