Film Cooling Experimental Study on Sinusoidal Corrugated Liner for Afterburner
-
Shan Yong
,
Tan Xiao Ming
Abstract
The need of improved cooling effectiveness for hot components in jet engines has led to new designs of afterburner liners. In the present paper, experiments were performed to reveal the cooling characteristics and flow loss of various sinusoidal corrugated liners for an advanced afterburner. It is found that there are alternate high temperature and low temperature zones corresponding to the wave crests and troughs of the corrugated liner, respectively. Compared to the flat liner, the corrugated liner increases cooling effectiveness by 10 % at the blowing ratio of 0.5, by 4.5 % at the blowing ratio of 3.2. However, the difference in discharge coefficients for these two kinds of liners is only 4.3 %. The increased opening ratio of film holes from 1.42 % to 3.72 % for corrugated liners is able to improve the cooling effectiveness by 9.8 %. However, the discharge coefficient is decreased by 34.1 %. The augment of amplitude of liners can enhance the ram effect of cooling air, which has an advantage to increase the local blowing ratio, and to form good cooling film at the windward of wave troughs. The flow loss is bigger while the cooling effectiveness is enhanced due to the change of amplitude of the liner.
Funding source: National Natural Science Foundation of China
Award Identifier / Grant number: NO. 51306088
Funding statement: This work was supported by the National Natural Science Foundation of China; [NO. 51306088].
Acknowledgment
The authors gratefully acknowledge the financial support for this project from National Natural Science Foundation of China, NO. 51306088.
Nomenclature
- A
Area of flow, mm2
Discharge coefficient
- D
Diameter of film holes, mm
- H
Amplitude, mm
- L
Wave length, mm
- M
Blowing ratio
- P
Pressure, Pa
- p
Interval distance along span wise, mm
Flow rate, kg/s
- s
Interval distance along stream wise, mm
- T
Temperature, K
Velocity of flow, m/s
Density of flow, kg/m3
Cooling effectiveness
Opening ratio of film holes
- Subscript
- c
Secondary flow (coolant flow)
- ∞
Primary flow (hot flow)
- w
wall
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© 2020 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Combined Flow Control of Positively Bowed Blade and Vortex Generator Jet on a Compressor Cascade
- Design and Numerical Investigations on a Dual-Duct Variable Geometry RBCC Inlet
- Film Cooling Experimental Study on Sinusoidal Corrugated Liner for Afterburner
- Fatigue Life Prediction of Fan Blade Using Nominal Stress Method and Cumulative Fatigue Damage Theory
- Investigation of Flow Distortion Generated Forced Response of a Radial Turbine with Vaneless Volute
- A Comparison of the Wake Effects Generated by the Biased Triangle Bar and Traditional Cylinder Bar to the Boundary Layer on Suction Surface of LPT Blade
- Exergetic, Exergoeconomic, Sustainability and Environmental Damage Cost Analyses of J85 Turbojet Engine with Afterburner
- Large Eddy Simulation of Secondary Flows in an Ultra-High Lift Low Pressure Turbine Cascade at Various Inlet Incidences
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Combined Flow Control of Positively Bowed Blade and Vortex Generator Jet on a Compressor Cascade
- Design and Numerical Investigations on a Dual-Duct Variable Geometry RBCC Inlet
- Film Cooling Experimental Study on Sinusoidal Corrugated Liner for Afterburner
- Fatigue Life Prediction of Fan Blade Using Nominal Stress Method and Cumulative Fatigue Damage Theory
- Investigation of Flow Distortion Generated Forced Response of a Radial Turbine with Vaneless Volute
- A Comparison of the Wake Effects Generated by the Biased Triangle Bar and Traditional Cylinder Bar to the Boundary Layer on Suction Surface of LPT Blade
- Exergetic, Exergoeconomic, Sustainability and Environmental Damage Cost Analyses of J85 Turbojet Engine with Afterburner
- Large Eddy Simulation of Secondary Flows in an Ultra-High Lift Low Pressure Turbine Cascade at Various Inlet Incidences
