Add to ORKGThe stator and rotor blade hub sections designed for a high\ud pressure turbine stage were studied in detail for their\ud aerodynamic and heat transfer characteristics . The profile\ud sections were tested in the National Aeronautical Laboratory\ud Cascade Tunnels over a range of exit flow Mach numbers . The flow field and heat transfer characteristics of the cascades were also code based on Denton's method and the boundary layer code incorporating K- E turbulence model. The results indicated that there was a scope for improving the blade\ud profile sections for high Mach number applications
A combined experimental and analytical program was conducted to examine the effects of inlet turbule...
The first part of the paper presents commissioning of a single-stage high-pressure (HP) turbine empl...
Thesis. 1976. Sc.D.--Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.Mi...
The stator and rotor blade hub sections designed for a high pressure turbine stage were studied in ...
The stator and rotor blade hub sections designed for a high pressure turbine stage were studied in d...
The stator and rotor blade hub sections designed for a\ud High pressure turbine stage were studied i...
High pressure turbine blade profile sections of GTX-35 VS engine were analysed by 2D-Euler code and ...
The results of aerodynamic and heat transfer experimental investigations performed in a high Reynold...
Higher operating temperatures increase the efficiency of aircraft gas turbine engines, but can also ...
A major addition to European research facilities is the Oxford University Engineering Laboratory (O....
This work is motivated by the need to accurately predict heat transfer in turbomachinery. For effici...
The quest for higher performances and durability of modern aero-engines requires the understanding o...
This is Volume 3 - Heat Transfer Data Tabulation (65 percent Axial Spacing) of a combined experiment...
The Primary basis for heat transfer analysis of turbine airfoils is experimental data obtained in li...
Experimental temperatures are presented for an air-cooled turbine rotor blade tested in an engine. T...
A combined experimental and analytical program was conducted to examine the effects of inlet turbule...
The first part of the paper presents commissioning of a single-stage high-pressure (HP) turbine empl...
Thesis. 1976. Sc.D.--Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.Mi...
The stator and rotor blade hub sections designed for a high pressure turbine stage were studied in ...
The stator and rotor blade hub sections designed for a high pressure turbine stage were studied in d...
The stator and rotor blade hub sections designed for a\ud High pressure turbine stage were studied i...
High pressure turbine blade profile sections of GTX-35 VS engine were analysed by 2D-Euler code and ...
The results of aerodynamic and heat transfer experimental investigations performed in a high Reynold...
Higher operating temperatures increase the efficiency of aircraft gas turbine engines, but can also ...
A major addition to European research facilities is the Oxford University Engineering Laboratory (O....
This work is motivated by the need to accurately predict heat transfer in turbomachinery. For effici...
The quest for higher performances and durability of modern aero-engines requires the understanding o...
This is Volume 3 - Heat Transfer Data Tabulation (65 percent Axial Spacing) of a combined experiment...
The Primary basis for heat transfer analysis of turbine airfoils is experimental data obtained in li...
Experimental temperatures are presented for an air-cooled turbine rotor blade tested in an engine. T...
A combined experimental and analytical program was conducted to examine the effects of inlet turbule...
The first part of the paper presents commissioning of a single-stage high-pressure (HP) turbine empl...
Thesis. 1976. Sc.D.--Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.Mi...