Follow
Harika S. Kahveci
Harika S. Kahveci
Verified email at metu.edu.tr
Title
Cited by
Cited by
Year
Effect of cavity depth on thermal performance of a cooled blade tip under rotation
S Sakaoglu, HS Kahveci
International Journal of Heat and Mass Transfer 143, 118561, 2019
252019
Heat Transfer for the Film-Cooled Vane of a 1-1/2 Stage High-Pressure Transonic Turbine—Part I: Experimental Configuration and Data Review With Inlet Temperature Profile Effects
HS Kahveci, CW Haldeman, RM Mathison, MG Dunn
Journal of turbomachinery 135 (2), 2013
182013
Effect of Turbine Blade Tip Cooling Configuration on Tip Leakage Flow and Heat Transfer
S Sakaoglu, HS Kahveci
Journal of Turbomachinery 142 (2), 2020
162020
An optimization study for rotorcraft avionics bay cooling
A Akin, HS Kahveci
Aerospace Science and Technology 90, 1-11, 2019
152019
Effect of turbulence modeling for the prediction of flow and heat transfer in rotorcraft avionics bay
A Akin, HS Kahveci
Aerospace Science and Technology 95, 105453, 2019
92019
Heat Transfer for the Film-Cooled Vane of a 1-1/2 Stage High-Pressure Transonic Turbine—Part II: Effect of Cooling Variation on the Vane Airfoil and Inner End Wall
HS Kahveci, CW Haldeman, RM Mathison, MG Dunn
Journal of turbomachinery 135 (2), 2013
92013
Implementation of a Stereoscopic PIV in Rotating Machinery Including Helicopter Rotor Flows
HS Kahveci
Pennsylvania State University, 2004
72004
Effect of Turbine Blade Tip Cooling Configuration on Tip Leakage Flow and Heat Transfer
S Sakaoglu, HS Kahveci
Turbo Expo: Power for Land, Sea, and Air 58646, V05AT12A001, 2019
62019
Validation of MISES 2-D Boundary Layer Code for High Pressure Turbine Aerodynamic Design
PL Andrew, HS Kahveci
Turbo Expo: Power for Land, Sea, and Air 47950, 879-893, 2007
62007
Airfoil and method for manufacturing an airfoil
MA Jones, AE Smith, HS Kahveci
US Patent App. 13/600,717, 2014
52014
Heat Transfer for the Film-Cooled Vane of a 1-1/2 Stage High-Pressure Transonic Turbine: Part I—Experimental Configuration and Data Review With Inlet Temperature Profile Effects
HS Kahveci, CW Haldeman, RM Mathison, MG Dunn
Turbo Expo: Power for Land, Sea, and Air 54655, 1719-1733, 2011
52011
Heat Transfer for the Film-Cooled Vane of a 1-1/2 Stage High-Pressure Transonic Turbine: Part II—Effect of Cooling Variation on the Vane Airfoil and Inner Endwall
HS Kahveci, CW Haldeman, RM Mathison, MG Dunn
Turbo Expo: Power for Land, Sea, and Air 54655, 1735-1744, 2011
52011
Investigation of a rotor blade with tip cooling subject to a nonuniform temperature profile
HS Kahveci
Journal of Turbomachinery 143 (7), 2021
42021
The Influence of Film Cooling and Inlet Temperature Profile on Heat Transfer for the Vane Row of a 1-1/2 Stage Transonic High-Pressure Turbine
HS Kahveci
The Ohio State University, 2010
42010
Flow around helicopter blade tip sections using 2D particle image velocimeter-part I
HS Kahveci, C Camci
11th International Symposium on Transport Phenomena and Dynamics of Rotating …, 2006
42006
Validation of MISES Two-Dimensional Boundary Layer Code for High-Pressure Turbine Aerodynamic Design
PL Andrew, HS Kahveci
Journal of turbomachinery 131 (3), 2009
32009
Flow Around Helicopter Blade Tip Sections Using a (3D) Stereoscopic Particle Image Velocimeter—Part II
HS Kahveci, C Camci
11th International Symposium on Transport Phenomena and Dynamics of Rotating …, 2006
32006
Uncertainty Analysis of Heat Transfer Predictions Using Statistically Modeled Data From a Cooled 1-1/2 Stage High-Pressure Transonic Turbine
HS Kahveci, KR Kirtley
Journal of Turbomachinery 136 (6), 2014
22014
Use of Artificial Neural Network in Rotorcraft Cooling System.
A AKIN, HS Kahveci
Journal of Aeronautics & Space Technologies/Havacilik ve Uzay Teknolojileri …, 2019
12019
Comparison of Temperature Profile and Heat Transfer Predictions With Statistically-Modeled Data From a Cooled 1-1/2 Stage High-Pressure Transonic Turbine
HS Kahveci, KR Kirtley
Turbo Expo: Power for Land, Sea, and Air 55164, V03CT14A001, 2013
12013
The system can't perform the operation now. Try again later.
Articles 1–20