Turbo-machineries,　as　key　components,　have　a　wide　utilization　in　fields　of　civil,　aerospace,　and　mechanical　engineering.　By　calculating　natural　frequencies　and　dynamical　deformations,　we　have　explained　the　rationality　of　the　series　form　for　the　aerodynamic　force　of　the　blade　under　the　subsonic　flow　in　our　earlier　studies.　In　this　paper,　the　subsonic　aerodynamic　force　obtained　numerically　is　applied　to　the　low　pressure　compressor　blade　with　a　low　constant　rotating　speed.　The　blade　is　established　as　a　pre-twist　and　presetting　cantilever　plate　with　a　rectangular　section　under　combined　excitations,　including　the　centrifugal　force　and　the　aerodynamic　force.　In　view　of　the　first-order　shear　deformation　theory　and　von-Karman　nonlinear　geometric　relationship,　the　nonlinear　partial　differential　dynamical　equations　for　the　warping　cantilever　blade　are　derived　by　Hamilton＇s　principle.　The　second-order　ordinary　differential　equations　are　acquired　by　the　Galerkin　approach.　With　consideration　of　1:3　internal　resonance　and　1/2　sub-harmonic　resonance,　the　averaged　equation　is　derived　by　the　asymptotic　perturbation　methodology.　Bifurcation　diagrams,　phase　portraits,　waveforms,　and　power　spectrums　are　numerically　obtained　to　analyze　the　effects　of　the　first　harmonic　of　the　aerodynamic　force　on　nonlinear　dynamical　responses　of　the　structure.