Author: Irene CresciPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
High Pressure Nozzle Guide Vane Cooling System Flow Characteristics
Author: Irene CresciFilm-cooling of a Turbine Nozzle Guide Vane Endwall
Author: Nozzle Guide Vane Cooling
Author: G. A. HallsDischarge Coefficients of Nozzle Guide Vane Film Cooling Holes
Author: Dave RowburyNozzle Guide Vane Sweeping Jet Impingement Cooling
Author: Lucas AgricolaPublisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 91
Book Description
Sweeping jet impingement cooling was investigated in a gas turbine nozzle guide vane design with an engine-relevant Biot number of 0.3. Sweeping jets were created with fluidic oscillators and were compared to steady jets produced by cylindrical orifices (with length-to-diameter ratio of 1), the current state-of-the-art in engine designs. Experiments were performed in a low speed linear cascade with additively manufactured test pieces. The impingement cooling geometries were examined at multiple coolant mass flow rates and freestream turbulence intensities. The overall effectiveness of each cooling geometry was calculated using thermocouple measurements of the freestream and coolant temperatures, and infrared thermography measurements of the vane external surface temperature. A computational thermal inertia technique was used to determine the internal Nusselt numbers. The heat transfer provided by steady impinging jets produced a higher overall effectiveness and Nusselt number in the leading edge geometry. The sweeping jets provided more uniform heat transfer, reducing thermal gradients near the stagnation point. Pressure drop across each jet geometry was measured at a range of applicable mass flow rates. Fluidic oscillators were shown to create similar pressure drop to circular orifice holes when additive manufacturing abilities were fully incorporated in the nozzle guide vane internal cooling designs.
The Use of Intersecting Film Cooling Passages for Nozzle Guide Vane Cooling
Author: Scott Raymond NowlinPublisher:
ISBN:
Category : Cooling systems
Languages : en
Pages : 0
Book Description
"An experimental and computational investigation has been conducted on the impact of intersecting film cooling passages on turbine vane sstagnation region cooling performance in terms of the passage loss (discharge) coefficient, passage surface heat transfer coefficient, and external (mainstream) surface film coolant distributions. Passage intersections are created within component walls by orienting and inclining holes such that passages either wholly or partially intersect, creating so-called lattice of matrix intersections respectively. Non-rotating turbine vanes are the study subject through conclusions regarding improved convective cooling performance and observed film behaviour likely extend to rotating blades."--Excerpted from Abstract, page iii.
An Investigation of the Effects of Nozzle Guide Vane Trailing Edge Cooling on Rotor Heat Transfer in a Transonic Turbine Stage
Author: Aaron James GleixnerPublisher:
ISBN:
Category :
Languages : en
Pages : 330
Book Description
Dendritic Cooling for Nozzle Guide Vanes
Author: James John Robert BatstonePublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
The Influence of Film-cooling on the Aerodynamic Performance of a Turbine Nozzle Guide Vane
Author: C. OsnaghiPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Presented at the International Gas Turbine & Aeroegine Congress & Exhibition, Orlando, FL, Jun 2-Jun 5, 1997.
Author: Rohit Anand Oke