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Blading Design for Axial Turbomachines.

ADA211103

Publication Date	1989
Page Count	213
Abstract	The efficiency and performance of the turbomachinery components of future aero engines can considerably be improved by applying recent advances in understanding the flow behavior of axial compressor and turbine bladings. Thus, the optimal profile pressure distribution as input for new blading design methods has an important effect on losses and flow deflection. The boundary-layer behaviour has to be carefully taken into account with respect to laminar/turbulent transition, shock/boundary-layer interaction and separation effects. In addition to these aerodynamical questions, unsteady effects and the limitations from structural and vibrational conditions also have to be taken into account. The Lecture Series deals with two main topics: -design methods and their principles, limitations - application to axial compressors and turbines, experience. Contents: Review of Turbomachinery Blading Design Problems; Design Criteria for Optimal Blading Design; Overview on Blading Design Methods; Performance Prediction for Axial-Flow Compressor and Turbine Blading; Blading Design for Multi-Stage HP Compressors; Transonic and Supersonic Compressor Blading Design; Blading Design for Cooled High-Pressure Turbines; and Aerodynamic Design of Low Pressure Turbines. (jhd)
Keywords	Turbine blades Axial flow compressor blades Aerodynamics Axial flow compressors Boundary layer Cooling Deflection High pressure Interactions Laminar flow Lectures Low pressure Optimization Pressure distribution Profiles Separation Shock Structural properties Supersonic characteristics Transitions Transonic characteristics Turbomachinery Turbulence Vibration Foreign technology Gas turbines NATO Furnished
Source Agency	Non Paid ADAS
NTIS Subject Category	81D - Jet & Gas Turbine Engines
Corporate Authors	Advisory Group for Aerospace Research and Development, Neuilly-sur-Seine (France).
Supplemental Notes	Presented at the Propulsion and Energetics Panel and the Consultant and Exchange Programme of AGARD, Toronoto, Canada, 1-2 Jun 89 and Cologne, Germany, 15-16 Jun 89.
Document Type	Technical Report
Title Note	Lecture series.
NTIS Issue Number	198923

Blading Design for Axial Turbomachines.

Blading Design for Axial Turbomachines.
ADA211103

Publication Date	1989
Page Count	213
Abstract	The efficiency and performance of the turbomachinery components of future aero engines can considerably be improved by applying recent advances in understanding the flow behavior of axial compressor and turbine bladings. Thus, the optimal profile pressure distribution as input for new blading design methods has an important effect on losses and flow deflection. The boundary-layer behaviour has to be carefully taken into account with respect to laminar/turbulent transition, shock/boundary-layer interaction and separation effects. In addition to these aerodynamical questions, unsteady effects and the limitations from structural and vibrational conditions also have to be taken into account. The Lecture Series deals with two main topics: -design methods and their principles, limitations - application to axial compressors and turbines, experience. Contents: Review of Turbomachinery Blading Design Problems; Design Criteria for Optimal Blading Design; Overview on Blading Design Methods; Performance Prediction for Axial-Flow Compressor and Turbine Blading; Blading Design for Multi-Stage HP Compressors; Transonic and Supersonic Compressor Blading Design; Blading Design for Cooled High-Pressure Turbines; and Aerodynamic Design of Low Pressure Turbines. (jhd)
Keywords	Turbine blades Axial flow compressor blades Aerodynamics Axial flow compressors Boundary layer Cooling Deflection High pressure Interactions Laminar flow Lectures Low pressure Optimization Pressure distribution Profiles Separation Shock Structural properties Supersonic characteristics Transitions Transonic characteristics Turbomachinery Turbulence Vibration Foreign technology Gas turbines NATO Furnished
Source Agency	Non Paid ADAS
NTIS Subject Category	81D - Jet & Gas Turbine Engines
Corporate Authors	Advisory Group for Aerospace Research and Development, Neuilly-sur-Seine (France).
Supplemental Notes	Presented at the Propulsion and Energetics Panel and the Consultant and Exchange Programme of AGARD, Toronoto, Canada, 1-2 Jun 89 and Cologne, Germany, 15-16 Jun 89.
Document Type	Technical Report
Title Note	Lecture series.
NTIS Issue Number	198923