Computation of tip clearance effect on characteristic of low pressure compressor of engine RD-33 - PDF (Russian)
Copyright (c) 2015 VESTNIK of the Samara State Aerospace University
Copyright (c) 2015 VESTNIK of the Samara State Aerospace University
ISSN 2542-0453 (Print)
ISSN 2541-7533 (Online)
User
Article Tools
Email this article (Login required)
Email the author (Login required)
Email this article (Login required)
Email the author (Login required)
Keywords
Combustion chamber
Gas turbine engine
Mathematical model
Spacecraft
algorithm
blade
combustion chamber
deformation
design
efficiency
endurance limit
experiment
finite element method
gas turbine engine
mathematical model
modeling
optimization
residual stresses
simulation
structure
turbine
×
User
Article Tools
Email this article (Login required)
Email the author (Login required)
Email this article (Login required)
Email the author (Login required)
Keywords
Combustion chamber
Gas turbine engine
Mathematical model
Spacecraft
algorithm
blade
combustion chamber
deformation
design
efficiency
endurance limit
experiment
finite element method
gas turbine engine
mathematical model
modeling
optimization
residual stresses
simulation
structure
turbine
Copyright (c) 2015 VESTNIK of the Samara State Aerospace University