Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
-
Jiayi Zhao
,
Wanyang Wu
Abstract
The controllable speed casing is a novel casing treatment approach that makes partial casing rotate at adjustable and proper speed to achieve stability expansion. Structural parameters of casing treatment are found to influence the effect of stability expansion by many studies. In this paper, the effect of the ending position of the rotatable ring in controllable speed casing on the tip leakage flow and the stability expansion was studied numerically. The results show that when the rotatable ring rotates at 30 % and 50 % rotor design speed, the controllable speed casing achieves the stability expansion of the compressor rotor no matter where the ending position is. The upstream movement of the ending position decreases the axial pressure gradient in the middle and rear of the tip passage. It pushes the shock wave downstream, which reduces blockage region at tip leading edge. The upstream movement of the ending position contributes to an approximately linear increase in the stable operating margin.
Funding source: National Natural Science Foundation of China
Award Identifier / Grant number: 52236005
Funding source: Science Center for Gas Turbine Project
Award Identifier / Grant number: P2022-B-II-007-001
Nomenclature
- SP
-
starting position
- EP
-
ending position
- SC
-
stationary casing
- RC
-
rotatable ring
- PE
-
peak efficiency point
- SM
-
stable operating margin
- SMI
-
stable operating margin improvement
- C ax
-
tip axial chord length
- AVDR
-
axial velocity density ratio
- π
-
total pressure ratio
- m
-
mass flow rate (kg/s)
- w
-
relative velocity magnitude (m/s)
- ψ t
-
tangential velocity coefficient
- w θ
-
relative tangential velocity (m/s)
- C p
-
static pressure coefficient
- Ma
-
mach number
- LFA
-
leakage flow angle (°)
- p
-
static pressure (Pa)
- ρ
-
density (kg/m³)
- U
-
velocity at infinity (m/s)
- V t
-
blade tip tangential speed (m/s)
- V z
-
axial velocity (m/s)
- Grad_Z C p
-
C p gradient along axis
-
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.
-
Research funding: The authors would like to thank the National Natural Science Foundation of China (NSFC, Grant Nos. 52236005.) and Science Center for Gas Turbine Project (P2022-B-II-007-001) for funding this work.
-
Competing interests: The authors state no conflict of interest.
-
Data availability: The raw data can be obtained on request from the corresponding author.
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Articles in the same Issue
- Frontmatter
- Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
- Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor
- In-service load calculation surrogate models for high-pressure turbine blade life digital twin
- Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement
- Study on one-dimensional performance prediction of multi-stage axial turbine based on the blade height
- Dynamic characteristics of open-ends squeeze film dampers with air ingestion
- Fluid flow in a microdiffuser at small Reynolds numbers
- A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
- Effects of turbulence and flamelet combustion modelling on the CFD simulation of a dual inlet ramjet combustor
- Design and combustion characteristics analysis of a static shaft turbofan engine
- Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
- Endwall heat transfer in wedge channel with teardrop pin fins, circular fins and oblong pin fins
- Virtual deflection with synthetic jet actuators at high angles of attack
- Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control
- Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0
- Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
- Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor
- Effect of velocity ratio and Mach number on thin lip coaxial jet
- C conjugate heat transfer simulation of swirl internal cooling on blade leading edge
- Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine
- Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine
- Numerical investigation of force over the horizontal jet tab of various sector angle fixed to the convergent-divergent nozzle exit
