Add to ORKGPerformance characteristics and efficiency determined for air cooled turbojet engine suitable for supersonic speed fligh
The effect of turbofan engine overall pressure ratio, fan pressure ratio, and ductburner temperature...
The effects of turbine-blade cooling on engine performance were analytically investigated for a turb...
Engine performance and mission studies were performed for turbofan engines with supersonic through-f...
The efficiency of a two-stage turbine is discussed. The turbine efficiency was 0.932 for equivalent ...
Modifying the original turbine by closing down the first-rotor throat area and shrouding the first a...
An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed...
Design of single-stage turbine for rotor entering at supersonic speed - performance characteristic
Efficiency evaluation of two-stage turbine with low ratio of blade to jet speed suitable for bleed-t...
A blade design study is presented for a two-stage air-cooled turbine suitable for flight at a Mach n...
An 8.00-in mean diameter two-stage turbine was investigated over a range of speeds from 0 to 110 per...
Over-all performance of a two-stage turbine from a J35-A-23 turbojet engine is presented. Limiting b...
Turbine aerodynamic and cooling requirements for turbojet powered Mach 3 transport using methane fue
Performance characteristics of high-weight flow, low pressure ratio, single stage turbine rotor and ...
Flow analysis to determine turbine efficiency as function of inlet temperature for two stage turbin
The experimental performance of a modified turbine for driving a supersonic compressor is presented ...
The effect of turbofan engine overall pressure ratio, fan pressure ratio, and ductburner temperature...
The effects of turbine-blade cooling on engine performance were analytically investigated for a turb...
Engine performance and mission studies were performed for turbofan engines with supersonic through-f...
The efficiency of a two-stage turbine is discussed. The turbine efficiency was 0.932 for equivalent ...
Modifying the original turbine by closing down the first-rotor throat area and shrouding the first a...
An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed...
Design of single-stage turbine for rotor entering at supersonic speed - performance characteristic
Efficiency evaluation of two-stage turbine with low ratio of blade to jet speed suitable for bleed-t...
A blade design study is presented for a two-stage air-cooled turbine suitable for flight at a Mach n...
An 8.00-in mean diameter two-stage turbine was investigated over a range of speeds from 0 to 110 per...
Over-all performance of a two-stage turbine from a J35-A-23 turbojet engine is presented. Limiting b...
Turbine aerodynamic and cooling requirements for turbojet powered Mach 3 transport using methane fue
Performance characteristics of high-weight flow, low pressure ratio, single stage turbine rotor and ...
Flow analysis to determine turbine efficiency as function of inlet temperature for two stage turbin
The experimental performance of a modified turbine for driving a supersonic compressor is presented ...
The effect of turbofan engine overall pressure ratio, fan pressure ratio, and ductburner temperature...
The effects of turbine-blade cooling on engine performance were analytically investigated for a turb...
Engine performance and mission studies were performed for turbofan engines with supersonic through-f...