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.
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.
The Influence of Film Cooling on Turbine Aerodynamic Performance
Author: Chia Hui LimEffect of Cooling-hole Geometry on Aerodynamic Performance of a Film-cooled Turbine Vane Tested with Cold Air in a Two-dimensional Cascade
Author: John F. KlineEffect of Cooling-hole Geometry on Aerodynamic Performance of a Film-cooled Turbine Van Tested with Cold Air in a Two-dimensional Cascade
Author: John F. KlinePublisher:
ISBN:
Category : Turbines
Languages : en
Pages : 52
Book Description
The Effects of Film Cooling Upon the Aerodynamic Performance of Transonic Turbine Blades
Author: B. R. HallerAerodynamic Performance of a Fully Film Cooled Core Turbine Vane Tested with Cold Air in a Two-dimensional Cascade
Author: Roy G. StabePublisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 24
Book Description
The aerodynamic performance of a fully film cooled core turbine vane was investigated experimentally in a two-dimensional cascade of 10 vanes. Three of the 10 vanes were cooled; the others were solid (uncooled) vanes. Cold air was used for both the primary and coolant flows. The cascade test covered a range of pressure ratios corresponding to ideal exit critical velocity ratios of 0.6 to 0.95 and a range of coolant flow rates to 7.5 percent of the primary flow. The coolant flow was varied by changing the coolant supply pressure. The principal measurements were cross-channel surveys of exit total pressure, static pressure, and flow angle. The results presented include exit survey data and overall performance in terms of loss, flow angle, and weight flow for the range of exit velocity ratios and coolant flows investigated. The performance of the cooled vane is compared with the performance of an uncooled vane of the same profile and also with the performance obtained with a single cooled vane in the 10-vane cascade.
Cold-air Annular-cascade Investigation of Aerodynamic Performance of Cooled Turbine Vanes: Trailing-edge ejection, film cooling, and transpiration cooling
Author: Goldman, Louis J.Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 40
Book Description
Aerodynamic Performance Measurements of a Fully Scaled, Film-coated, Turbine Stage
Author: Christopher Michael SpadacciniPublisher:
ISBN:
Category :
Languages : en
Pages : 148
Book Description
Film Cooling, Heat Transfer and Aerodynamic Measurements in a Three Stage Research Gas Turbine
Author: Arun SuryanarayananPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
The existing 3-stage turbine research facility at the Turbomachinery Performance and Flow Research Laboratory (TPFL), Texas A and M University, is re-designed and newly installed to enable coolant gas injection on the first stage rotor platform to study the effects of rotation on film cooling and heat transfer. Pressure and temperature sensitive paint techniques are used to measure film cooling effectiveness and heat transfer on the rotor platform respectively. Experiments are conducted at three turbine rotational speeds namely, 2400rpm, 2550rpm and 3000rpm. Interstage aerodynamic measurements with miniature five hole probes are also acquired at these speeds. The aerodynamic data characterizes the flow along the first stage rotor exit, second stage stator exit and second stage rotor exit. For each rotor speed, film cooling effectiveness is determined on the first stage rotor platform for upstream stator-rotor gap ejection, downstream discrete hole ejection and a combination of upstream gap and downstream hole ejection. Upstream coolant ejection experiments are conducted for coolant to mainstream mass flow ratios of MFR=0.5%, 1.0%, 1.5% and 2.0% and downstream discrete hole injection tests corresponding to average hole blowing ratios of M = 0.5, 0.75, 1.0, 1.25, 1.5, 1.75 and 2.0 for each turbine speed. To provide a complete picture of hub cooling under rotating conditions, experiments with simultaneous injection of coolant gas through upstream and downstream injection are conducted for an of MFR=1% and Mholes=0.75, 1.0 and 1.25 for the three turbine speeds. Heat transfer coefficients are determined on the rotor platform for similar upstream and downstream coolant injection. Rotation is found to significantly affect the distribution of coolant on the platform. The measured effectiveness magnitudes are lower than that obtained with numerical simulations. Coolant streams from both upstream and downstream injection orient themselves towards the blade suction side. Passage vortex cuts-off the coolant film for the lower MFR for upstream injection. As the MFR increases, the passage vortex effects are diminished. Effectiveness was maximum when Mholes was closer to one as the coolant ejection velocity is approximately equal to the mainstream relative velocity for this blowing ratio. Heat transfer coefficient and film cooling effectiveness increase with increasing rotational speed for upstream rotor stator gap injection while for downstream hole injection the maximum effectiveness and heat transfer coefficients occur at the reference speed of 2550rpm.
Cold-air Annular-cascade Investigation of Aerodynamic Performance of Cooled Turbine Vanes
Author: Goldman, Louis J.Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 34
Book Description