Numerical study on the effect of distortion of S-duct on flow field and performance of a full annulus transonic fan
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Zhi-yuan Cao
,
Cheng Song
Abstract
To reveal the influence of distortion of S-duct on the flow field and performance of transonic fan, full annulus unsteady numerical simulation was carried out under S-duct/fan integrated condition. This study focuses on the coupling flow of S-duct/fan integrated condition under peak efficiency (PE) condition and near stall (NS) condition. Results show that, compared with the condition that S-duct or fan is investigated alone, the distortion of S-duct is suppressed under S-duct/fan integrated condition. The curved structure of S-duct is the important reason for the flow migration from undistorted region to distortion region. Higher inlet relative Mach number and more work input of the rotor are observed in the counter-swirl region. The flow separation in S-duct is weakened under NS condition compared with that of PE condition. Counter-swirl region of blade tip has larger region of blockage, and rotating stall inception is most likely to occur in this region.
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This work was supported by National Natural Science Foundation of China (No. 51806174) and National Science and Technology Major Project (J2019-II-0011-0031). Thanks for the funding from AECC Sichuan Gas Turbine Research Establishment.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
Nomenclature
- C p
-
static pressure coefficient
- C ax
-
axial chord
- P t
-
total pressure
- P t1
-
total pressure of S-duct inlet
- P
-
static pressure
- P 1
-
static pressure of S-duct inlet
- ρ
-
density
- ρ 1
-
density of S-duct inlet under peak efficiency condition
- ρ 2
-
density of S-duct inlet under near stall condition
- V z
-
axial velocity
- V z1
-
axial velocity of S-duct inlet under peak efficiency condition
- V z2
-
axial velocity of S-duct inlet under near stall condition
- T t
-
total temperature
- T t1
-
total temperature of S-duct inlet under peak efficiency condition
- Ma
-
Mach number
- LE
-
leading edge
- TE
-
trailing edge
- DI
-
distortion intensity
- AIP
-
aerodynamic interface plane
- PE
-
peak efficiency condition
- NS
-
near stall condition
References
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© 2023 Walter de Gruyter GmbH, Berlin/Boston
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- Uncertainty quantification by probabilistic analysis of circular fins
- Influences of unbalance phase combination on the dynamic characteristics for a turboprop engine
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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
