Two-dimensional Compressible Flow in Centrifugal Compressors with Logarithmic-spiral Blades PDF Download
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Author: Gaylord O. Ellis Publisher: ISBN: Category : Air flow Languages : en Pages : 54
Book Description
Two numerical examples are presented for two-dimensional, compressible, nonviscous flow in centrifugal compressors with backward-curved, logarithmic-spiral blades. The two examples are for different blade angles and are compared with a third example for straight, radial blades. The numerical results are presented in tables of the stream-function distribution and in plots of the streamlines, constant Mach number lines, and constant-pressure-ratio lines. In addition, a simplified analysis for logarithmic-spiral blades is presented that can be used to determine flow conditions within the impeller except near the imperller tip and impeller inlet.
Author: Gaylord O. Ellis Publisher: ISBN: Category : Air flow Languages : en Pages : 54
Book Description
Two numerical examples are presented for two-dimensional, compressible, nonviscous flow in centrifugal compressors with backward-curved, logarithmic-spiral blades. The two examples are for different blade angles and are compared with a third example for straight, radial blades. The numerical results are presented in tables of the stream-function distribution and in plots of the streamlines, constant Mach number lines, and constant-pressure-ratio lines. In addition, a simplified analysis for logarithmic-spiral blades is presented that can be used to determine flow conditions within the impeller except near the imperller tip and impeller inlet.
Author: Louis P. Tosti Publisher: ISBN: Category : Airplanes Languages : en Pages : 692
Book Description
An investigation of the take-off, landing, and hovering-flight characteristics of a four-engine-transport, vertical take-off airplane has been conducted with a remotely controlled free-flight model. The model had four propellers distributed along the wing with thrust axes parallel to the fuselage axis. In order to produce direct lift for hovering flight, the propeller slipstream was deflected downward about 70 degrees by a full-span 65-percent-chord flap deflected 90 degrees and eight extensible vanes arranged above the wing in a cascade relation.
Author: Alois T. Sutor Publisher: ISBN: Category : Airplanes Languages : en Pages : 706
Book Description
Analytical expressions are derived to show the geometric, thermodynamic, and aerodynamic relations among compressor, turbine, and exhaust nozzle for a gas-turbine engine. For a known compressor performance map, a matching method is described to show some of the design compromises that must be made when the components are to be combined into a turbine-propeller engine. A method of predicting engine performance for a range of operating conditions from known component maps is presented. An illustrative example of the matching method and the performance analysis is presented, showing some of the practical limitations of engine operation.
Author: Gaylord O. Ellis
Author: Gaylord O. Ellis
Author: United States. National Advisory Committee for Aeronautics
Author: Louis P. Tosti
Author: 
Author: Alois T. Sutor
Author: 
Author: Business and Defense Services Administration
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: