Author: A.B. TurnerPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Local heat transfer measurements on a gas turbine blade (Journal of Mechanism v13 n1 Feb1 1971 p1-12).
Author: A.B. TurnerLocal Heat Transfer Measurements on a Gas Turbine Blade
Author: A. B. TurnerHeat Transfer Measurements and Predictions on a Power Generation Gas Turbine Blade
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
Detailed heat transfer measurements and predictions are given for a power generation turbine rotor with 129 deg of nominal turning and an axial chord of 137 mm. Data were obtained for a set of four exit Reynolds numbers comprised of the design point of 628,000, -20%, +20%, and +40%. Three ideal exit pressure ratios were examined including the design point of 1.378, -10%, and +10%. Inlet incidence angles of 0 deg and +/-2 deg were also examined. Measurements were made in a linear cascade with highly three-dimensional blade passage flows that resulted from the high flow turning and thick inlet boundary layers. Inlet turbulence was generated with a blown square bar grid. The purpose of the work is the extension of three-dimensional predictive modeling capability for airfoil external heat transfer to engine specific conditions including blade shape, Reynolds numbers, and Mach numbers. Data were obtained by a steady-state technique using a thin-foil heater wrapped around a low thermal conductivity blade. Surface temperatures were measured using calibrated liquid crystals. The results show the effects of strong secondary vortical flows, laminar-to-turbulent transition, and also show good detail in the stagnation region.
Measurements of Heat Transfer, Flow, and Pressures in a Simulated Turbine Blade Internal Cooling Passage
Author: Louis M. RussellPublisher:
ISBN:
Category : Flow visualization
Languages : en
Pages : 30
Book Description
An experimental study was made to obtain quantitative information on heat transfer, flow, and pressure distribution in a branched duct test section that had several significant features of an internal cooling passage of a turbine blade. The objective of this study was to generate a set of experimental data that could be used for validation of computer codes that would be used to model internal cooling. Surface heat transfer coefficients and entrance flow conditions were measured at nominal entrance Reynolds numbers of 45 000, 335 000, and 726 000. Heat transfer data were obtained by using a steady-state technique in which an Inconel heater sheet is attached to the surface and coated with liquid crystals. Visual and quantitative flow-field data from particle image velocimetry measurements for a plane at midchannel height for a Reynolds number of 45 000 were also obtained. The flow was seeded with polystyrene particles and illuminated by a laser light sheet. Pressure distribution measurements were made both on the surface with discrete holes and in the flow field with a total pressure probe. The flow-field measurements yielded flow-field velocities at selected locations. A relatively new method, pressure sensitive paint, was also used to measure surface pressure distribution. The pressure paint data obtained at Reynolds numbers of 335 000 and 726 000 compared well with the more standard method of measuring pressures by using discrete holes.
Experimental Investigation of the Heat-transfer Characteristics of an Air-cooled Sintered Porous Turbine Blade
Author: Louis J. Schafer (Jr.)Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 38
Book Description
Temperatures and Stresses on Hollow Blades for Gas Turbines
Author: Erich PollmanPublisher:
ISBN:
Category : Blades
Languages : en
Pages : 600
Book Description
The present treatise reports on theoretical investigations and test-stand measurements which were carried out in the BMW Flugmotoren GMbH in developing the hollow blade for exhaust gas turbines. As an introduction the temperature variation and the stress on a turbine blade for a gas temperature of 900 degrees and circumferential velocities of 600 meters per second are discussed. The assumptions onthe heat transfer coefficients at the blade profile are supported by tests on an electrically heated blade model. The temperature distribution in the cross section of a blade Is thoroughly investigated and the temperature field determined for a special case. A method for calculation of the thermal stresses in turbine blades for a given temperature distribution is indicated. The effect of the heat radiation on the blade temperature also is dealt with. Test-stand experiments on turbine blades are evaluated, particularly with respect to temperature distribution in the cross section; maximum and minimum temperature in the cross section are ascertained. Finally, the application of the hollow blade for a stationary gas turbine is investigated. Starting from a setup for 550 C gas temperature the improvement of the thermal efficiency and the fuel consumption are considered as well as the increase of the useful power by use of high temperatures. The power required for blade cooling is taken into account.
Heat Transfer Measurement on the Surface of a Large Scale Gas Turbine Blade with a Profiled Endwall
Author: Michael A. VolkTurbine Engine Hot Section Technology, 1987
Author: Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 492
Book Description
Local Mass Transfer Measurement from a Turbine Blade
Author: Haiping WangEffect of Blade-tip Crossover Passages on Natural-convection Water-cooling of Gas-turbine Blades
Author: Charles F. ZalabakPublisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 32
Book Description
A water-cooled turbine was fabricated and tested to determine the effect of a connecting passage at the turbine rotor blade tip between a radial coolant passage 0.10 inch in diameter (length-diameter ratio = 25.5) and radial coolant passages in the legnth-diameter range of 5.1 to 20.4. Coolant flow through the connecting passage is induced by free-convection forces in the radial passages.