0
Research Papers

Measurements of Hub Flow Interaction on Film Cooled Nozzle Guide Vane in Transonic Annular Cascade

[+] Author and Article Information
Lamyaa A. El-Gabry

Mechanical Engineering Department,
The American University in Cairo,
New Cairo 11835, Egypt;
Research Fellow
Department of Energy Technology,
Royal Institute of Technology (KTH),
Stockholm 10044, Sweden

Ranjan Saha, Jens Fridh, Torsten Fransson

Department of Energy Technology,
Royal Institute of Technology (KTH),
Stockholm 10044, Sweden

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 5, 2014; final manuscript received November 14, 2014; published online January 28, 2015. Editor: Kenneth C. Hall.

J. Turbomach 137(8), 081004 (Aug 01, 2015) (9 pages) Paper No: TURBO-14-1287; doi: 10.1115/1.4029242 History: Received November 05, 2014; Revised November 14, 2014; Online January 28, 2015

An experimental study has been performed in a transonic annular sector cascade of nozzle guide vanes (NGVs) to investigate the aerodynamic performance and the interaction between hub film cooling and mainstream flow. The focus of the study is on the endwalls, specifically the interaction between the hub film cooling and the mainstream. Carbon dioxide (CO2) has been supplied to the coolant holes to serve as tracer gas. Measurements of CO2 concentration downstream of the vane trailing edge (TE) can be used to visualize the mixing of the coolant flow with the mainstream. Flow field measurements are performed in the downstream plane with a five-hole probe to characterize the aerodynamics in the vane. Results are presented for the fully cooled and partially cooled vane (only hub cooling) configurations. Data presented at the downstream plane include concentration contour, axial vorticity, velocity vectors, and yaw and pitch angles. From these investigations, secondary flow structures such as the horseshoe vortex, passage vortex, can be identified and show the cooling flow significantly impacts the secondary flow and downstream flow field. The results suggest that there is a region on the pressure side (PS) of the vane TE where the coolant concentrations are very low suggesting that the cooling air introduced at the platform upstream of the leading edge (LE) does not reach the PS endwall, potentially creating a local hotspot.

Copyright © 2015 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Fig. 1

Sketch annular cascade upstream of test section [23]

Grahic Jump Location
Fig. 2

(a) Cut-through of cascade at midspan [23]. (b) Cooling holes on test NGV [23].

Grahic Jump Location
Fig. 3

Distribution of blowing ratio for the vane cooling holes at mass flux ratio 7.75%

Grahic Jump Location
Fig. 4

Airfoil Mach number distribution at 25%, 50%, and 75% span

Grahic Jump Location
Fig. 5

Endwall Mach number distribution from CFD simulation

Grahic Jump Location
Fig. 6

Normalized inlet total pressure

Grahic Jump Location
Fig. 7

Total pressure distribution at 20% span

Grahic Jump Location
Fig. 8

Exit flow angle distribution for fully air cooled vane

Grahic Jump Location
Fig. 9

Pitch angle distribution for fully air cooled vane

Grahic Jump Location
Fig. 10

Flow vector for fully air-cooled vane

Grahic Jump Location
Fig. 11

Near hub vorticity for fully air-cooled vane

Grahic Jump Location
Fig. 12

Comparison of velocity vector for fully air cooled (black) and hub air cooled (red)

Grahic Jump Location
Fig. 13

Vorticity distribution for partially cooled with air

Grahic Jump Location
Fig. 14

Velocity vectors for air cooled (black) and CO2 cooled (red)

Grahic Jump Location
Fig. 15

Vorticity distribution for CO2 cooled

Grahic Jump Location
Fig. 16

CO2 concentration measurement repeatability

Grahic Jump Location
Fig. 17

CO2 concentration and flow vectors for CO2 cooled vane matching BR (run 5)

Grahic Jump Location
Fig. 18

CO2 concentration and flow vectors for CO2 cooled vane matching MR (run 6)

Grahic Jump Location
Fig. 19

CO2 concentration and vorticity (thin line) for CO2 cooled vane matching BR (run 5)

Grahic Jump Location
Fig. 20

CO2 concentration and vorticity (thin line) for CO2 cooled matching MR (run 6)

Grahic Jump Location
Fig. 21

Percent difference of CO2 between matched blowing ratio and momentum ratio

Grahic Jump Location
Fig. 22

Pitch and yaw angle definition [22]

Tables

Errata

Discussions

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 eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In