Heat Transfer Performance of a Transonic Turbine Blade Passage in presence of Leakage Flow though Upstream Slot and Mateface Gap with Endwall Contouring

[+] Author and Article Information
Arnab Roy

Department of Mechanical Engineering, Virginia Tech, Blacksburg, VA 24061, USA; National Energy Technology Laboratory, Morgantown, WV 26507

Sakshi Jain

Department of Mechanical Engineering, Virginia Tech, Blacksburg, VA 24061, USA; Cummins Columbus Engine Plant, 500 Central Ave, Columbus IN-47201

Srinath V. Ekkad

Department of Mechanical Engineering, Virginia Tech, 301 Burruss Hall, 800 Drillfield Drive, Blacksburg, VA 24061

Wing Ng

Department of Mechanical Engineering, Virginia Tech, 425 Goodwin Hall (0238), 635 Prices Fork Road, Blacksburg, VA 24061

Andrew Lohaus

Siemens Energy, Inc., 4400 Alafaya Trail, Orlando, FL 32789

Michael Crawford

Siemens Energy, Inc., 11842 Corporate Boulevard, Orlando, FL 32817, USA

Santosh Abraham

Siemens Energy, Inc., 5101 Westinghouse Boulevard, Charlotte, NC 28273-9640

1Corresponding author.

ASME doi:10.1115/1.4037909 History: Received August 02, 2017; Revised August 28, 2017


Comparison of heat transfer performance of a non-axisymmetric contoured endwall to a planar baseline endwall in presence of leakage flow through stator-rotor rim seal interface and mateface gap is reported in this paper. Heat transfer experiments were performed on a high turning turbine airfoil passage at Virginia Tech's transonic blow down cascade facility under design conditions for two leakage flow configurations - 1) mateface blowing only, 2) simultaneous coolant injection from the upstream slot and mateface gap. Coolant to mainstream mass flow ratios (MFR) were 0.35% for mateface blowing only, whereas for combination blowing, a 1.0% MFR was chosen from upstream slot and 0.35% MFR from mateface. A common source of coolant supply to the upstream slot and mateface plenum made sure the coolant temperatures were identical at both upstream slot and mateface gap at the injection location. The contoured endwall geometry was generated to minimize secondary aerodynamic losses. Transient Infrared thermography technique was used to measure endwall surface temperature and a linear regression method was developed for simultaneous calculation of heat transfer coefficient (HTC) and adiabatic cooling effectiveness (ETA), assuming a 1D semi-infinite transient conduction. Results indicate reduction in local hot spot regions near suction side as well as area averaged HTC using the contoured endwall compared to baseline endwall for all coolant blowing cases. Contoured geometry also shows better coolant coverage further along the passage. Detailed interpretation of the heat transfer results along with near endwall flow physics has also been discussed.

Siemens AG
Your Session has timed out. Please sign back in to continue.






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