Flow Field Measurement in Multi-stage Axial Compressor Stator by Using Multi-hole Pneumatic Probes
-
Wang Zhiqiang
,
Lu Bo
Abstract
In order to realize the stator’s internal flow field measurement of the multi-stage axial compressor, many different lengths of L-type five-hole probes and one four-hole probe have been designed. The detailed 3D (three-dimensional) flow fields in the stator blade passage of original and modified large scale compressors have been measured with the probes traversed by a probe traverse mechanism. The objective of the study is to assess the measurement method of adopting multi-hole pneumatic probes to achieve the flow field of stator vane passage. Results clearly demonstrate the flow field characteristics of stator blade passage in original and modified compressors. Furthermore, the reliability of adopted multi-hole pneumatic probes is validated. Therefore, it is proved that the probe traverse mechanism drives the L-type five-hole probe or other probe method can be applied to internal flow field measurements for the stator of large scale multi-stage compressors.
Funding statement: Funding: This study was co-supported by the National Natural Science Foundation of China (No. 51406080) and the Fundamental Research Funds for the Central Universities (No. NS2014022).
Nomenclature
- Ma
Mach number
Surface static pressure, Pa
Total pressure, Pa
Deviation angle, °
Yaw angle, °
Pitch angle, °
Total pressure loss coefficient
- Pt_rec
Total pressure recovery coefficient
Mass flow rate coefficient
Torque efficiency
Total-to-total pressure rise coefficient
Inlet axial velocity, m/s
Inlet mass flow rate, kg/s
Midspan rotational speed, m/s
Torque, Nm
Rotation speed, RPM
Subscript
- dyn
Dynamic
- in
Stator inlet plane
- out
Stator outlet plane
Abbreviations
- LSC1
Two-stage low speed compressor
- LSC2
Four-stage low speed compressor
- PS
Pressure surface
- SS
Suction surface
- CFD
Computational fluid dynamics
- DP
Design point
- IGV
Inlet guide vane
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© 2017 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Influence of Structural Parameters on the Performance of Vortex Valve Variable-Thrust Solid Rocket Motor
- Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector
- Investigation of HP Turbine Blade Failure in a Military Turbofan Engine
- Nozzle Admittance and Damping Analysis Using the LEE Method
- Software Development for EECU Platform of Turbofan Engine
- Numerical Study of the Propulsive Performance of the Hollow Rotating Detonation Engine with a Laval Nozzle
- Analysis of Compressor Surge in a Military Turbojet Engine: A Case Study
- The Combined Effects of Surface Roughness with Upstream Wakes on the Boundary Layer Development of an Ultra-High-Lift LPT Blade
- Numerical Investigation of a Model Scramjet Combustor Using DDES
- Flow Field Measurement in Multi-stage Axial Compressor Stator by Using Multi-hole Pneumatic Probes
- Effect of Air Pressure and Gutter Angle on Flame Stability and DeZubay Number for Methane-Air Combustion
- Control of Subsonic and Sonic Jets with Limiting Tabs
Artikel in diesem Heft
- Frontmatter
- Influence of Structural Parameters on the Performance of Vortex Valve Variable-Thrust Solid Rocket Motor
- Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector
- Investigation of HP Turbine Blade Failure in a Military Turbofan Engine
- Nozzle Admittance and Damping Analysis Using the LEE Method
- Software Development for EECU Platform of Turbofan Engine
- Numerical Study of the Propulsive Performance of the Hollow Rotating Detonation Engine with a Laval Nozzle
- Analysis of Compressor Surge in a Military Turbojet Engine: A Case Study
- The Combined Effects of Surface Roughness with Upstream Wakes on the Boundary Layer Development of an Ultra-High-Lift LPT Blade
- Numerical Investigation of a Model Scramjet Combustor Using DDES
- Flow Field Measurement in Multi-stage Axial Compressor Stator by Using Multi-hole Pneumatic Probes
- Effect of Air Pressure and Gutter Angle on Flame Stability and DeZubay Number for Methane-Air Combustion
- Control of Subsonic and Sonic Jets with Limiting Tabs
