Film Cooling on a Gas Turbine Rotor Blade

Takeishi, Kenichiro; Aoki, S.; Satō, Tomohiko; Tsukagoshi, Keizo

doi:10.1115/1.2928036

Cited by 114 publications

(27 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Dring et al (1980) reported film cooling effectiveness in a rotating configuration in a low speed tunnel. Takeishi et al (1992) also studied film cooling effectiveness on a stator-rotor stage, simulating a heavy duty gas turbine. Measured effectiveness values on the suction side for the rotating turbine blade seemed to match the data from the stationary cascade; whereas the rotating effectiveness on the pressure side seemed to be significantly lower than the nonrotating case.…”

Section: Film Cooling Under Rotating Conditionsmentioning

confidence: 99%

Turbine Blade Film Cooling Using PSP Technique

Han¹,

Rallabandi²

2010

Frontiers in Heat and Mass Transfer

192

View full text Add to dashboard Cite

Film cooling is widely used to protect modern gas turbine blades and vanes from the ever increasing inlet temperatures. Film cooling involves a very complex turbulent flow-field, the characterization of which is necessary for reliable and economical design. Several experimental studies have focused on gas turbine blade, vane and end-wall film cooling over the past few decades. Measurements of heat transfer coefficients, film cooling effectiveness values and heat flux ratios using several different experimental methods have been reported. The emphasis of this current review is on the Pressure Sensitive Paint (PSP) mass transfer analogy to determine the film cooling effectiveness. The theoretical basis of the method is presented in detail. Important results in the open literature obtained using the PSP method are presented, discussing parametric effects of blowing ratio, momentum ratio, density ratio, hole shape, surface geometry, free-stream turbulence on flat plates, turbine blades, vanes and end-walls. The PSP method provides very high resolution contours of film cooling effectiveness, without being subject to the conduction error in high thermal gradient regions near the hole.

show abstract

Section: Film Cooling Under Rotating Conditionsmentioning

confidence: 99%

Turbine Blade Film Cooling Using PSP Technique

Han¹,

Rallabandi²

2010

Frontiers in Heat and Mass Transfer

192

View full text Add to dashboard Cite

show abstract

“…The results show that the calculated value is lower in most cases, but that the deviations are acceptable. Takeishi et al [3] studied the superposition effect of film cooling effectiveness for multi-row holes on a turbine blade. The results show the Sellers' method is suitable for the suction side of the vane, and only suitable for a rotating working blade far downstream of the film cooling holes.…”

Section: Introductionmentioning

confidence: 99%

Investigation of film cooling and superposition method for double row dustpan‐shaped holes

Zhu

Tao

2008

Heat Trans. Asian Res.

View full text Add to dashboard Cite

Film cooling effectiveness for injection from single row and double row dustpan-shaped holes was studied experimentally. The difference in cooling performance between single row and double row holes are described. The results show that the optimal blowing ratio of injection from double row holes is higher than that of injection from a single row hole. In the case of higher blowing ratios, the traditional superposition calculation method underpredicts the film cooling effectiveness of the double row injection based on that of the single row hole injection. The modified superposition calculation method is given in this paper.

show abstract

“…At the reference speed of 2,550 rpm, the rotor platform has the maximum cooling effectiveness and coolant coverage. Takeishi [3] measured the film cooling effectiveness on a rotor blade using the heat-mass transfer method. On the suction side, the film cooling effectiveness fits well with that in stationary cascade, but is lower than that in stationary on the pressure side.…”

Section: Introductionmentioning

confidence: 99%

Film cooling performance in a low speed 1.5-stage turbine: effects of mainstream Reynolds number and turbulence

Zhu

Wang

et al. 2014

Heat Mass Transfer

View full text Add to dashboard Cite

The effects of mainstream Reynolds number and turbulence to film cooling performance were investigated experimentally and computationally under rotating conditions in a 1.5-stage turbine. The rotor of the turbine included 18 blades with chord of 124.3 mm and height of 99 mm. A film hole was set in the middle span of the rotor blade surface with injection angles of 28°on the pressure side and 36°on the suction side respectively. The Reynolds number based on the mainstream velocity of the turbine outlet and the chord length of the rotor blade varied from 1.9 9 10 5 to 2.1 9 10 5 . Measurements were made at three different rotation speeds of 702, 737 and 800 rpm to keep the rotating number consistent at 0.0280 while the blowing ratio varied from 0.5 to 2.0. Air and CO 2 worked as coolant to achieve the density ratio of 1.03 and 1.57, respectively. Computational investigation was performed using the hexahedral structured grids and k-e turbulence model. Results showed that the film coverage and cooling effectiveness are enlarged while the film deflection is weakened as the mainstream Reynolds number increases. Furthermore, the mainstream turbulence plays a negative role in the film coverage and cooling effectiveness at lower blowing ratio on both the pressure side and suction side while it promotes the film reattachment at higher blowing ratio on the suction side.

show abstract

Film Cooling on a Gas Turbine Rotor Blade

Cited by 114 publications

References 0 publications

Turbine Blade Film Cooling Using PSP Technique

Turbine Blade Film Cooling Using PSP Technique

Investigation of film cooling and superposition method for double row dustpan‐shaped holes

Film cooling performance in a low speed 1.5-stage turbine: effects of mainstream Reynolds number and turbulence

Contact Info

Product

Resources

About