Influence of Additional Leading-Edge Surface Roughness on Performances in Highly Loaded Compressor Cascade
-
Shaowen Chen
,
Hao Xu
Abstract
Experimental research has been carried out at low speed to investigate the effect of additional leading-edge surface roughness on a highly-loaded axial compressor cascade. A 5-hole aerodynamic probe has been traversed across one pitch to obtain the distribution of total pressure loss coefficient, secondary flow vector, flow angles and other aerodynamic parameters at the exit section. Meanwhile, ink-trace flow visualization has been used to measure the flow fields on the walls of cascades and a detailed topology structure of the flow on the walls has been obtained. Aerodynamic parameters and flow characteristics are compared by arranging different levels of roughness on various parts of the leading edge. The results show that adding surface roughness at the leading edge and on the suction side obviously influences cascade performance. Aggravated 3-D flow separation significantly increases the loss in cascades, and the loss increases till 60% when the level of emery paper is 80 mm. Even there is the potential to improve cascade performance in local area of cascade passage. The influence of the length of surface roughness on cascade performance is not always adverse, and which depends on the position of surface roughness.
©2015 by De Gruyter
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- Frontmatter
- Lean Blow-out Studies in a Swirl Stabilized Annular Gas Turbine Combustor
- Effect of Fuel Particle Size on the Stability of Swirl Stabilized Flame in a Gas Turbine Combustor
- Design Optimization of a Centrifugal Fan with Splitter Blades
- Influence of Additional Leading-Edge Surface Roughness on Performances in Highly Loaded Compressor Cascade
- Virtual Turbine Engine Test Bench Using MGET Test Device
- Gas Turbine Fault Diagnosis Using Probabilistic Neural Networks
- Vibration Characteristics of Squeeze Film Damper during Maneuver Flight
- Aerodynamic Optimization Design of Multi-stage Turbine Using the Continuous Adjoint Method
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Articles in the same Issue
- Frontmatter
- Lean Blow-out Studies in a Swirl Stabilized Annular Gas Turbine Combustor
- Effect of Fuel Particle Size on the Stability of Swirl Stabilized Flame in a Gas Turbine Combustor
- Design Optimization of a Centrifugal Fan with Splitter Blades
- Influence of Additional Leading-Edge Surface Roughness on Performances in Highly Loaded Compressor Cascade
- Virtual Turbine Engine Test Bench Using MGET Test Device
- Gas Turbine Fault Diagnosis Using Probabilistic Neural Networks
- Vibration Characteristics of Squeeze Film Damper during Maneuver Flight
- Aerodynamic Optimization Design of Multi-stage Turbine Using the Continuous Adjoint Method
- A Target Indirect Thrust Measurement Method of Pulse Detonation Engine
- Research on Modeling of Propeller in a Turboprop Engine
