0
TECHNICAL PAPERS

# Local Heat/Mass Transfer Characteristics on a Rotating Blade With Flat Tip in a Low-Speed Annular Cascade—Part II: Tip and Shroud

[+] Author and Article Information
Dong-Ho Rhee, Hyung Hee Cho

Department of Mechanical Engineering, Yonsei University, Seoul 120-749, Korea

J. Turbomach 128(1), 110-119 (Feb 01, 2005) (10 pages) doi:10.1115/1.2098767 History: Received October 01, 2004; Revised February 01, 2005

## Abstract

The local heat/mass transfer characteristics on the tip and shroud were investigated using a low speed rotating turbine annular cascade. Time-averaged mass transfer coefficients on the tip and shroud were measured using a naphthalene sublimation technique. A low speed wind tunnel with a single stage turbine annular cascade was used. The turbine stage is composed of sixteen guide plates and blades. The chord length of blade is 150 mm and the mean tip clearance is about 2.5% of the blade chord. The tested Reynolds number based on inlet flow velocity and blade chord is $1.5×105$ and the rotational speed of the blade is 255.8 rpm at design condition. The results were compared with the results for a stationary blade and the effects of incidence angle of incoming flow were examined for incidence angles ranging from $−15$ to $+7deg$. The off-design test conditions are obtained by changing the rotational speed with a fixed incoming flow velocity. Flow reattachment on the tip near the pressure side edge dominates the heat transfer on the tip surface. Consequently, the heat/mass transfer coefficients on the blade tip are about 1.7 times as high as those on the blade surface and the shroud. However, the heat transfer on the tip is about 10% lower than that for the stationary case due to reduced leakage flow with the relative motion. The peak regions due to the flow reattachment are reduced and shifted toward the trailing edge and additional peaks are formed near the leading edge region with decreasing incidence angles. But, quite uniform and high values are observed on the tip with positive incidence angles. The time-averaged heat/mass transfer on the shroud surface has a level similar to that of the stationary cases.

<>

## Figures

Figure 1

Schematics of experimental apparatus and test section. (a) Experimental apparatus; (b) test section

Figure 2

Distribution of static pressure coefficient on the shroud surface for stationary blade

Figure 3

Contour plots of ShC on the tip and shroud surface at ReC=1.5×105. (a) On the tip; (b) on the shroud; (c) on the blade surface (28).

Figure 4

Pitchwise distributions of ShC on the tip and shroud for stationary blade at ReC=1.5×105. (a) i=0deg(it=−4.1deg); (b) i=+2.9deg(it=0deg).

Figure 5

Contour plots of ShC on the flat tip of blade for rotating blade. (a) i=0 deg (it=4.1 deg); (b) i=2.9 deg (it=0 deg).

Figure 6

Local distributions of Sh on the tip for the rotating blade at design condition (i=0deg,it=−4.1deg)

Figure 7

Pitchwise averaged ShC on the tip for the rotating blade at ReC,in=1.5×105 and N=255.8rpm

Figure 8

Streamwise distribution of pitchwise-averaged ShC on the shroud for the rotating blade at design condition (i=0deg)

Figure 9

Contour plots of ShC on the flat tip of blade with positive incidence angles at ReC,ex=1.8×105. (a) i=+5deg(it=+2.8deg); (b) i=+7deg(it=+5.5deg).

Figure 10

Contour plots of ShC on the flat tip of blade with negative incidence angles at ReC,ex=1.8×105. (a) i=−5deg(it=−11.4deg); (b) i=−10deg(it=−19.0deg); (c) i=−15deg(it=−26.9deg).

Figure 11

Pitchwise averaged ShC on the tip of blade with various incidence angles at ReC,ex=1.8×105

Figure 12

Area averaged ShC on the tip of blade with various incidence angles at ReC,ex=1.8×105

## Related

Some tools below are only available to our subscribers or users with an online account.

### Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related Proceedings Articles
Related eBook Content
Topic Collections