journal article·2019-07-01Open access

Performance analysis of different influencing factors on film cooling and the internal relations with vortex structures

Jianlong Chang, Yang Du, Shizhen Zheng, Xinlei Duan, Yanchen Liu

AIP Advances· Volume 9· Issue 7

Abstract

Film cooling is a cooling technique in which a protective layer is generated by the coolant along the wall to shield the wall surface against high temperature flow. When the fluids of the coolant and high-temperature gas are of different qualities, it is often accompanied by the mass and energy transfer. During the film cooling process, the lower-temperature gas is transported to the surface through the tangential gap on the wall which requires thermal protection. And then the film is formed along the direction of the high-temperature flow, causing the solid wall isolated from the high temperature gas, thereby it can prevent the wall surface from being touched and damaged by hot stream. Since the film cooling sets high standards for hole shape, the structure of injection, the length of the coolant supply tube, the angle of incidence, the blowing ratio, the thickness of the boundary layer, ribs and the Reynolds number, etc., the analysis and optimization of these factors have been particular significance on improving cooling efficiency. This paper introduces the dominant factors which influence film cooling effectiveness, besides, analyzes the methods to achieve the best cooling results. The impact of the vortex structures on enhancing film cooling performance is explored. Moreover, a new train of thought is proposed to improve the cooling efficiency under the joint action of the vortex generator and the synthetic jet.
Source: crossref · Quality: baseline

Research context

OpenAlex topics: Heat Transfer Mechanisms · Turbomachinery Performance and Optimization · Fluid Dynamics and Turbulent Flows

SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.

Affiliations

College of Mechatronic Engineering, North University of China 1 , Taiyuan 030051, China

Institute of Military-civilian Integration and Innovation, North University of China 2 , Taiyuan 030051, China

Funding

Aerospace Light Alloy Components Adavanced Manufactureing Team In North Univesity of China · Shanxi Youth Natural Science Foudation of Shanxi China · National Natural Science Foundation of China

References (71)

