Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor
-
Hefang Deng
,
Kailong Xia
,
Xiaoqing Qiang
,
Mingmin Zhu
Abstract
The cantilevered stator is a typical configuration for axial compressors. To gain insight into the effect of the hub leakage flow, unsteady simulations were performed in a multi-stage cantilevered compressor. The main goal is to gain a better understanding of the interaction between the upstream rotor wake and hub leakage flow, and the effect of the hub leakage flow on the downstream rotor performance. The results show that the upstream rotor wake affects the hub loading of the cantilevered stator periodically and thus changes the leakage flow characteristics, leading to an unsteady benefit in the vicinity of the hub. At the higher span region, the unsteady benefit depends on the reversible recovery and the wake-boundary layer interaction. The increased hub clearance not only causes performance degradation on the cantilevered stator but deteriorates the downstream rotor performance, especially for the absolute angle due to the mass flow redistribution. These results indicate great attention should be paid to the interaction between the upstream rotor wake and the hub leakage flow, and also the stage matching caused by the hub leakage flow in the design process of cantilevered compressors.
Funding source: National Natural Science Foundation of China
Award Identifier / Grant number: 52076129
Award Identifier / Grant number: 51576124
Funding source: United Innovation Center (UIC) of Aerothermal Technologies for Turbomachinery
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: 2017-Ⅱ-0004-0017
Funding source: Innovation Fund from Engineering Research Center of Aerospace Science and Technology, Ministry of Education
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Research ethics: Not applicable.
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Author contributions: The authors have accepted responsibility for the entire content of this manuscript and approved its submission.
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Competing interests: The authors state no competing interests.
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Research funding: This work is supported by the National Natural Science Foundation of China (No. 52076129, No. 51576124), the National Science and Technology Major Project (2017-II-0004-0017), the United Innovation Center (UIC) of Aerothermal Technologies for Turbomachinery, and Innovation Fund from Engineering Research Center of Aerospace Science and Technology, Ministry of Education.
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Data availability: The raw data can be obtained on request from the corresponding author.
Nomenclature
- C
-
chord, mm & absolute velocity, m/s
- C p
-
static pressure coefficient
- h
-
passage height, mm
- P
-
pressure, Pa
- s
-
clearance size, mm
- ΔS
-
entropy generation, J/kg/K
- t
-
time, s
- T
-
temperature, K & blade passing period, s
- U
-
circumferential velocity, m/s
- V
-
velocity, m/s
- W
-
relative velocity, m/s
Greek symbols
- ζ
-
entropy loss coefficient
Subscripts
- 1
-
inlet plane
- 2
-
exit plane
- ax
-
axial direction
- in
-
inlet
- o
-
total parameter
Abbreviations
- HL
-
highly loaded condition
- HLF
-
hub leakage flow
- HLV
-
hub leakage vortex
- LE
-
leading edge
- LSRC
-
low-speed axial research compressor
- PE
-
peak efficiency condition
- PS
-
pressure side
- R3
-
third rotor
- R4
-
fourth rotor
- S3
-
third stator
- SS
-
suction side
- TE
-
trailing edge
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© 2024 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Deep residual ensemble model for predicting remaining useful life of turbo fan engines
- Review of gliding arc plasma assisted ignition and combustion for gas turbine application
- Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor
- Determination of the modern marine single shaft gas turbine rotor blades fatigue strength parameters
- Role of different cavity flame holders on the performance characteristics of supersonic combustor
- Thermal performance of teardrop pin fins and zig zag ribs in a wedge channel
- Investigation of varying tip clearance gap and operating conditions on the fulfilment of low-speed axial flow fan
- Upgraded one-dimensional code for the design of a micro gas turbine mixed flow compressor stage with various crossover diffuser configurations
- Performance evaluation of a scramjet engine utilizing varied cavity aft wall divergence with parallel injection in a reacting flow field
- Speed controller design for turboshaft engine using a high-fidelity AeroThermal model
- Multi-nozzle thrust matching control of STOVL engine
- Numerical analysis of brush seal hysteresis based on orthogonal test method
- Conjugated heat transfer characteristics of ribbed-swirl cooling in turbine blade under rotation condition
- Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine
- Flight trajectory optimization study of a variable-cycle turbine-based combined cycle engine hypersonic vehicle based on airframe/engine integration
- Constant temperature line identification on prototype gas turbine combustor with multi-colour change coating
- Sensitivity analysis of aero-engine performance optimization control system and its hardware test verification
- Compensator based improved model predictive control for Aero-engine
- Ignition experimental study based on rotating gliding arc
Articles in the same Issue
- Frontmatter
- Deep residual ensemble model for predicting remaining useful life of turbo fan engines
- Review of gliding arc plasma assisted ignition and combustion for gas turbine application
- Interaction effects between the rotor wake and hub leakage flow in a multi-stage cantilevered compressor
- Determination of the modern marine single shaft gas turbine rotor blades fatigue strength parameters
- Role of different cavity flame holders on the performance characteristics of supersonic combustor
- Thermal performance of teardrop pin fins and zig zag ribs in a wedge channel
- Investigation of varying tip clearance gap and operating conditions on the fulfilment of low-speed axial flow fan
- Upgraded one-dimensional code for the design of a micro gas turbine mixed flow compressor stage with various crossover diffuser configurations
- Performance evaluation of a scramjet engine utilizing varied cavity aft wall divergence with parallel injection in a reacting flow field
- Speed controller design for turboshaft engine using a high-fidelity AeroThermal model
- Multi-nozzle thrust matching control of STOVL engine
- Numerical analysis of brush seal hysteresis based on orthogonal test method
- Conjugated heat transfer characteristics of ribbed-swirl cooling in turbine blade under rotation condition
- Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine
- Flight trajectory optimization study of a variable-cycle turbine-based combined cycle engine hypersonic vehicle based on airframe/engine integration
- Constant temperature line identification on prototype gas turbine combustor with multi-colour change coating
- Sensitivity analysis of aero-engine performance optimization control system and its hardware test verification
- Compensator based improved model predictive control for Aero-engine
- Ignition experimental study based on rotating gliding arc
