Influences of unbalance phase combination on the dynamic characteristics for a turboprop engine
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Wang Qing-ping
,
Zhang Wen-chao
Abstract
To reduce excessive vibration of a turboprop engine with qualified balanced compressor and turbine rotor, the finite element model of the rotor system was established. The magnitude, axial distribution and especially the phase combinations of the residual unbalances were considered and optimized. Based on the numerical results, the whole engine tests were conducted for verification. The numerical and experimental results show that the vibration level of the rotor system can be significantly reduced by only changing the phase combination of the residual unbalances. The magnitude, axial distribution of residual unbalance and rotational speed of the rotor play a very important role in determining the optimal phase combination. The optimal phase combination under different rotational speeds might be conflicting, and reasonably designed optimization would be a feasible solution. The findings of the research can provide important reference for the design and troubleshooting for similar industrial turbine engines.
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Author contribution: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: None declared.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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Articles in the same Issue
- Frontmatter
- Numerical investigations of heat transfer characteristics using oblong fins and circular fins in a wedge channel
- An efficient flow control technique based on co-flow jet and multi-stage slot circulation control applied to a supercritical airfoil
- Reacting flow analysis in scramjet engine: effect of mass flow rate of fuel and flight velocity
- Installed performance seeking control based on supersonic variable inlet/engine coupling model
- Effect of zero penetration angle chevrons in supersonic jet noise and screech tone mitigation
- The aerodynamic performance degradation analysis of a small high bypass turbofan engine compression system with fan rotor blade leading edge erosion
- Flow structure comparison of film cooling versus hybrid cooling: a CFD study
- Experimental investigation on a Jeffcott rotor with combined coupling misalignment using time-frequency analysis
- Effect of free boundary on the performance of single expansion nozzle
- Optimization and numerical investigation of combined design of blade and endwall on rotor 67
- Numerical study on the effect of distortion of S-duct on flow field and performance of a full annulus transonic fan
- Research on a high-precision real-time improvement method for aero-engine component-level model
- Uncertainty quantification by probabilistic analysis of circular fins
- Influences of unbalance phase combination on the dynamic characteristics for a turboprop engine
- Study on the water ingestion performance of compressor with inlet particle separator
- The role of volume effect on the transient behavior of a transonic compressor
- Experimental analysis of performance and tip dynamic pressure in a compressor cascade with high-speed moving endwall
- Numerical study of the impact of hydrogen addition, swirl intensity and equivalence ratio on methane-air combustion
- Active subspace-based performance analysis of supersonic through-flow fan rotor
- Assessment of performance degradation of a mixed flow low bypass turbofan engine through GasTurb simulation
- Numerical investigation of tip clearance flow in a variable geometry turbine with non-uniform partial clearance