Show source-provided references
1. Conceptual design and cooling blade development of 1700 °C class high-temperature gas turbine
2. 1982
3. Experimental investigations on the effects of inclination angle and blowing ratio on the flat-plate film cooling enhancement using the vortex generator downstream10.1016/j.applthermaleng.2017.03.089 ↗
4. Liquid jet in a subsonic gaseous crossflow: Recent progress and remaining challenges10.1016/j.pecs.2016.08.003 ↗
5. A comparison of classical and pulsating jets in crossflow at various Strouhal numbers10.1155/2017/5279790 ↗
6. CRVP in a reacting jet in crossflow
7. Near-hole thermal field measurements for round compound angle film cooling holes fed by cross-flow
8. Experimental investigation of the influence of freestream turbulence on an anti-vortex film cooling hole10.1016/j.expthermflusci.2016.10.025 ↗
9. Effects of hole geometry and density on three-dimensional film cooling10.1016/0017-9310(74)90007-6 ↗
10. Film-cooling holes with expanded exits: Near-hole heat transfer coefficients10.1016/s0142-727x(99)00076-4 ↗
11. Experimental investigation of film cooling effectiveness for a new shaped hole at the leading edge
12. Experimental and numerical studies on leading edge film cooling performance: Effects of hole exit shape and freestream turbulence
13. Effect of a crossflow at the entrance to a film-cooling hole10.1115/1.2819277 ↗
14. Experimental study of showerhead cooling on a cylinder comparing several configurations using cylindrical and shaped holes10.1115/1.555420 ↗
15. Influence of shaped injection holes on turbine blade leading edge film cooling10.1016/j.ijheatmasstransfer.2003.07.008 ↗
16. Turbine blade showerhead film cooling: Influence of hole angle and shaping10.1016/j.ijheatfluidflow.2007.01.002 ↗
17. Influence of film-hole shape and angle on showerhead film cooling using PSP technique10.1115/1.3082413 ↗
18. Numerical evaluation of the performance of the sister–shaped single–hole schemes on turbine blade leading edge film cooling
19. Effects of side hole position and blowing ratio on sister hole film cooling performance in a flat plate10.1016/j.applthermaleng.2015.09.118 ↗
20. Double-jet ejection of cooling air for improved film-cooling
21. Experimental and numerical studies on leading edge film cooling performance: Effects of hole exit shape and freestream turbulence
22. On the nature of jets entering a turbulent flow: Part A—Jet–mainstream interaction10.1115/1.3446601 ↗
23. Measurements in film cooling flows: Hole L/D and turbulence intensity effects10.1115/1.2841791 ↗
24. Numerical modelling of film cooling with and without mist injection10.1007/s00231-008-0465-6 ↗
25. Stagnation region gas film cooling for turbine blade leading edge applications
26. Stagnation film cooling and heat transfer, including its effect within the hole pattern10.1115/1.3262169 ↗
27. Enhancement of film cooling performance at the leading edge of turbine blade
28. Leading edge film cooling heat transfer through one row of inclined film slots and holes including mainstream turbulence effects10.1115/1.2910907 ↗
29. Flow visualization study of passive flow control features on a film-cooled turbine blade leading edge
30. The effect of internal cross-flow on the adiabatic effectiveness of compound angle film cooling holes
31. A detailed analysis of film cooling physics: Part II—Compound-angle injection with cylindrical holes10.1115/1.555434 ↗
32. Comparison the cooling performance of cylindrical and fan-shaped cooling holes with special emphasis on the effect of internal coolant cross-flow
33. A numerical study on the 2D film cooling of a flat surface10.1080/10407782.2014.949131 ↗
34. Film cooling effectiveness and heat transfer on the trailing edge cutback of gas turbine airfoils with various internal cooling designs10.1115/1.2103094 ↗
35. Turbulent heat transfer and large coherent structures in trailing-edge cutback film cooling10.1007/s10494-011-9379-3 ↗
36. The effects of inlet Reynolds number, exit Mach number and incidence angle on leading edge film cooling effectiveness of a turbine blade in a linear transonic cascade
37. Film cooling with large density differences between the mainstream and the secondary fluid measured by the heat-mass transfer analogy10.1115/1.3450752 ↗
38. The influence of foreign gas injection and slot geometry on film cooling effectiveness10.1016/0017-9310(69)90156-2 ↗
39. The use of foreign gas to simulate the effects of density ratios in film cooling10.1115/1.3262237 ↗
40. Film-cooling effectiveness downstream of a single row of holes with variable density ratio10.1115/1.2927894 ↗
41. Full-coverage discrete hole film cooling: Investigation of the effect of variable density ratio10.1115/1.2906860 ↗
42. Effect of coolant density on leading edge showerhead film cooling using the pressure sensitive paint measurement technique10.1115/1.4025225 ↗
43. Scaling of performance for varying density ratio coolants on an airfoil with strong curvature and pressure gradient effects
44. A numerical and experimental investigation of the slot film-cooling jet with various angles10.1115/1.1929821 ↗
45. Film cooling characteristics of a single round hole at various streamwise angles in a crossflow: Part I effectiveness10.1016/s0017-9310(02)00274-0 ↗
46. Two-dimensional numerical investigation of film cooling by a cool jet injected at various angles for different blowing ratios10.1243/09544062jmes905 ↗
47. Experimental investigation of film cooling with ejection from a row of holes for the application to gas turbine blades10.1115/1.3445904 ↗
48. Effects of freestream Mach number, Reynolds number, and boundary layer thickness on film cooling effectiveness of shaped holes
49. Reynolds number effect on leading edge film effectiveness and heat transfer coefficient10.1016/0017-9310(93)90052-8 ↗
50. Film cooling performance and flow characteristics of internal cooling channels with continuous/truncated ribs10.1016/j.ijheatmasstransfer.2016.09.065 ↗
51. Conjugated heat transfer analysis of a film cooling passage with different rib configurations10.1108/hff-04-2014-0110 ↗
52. Direct numerical simulation of film cooling with a fan-shaped hole under low Reynolds number conditions10.1016/j.ijheatmasstransfer.2018.03.011 ↗
53. Leading edge film cooling heat transfer with high free stream turbulence using a transient liquid crystal image method10.1016/s0142-727x(01)00121-7 ↗
54. Leading-edge film-cooling physics: Part I—Adiabatic effectiveness
55. The flow field structures of in-lined double jet-in-cross flow at low velocity ratio10.9766/kimst.2015.18.4.415 ↗
56. Experimental and CFD studies of NGV endwall cooling
57. Effect of upstream wake with vortex on turbine blade platform film cooling with simulated stator-rotor purge flow
58. Turbine nozzle endwall film cooling study using pressure-sensitive paint10.1115/1.1400113 ↗
59. Effect of endwall film cooling upstream of an airfoil/endwall junction to suppress the formation of horseshoe vortex in a symmetric airfoil
60. A novel antivortex turbine film-cooling hole concept10.1115/1.2777194 ↗
61. Improved film cooling effectiveness by placing a vortex generator downstream of each hole
62. Improvement of flat-plate film cooling performance by double flow control devices: Part I—Investigations on capability of a base-type device
63. Effect of vortex generators on film cooling effectiveness10.1115/1.4035275 ↗
64. Inclined jet in crossflow interacting with a vortex generator10.2514/1.49742 ↗
65. Large eddy simulations of film-cooling flows with a micro-ramp vortex generator10.1115/1.4006329 ↗
66. Anti-kidney pair of vortices in shaped holes and their influence on film cooling effectiveness
67. A numerical study on improving large angle film cooling performance through the use of sister holes10.1080/10407780902821532 ↗
68. Increasing adiabatic film-cooling effectiveness by using an upstream ramp
69. Experimental study on effects of internal ribs and rear bumps on film cooling effectiveness10.1115/1.4007546 ↗
70. Experimental study of the effects of an oscillating approach flow on overall cooling performance of a simulated turbine blade leading edge
71. Interaction between a vortex generator and a synthetic jet in a crossflow10.1063/1.4932359 ↗