Endwall film cooling using curtain cooling and discharge from upstream combustor walls is numerically examined in this study. The curtain cooling for the first-stage turbine vane endwall is accomplished by two rows of cylindrical film-cooling holes through the endwall at 20% of the axial chord length upstream of the vane leading edge. Flat plates with square trailing edges positioned upstream of the vane row model the combustor walls. Each is aligned with the leading edge of every second vane. A continuous slot is placed at the trailing edge of the combustor wall model through which combustor wall coolant is discharged. Analyses of cases with various slot geometries document the effects on bonus cooling of the downstream endwall. Various endwall blowing ratios and slot discharge flow ratios are applied. A comparison with a zero-slot-discharge datum case shows how the combustor wall discharge affects the flow fields near the passage endwalls, being detrimental to endwall curtain cooling in some cases. Discharge effects on bonus cooling are visible mainly near the vane leading edge and along the pressure side of the endwall passage. The effects of the discharge flow on endwall curtain cooling patterns are related to endwall film cooling performance.
|Original language||English (US)|
|Title of host publication||53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|State||Published - 2017|
|Event||53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017 - Atlanta, Georgia|
Duration: Jul 10 2017 → Jul 12 2017
|Name||53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017|
|Other||53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017|
|Period||7/10/17 → 7/12/17|
Bibliographical noteFunding Information:
financial support from the Key Project of National Natural
Science Foundation of China (Grant No. 51336007) and the China Scholarship Council (CSC).