Separation Control by Slot Jet in a Critically Loaded Compressor Cascade
-
Jiaguo Hu
,
Rugen Wang
Abstract
Separation in compressor cascade triggers flow loss and instability. This paper presents a passive flow control method by introducing a slot into the blade. The slot induces self-adapted jet, while the jet flow is used to suppress cascade’s separation. To study the flow control effect, experiments were conducted and flow field details were given by validated numerical simulations. The results show that a well-designed slot carries adequate jet airflow from pressure side (PS) to suction side (SS) due to the great pressure fall between the two sides. The jet airflow delays suction side separation within specific incidence angles, so the performance of cascade achieves considerable improvements. It enables to be concluded that the slot carries jet flow to SS separation zone, and then the self-adapted jet flow re-energizes low momentum fluid and suppresses vortices in the separation which are negative to the cascade flow.
Funding statement: The research work presented in this paper is funded by the National Natural Science Foundation of China (51336011).
Nomenclature
- ω
Total pressure loss
- φ
Static pressure rise
Flow turning angle (°)
- h
Blade height
- θ
Cascade turning angle
- γ
Stagger angle
- C
Chord length
- i
Attack angle (°)
- –
Relative parameter
- *
Total parameter
- 1
Inlet
- 2
Outlet
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© 2018 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- The Effect of Pulsed Injection on Supersonic Shear Layer Mixing in a Scramjet Combustor
- Entropy Generation Calculation of a Turbofan Engine: A Case of CFM56-7B
- Separation Control by Slot Jet in a Critically Loaded Compressor Cascade
- An Impingement Cooling Using Swirling Jets Induced by Helical Rod Swirl Generators
- Studies on Stepped Air Ejector Diffusers incorporating Heat Transfer Effects
- Assessment of Analytical Predictions for Radial Growth of Rotating Labyrinth Seals
- Ground Simulation of High Altitude Test of Turbo-Refrigeration Cycle
- Investigations on the Film Cooling of Counter-Inclined Film-Hole Row Structures for Turbine Vane Leading Edge
Articles in the same Issue
- Frontmatter
- Original Research Articles
- The Effect of Pulsed Injection on Supersonic Shear Layer Mixing in a Scramjet Combustor
- Entropy Generation Calculation of a Turbofan Engine: A Case of CFM56-7B
- Separation Control by Slot Jet in a Critically Loaded Compressor Cascade
- An Impingement Cooling Using Swirling Jets Induced by Helical Rod Swirl Generators
- Studies on Stepped Air Ejector Diffusers incorporating Heat Transfer Effects
- Assessment of Analytical Predictions for Radial Growth of Rotating Labyrinth Seals
- Ground Simulation of High Altitude Test of Turbo-Refrigeration Cycle
- Investigations on the Film Cooling of Counter-Inclined Film-Hole Row Structures for Turbine Vane Leading Edge
