Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
-
Honghui Xiang
,
Ning Ge
Abstract
Aiming at resolving the problem of measuring probe blockage effect in the performance experiments of high loaded axial flow compressors, an experimental investigation of the probe support disturbance effect on the compressor cascade flow field was conducted on a transonic plane cascade test facility. The influence characteristics of the probe support tail structure on the cascade downstream flow field under different operation conditions were revealed through the detailed analysis of the test data. The results show that the aerodynamic coupling effect between the upstream probe support wake and the downstream cascade flow field is very intense. Some factors, i. e. inlet Mach number, probe support tail structure, circumferential installing position of probe, and axial distance from the probe support trailing edge to the downstream cascade, are found to have the most impact on the probe disturbance intensity. Under high speed inlet flow condition, changing probe support tail structure can’t inhibit probe support disturbance intensity effectively. Whereas under low speed inlet flow condition, compared with the cylindrical probe, the elliptic probe can inhibit probe support wake loss and reduce disturbance effects on the downstream cascade flow field.
Funding statement: This work has been supported by the Jiangsu Province ordinary university graduate research innovation project (No. KYLX15_0260).
Nomenclature
- H
height of blade
- L
distance from probe to the wall
total pressure
- P
static pressure
total temperature
- T
static temperature
- δ
total pressure loss coefficient
flow density
flow velocity
measurement position of blade surface static pressure
long axis radius
short axis radius
- Subscripts
- 1
inlet
- 2
outlet
- w
wall
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Optimization Design and Experimental Study of a Two-disk Rotor System Based on Multi-Island Genetic Algorithm
- Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating speed
- Numerical Prediction of Impact of Clearance on Rotordynamic Coefficients for Labyrinth Brush Seal
- CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
- Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
- Soot Formation and Its Effect in an Aero Gas Turbine Combustor
- Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
- Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
- CFD Design Study of a Pressure Probe for Centerline Static Pressure Measurement in Supersonic Ejectors
- The Performance of the Self-Supplying Vortex Generator Jets on a High-Speed Compressor Cascade
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Optimization Design and Experimental Study of a Two-disk Rotor System Based on Multi-Island Genetic Algorithm
- Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating speed
- Numerical Prediction of Impact of Clearance on Rotordynamic Coefficients for Labyrinth Brush Seal
- CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
- Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
- Soot Formation and Its Effect in an Aero Gas Turbine Combustor
- Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
- Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
- CFD Design Study of a Pressure Probe for Centerline Static Pressure Measurement in Supersonic Ejectors
- The Performance of the Self-Supplying Vortex Generator Jets on a High-Speed Compressor Cascade
