Optimization and numerical investigation of combined design of blade and endwall on rotor 67
-
Xin Li
,
Weiwei Li
Abstract
In this work, a combined design of blade and endwall using the Extended Free Form Deformation technique is proposed and implemented on a transonic compressor rotor (the NASA Rotor 67). The best combined design is explored by numerical investigations and optimization via Kriging surrogate model method. As a result, by only modifying the hub and blade under 15 % span, the peak adiabatic efficiency is increased by 0.4 % and the overall aerodynamic performance for all operating conditions is also improved. An analysis shows that the enlarged dihedral angle between the hub and blade restrains boundary layer intersection and development. Meanwhile, the optimized hub changes the pressure distribution and prevents migration of cross-flow. As a result, the low-energy flow in the corner is accelerated downstream and the separation is limited, leading to an effective improvement in throughflow capability and aerodynamic performance in the corner region.
Acknowledgments
This work was sponsored by the National Major Science and Technology Project of China (Nos. 2017-II-0006-0020, 2017-II-0001-0013 and 2019-II-0003-0023).
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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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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
Nomenclature
- symbol
-
meaning and unit
- i
-
spanwise coordinate
- j
-
pitchwise coordinate
- k
-
streamwise coordinate
- η
-
adiabatic efficiency
- T 0
-
total temperature (K)
- P 0
-
total pressure (Pa)
- Cp
-
pressure coefficient
- LE
-
leading edge
- TE
-
trailing edge
- PS
-
pressure surface
- SS
-
suction surface
- FFD
-
free form deformation
- RSM
-
response surface model
- EFFD
-
extended free form deformation
- Ma
-
mach number
- TKE
-
turbulence kinetic energy (m2/s2)
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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
