Numerical investigation of a variable stator vane with nonuniform partial radial gaps in an annular compressor cascade
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Yimin Zhang
,
Shaowen Chen
,
Yueqi Liu
Abstract
A variable stator vane (VSV) with nonuniform partial radial gaps is numerically investigated in an annular compressor cascade. Five adjusting angles (α = −5.5°, −5°, 0°, 5° and 10°) are chosen to simulate different working conditions. The VSV is adjusted in negative direction means that the stagger angle increases and the VSV is more closed. Since the VSV is installed in an annular cascade, the heights of the partial gaps are nonuniform and reaches 3.8% of the span. Results show that as the VSV is adjusted negatively, the total pressure loss rises by 20.3% and a huge area of corner separation appears. The outflow angle is also more distorted along radial direction. Comparisons with a fixed-configuration stator show that although the VSV would cause higher loss, it indeed plays an important role in adjusting the outflow angle.
Funding source: National Nature Science Foundation of China
Award Identifier / Grant number: 52076052
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: Y2019-VIII-0013-0174
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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: The authors disclose receipt of the following financial support for the research of this article: This work was supported by the National Nature Science Foundation of China (Grant No. 52076052) and the National Science and Technology Major Project (Grand No. Y2019-VIII-0013-0174).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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- Frontmatter
- The International Journal of Turbo and Jet Engines
- The aerothermodynamic cycle optimal design of a turbofan engine
- Multi-condition design optimization of groove flow control technique in an axial-flow pump
- Analysis on impulse characteristics of pulse detonation engine with nozzles
- Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor
- Optimization of Kiel geometry for better recovery factor in high temperature measurement in aero gas turbine engine
- Applicability of correlational data-mining to small-scale turbojet performance map generation
- Effect of multi-zone effusion cooling on an adiabatic flat plate for gas turbine application
- Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence
- Modeling and analysis of 3D radiative heat transfer in combustor
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- Optimization-based transient control of turbofan engines: a sequential quadratic programming approach
- Investigations on the interaction between the front and aft purge flow and the downstream vane of 1.5-stage turbine
- A study on design optimization for compressor blisks
- Exploration of an unconventional validation tool to investigate aero engine transonic fan flutter signature
- Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor
- Predicting remaining useful life of turbofan engines using degradation signal based echo state network
- Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system
- Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
- Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor
- Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
- Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions
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- Gas dynamic analysis of the modern single shaft gas turbine engine flow path
- Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview
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- The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall
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- Effect of self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor
- Research on temperature rise characteristics of end V-groove ring seal
- Research on the influence of honeycomb cell blockage on the seal leakage characteristics
- Vortex structure control based bleed in axial compressor cascade with tip clearance using large eddy simulation
- Development and application of a profile loss model considering the low-Re effect in low-pressure turbine
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- Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications
- Multidisciplinary sensitivity analysis for turbine blade considering thickness uncertainties
- Accurate measurement and evaluation method of axial compressor efficiency under the influence of multiple factors
- Control mechanism of secondary flow in a turbine cascade with non-axisymmetric endwall profiling under Co-rotating incoming vortex
- Infrared simulation of aircraft rear fuselage based on a coupled CFD method
- Effect of multi-hole trench cooling on an adiabatic flat plate for gas turbine application
- Numerical study of transition process in different zones of a compressor cascade channel
