Author: Massachusetts Institute of Technology. Gas Turbine LaboratoryPublisher:
ISBN:
Category : Compressors
Languages : en
Pages : 50
Book Description
Three-dimensional Inviscid Flow Through a Highly-loaded Transonic Compressor Rotor
Author: Massachusetts Institute of Technology. Gas Turbine LaboratoryPublisher:
ISBN:
Category : Compressors
Languages : en
Pages : 50
Book Description
Scientific and Technical Aerospace Reports
Author: Transonic Flow Problems in Turbomachinery
Author: Thomas Charles AdamsonPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 724
Book Description
NASA Technical Memorandum
Author: Applied Mechanics Reviews
Author: Through-flow Calculations in Axial Turbomachinery
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Propulsion and Energetics PanelPublisher:
ISBN:
Category : Impellers
Languages : en
Pages : 256
Book Description
Boundary Layer and Wake Modifications to Compressor Design Systems
Author: Arun K. SehraPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 228
Book Description
The effect of blade-to-blade flow variations on the mean flow field of a highly loaded transonic axial flow compressor was invesitaged. The theoretical approach centered around modeling of three important phenomena associated with blade-to-blade flow fluctuations, which control the mean momentum and energy transfer processes. Apparent stresses were introduced into the mean flow momentum equations by pitchwise averaging. Loss concept of mean relative total pressure, due to conversion of mean flow kinetic energy to the energy of fluctuations, was introduced. Based on this concept, mean rothalpy and the production of apparent entropy were defined. An expression for mean rothalpy variation along the streamline was derived by pitchwise averaging of the energy equation. Mean flow equations suitable for the streamline curvature computational scheme were developed which include these three effects. Apparent stresses, mean rothalpy and apparent entropy variations were calculated from measured velocity fluctuations. The revised streamline curvature procedure was then used to predict the axisymmetric (peripheral mean) flow. The agreement of rotor outlet tangential velocity is excellent reproducing an unusual peak which is not explainable by usual techniques. The results showed that 3-D inviscid effects do not significantly modify the mean flow, and that the direct effect of apparent stresses on the mean flow is also small.
International Aerospace Abstracts
Author: Aeronautical Engineering
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
AGARD Conference Proceedings
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and DevelopmentPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 644
Book Description