scholarly journals Discussion: “Short Duration Measurements of Heat-Transfer Rate to a Gas Turbine Rotor Blade” (Consigny, H., and Richards, B. E., 1982, ASME J. Eng. Power, 104, pp. 542–550)

1982 ◽  
Vol 104 (3) ◽  
pp. 550-551
Author(s):  
Ronald M. C. So ◽  
Russell E. Sheer
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Heat Transfer Rate ◽  
Short Duration ◽  
Rotor Blade ◽  
Transfer Rate ◽  
Turbine Rotor ◽  
Turbine Rotor Blade

Effect of Flow Exit Angle and Blade Height on the Temperature Distribution of a Typical Gas Turbine Rotor Blade

2012 ◽  
Vol 452-453 ◽  
pp. 502-506
Author(s):  
Esmail Poursaeidi ◽  
Maryam Mohammadi ◽  
Seyed Sina Khamesi
Keyword(s):  
Heat Transfer ◽  
Temperature Distribution ◽  
Heat Transfer Rate ◽  
Direct Effect ◽  
Rotor Blade ◽  
Transfer Rate ◽  
Turbine Rotor ◽  
Exit Angle ◽  
Blade Height ◽  
Turbine Rotor Blade

One of the major factors which have important effects in turbine blade designing is temperature distribution and its heat transfer rate. The temperature distribution in blades depends on many factors; one of the most important ones is the geometry of the blades. In this paper by continuing some previous findings about the geometry[1], an optimized blade and a real one are compared from the thermally aspect view. Flow exit angle of the rotor blade and the blade height are two parameters which have direct effect on the heat transfer rate. The presented temperature distribution is solved based on the new flow exit angle of rotor blade. By optimizing the flow exit angle for the first time, the blade height is computed. By solving mathematically and thermodynamically relations and writing a solving code based on the finite volume method, the temperature and the heat transfer rate are computed numerically. These results shows the direct effect of flow exit angle on temperature distribution which can be used for upgrading the turbine efficiency.

Short Duration Measurements of Heat-Transfer Rate to a Gas Turbine Rotor Blade

1982 ◽  
Vol 104 (3) ◽  
pp. 542-550 ◽  
Author(s):  
H. Consigny ◽  
B. E. Richards
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Reynolds Number ◽  
Gas Turbine ◽  
Rotor Blade ◽  
Transfer Rate ◽  
Turbine Rotor ◽  
Turbulence Level ◽  
Flow Angle ◽  
Turbine Rotor Blade

The paper describes the results of an experimental study of the effect of Mach number, Reynolds number, inlet flow angle, and free-stream turbulence level on heat transfer rate to a gas turbine rotor blade. The measurements were made in the VKI short-duration isentropic light piston tunnel using thin film heat transfer gages painted on a machinable ceramic blade of 80 mm chord and 100 mm height. The tests were performed for three cascade inlet Mach numbers: 0.62, 0.92, 1.15; inlet unit Reynolds number was varied from 0.3 × 107 m−1 to 1.2 × 107 m−1; the inlet flow angle from 30 to 45 deg (for an inlet blade angle of 30 deg); the turbulence level from 0.8 percent to approximately 5 percent. The effect of changing these parameters on boundary layer transition and separation, on leading edge and average heat transfer to the blade was examined. For typical situations, experimental blade heat distributions were compared with boundary layer predictions using a two-equation closure model.

scholarly journals Analysis of Gas Turbine Rotor Blade Tip and Shroud Heat Transfer

1996 ◽  
Author(s):  
A. A. Ameri ◽  
E. Steinthorsson
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Rotor Blade ◽  
Stokes Equations ◽  
Computer Code ◽  
Turbine Rotor ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Turbine Rotor Blade ◽  
Blade Tip

Predictions of the rate of heat transfer to the tip and shroud of a gas turbine rotor blade are presented. The simulations are performed with a multiblock computer code which solves the Reynolds Averaged Navier-Stokes equations. The effect of inlet boundary layer thickness as well as rotation rate on the tip and shroud heat transfer is examined. The predictions of the blade tip and shroud heat transfer are in reasonable agreement with the experimental measurements. Areas of large heat transfer rates are identified and physical reasoning for the phenomena presented.

Gas Turbine Rotor Blade Film Cooling With and Without Simulated NGV Shock Waves and Wakes

1990 ◽  
Author(s):  
M. J. Rigby ◽  
A. B. Johnson ◽  
M. L. G. Oldfield
Keyword(s):  
Heat Transfer ◽  
Shock Wave ◽  
Gas Turbine ◽  
Film Cooling ◽  
Rotor Blade ◽  
Guide Vane ◽  
Turbine Rotor ◽  
Suction Surface ◽  
Turbine Rotor Blade ◽  
Wake Passing

Detailed heat transfer measurements have been made around a film-cooled transonic gas turbine rotor blade in the Oxford Isentropic Light Piston Tunnel. Film cooling behaviour for four film cooling configurations has been analysed for a range of blowing rates both without and with simulated nozzle guide vane (NGV) shock wave and wake passing. The superposition model of film cooling has been employed in analysis of time-mean heat transfer data, while time resolved unsteady heat transfer measurements have been analysed to determine interaction between film-cooling and unsteady shock wave and wake passing. It is found that there is a significant change of film-cooling behaviour on the suction surface when simulated NGV unsteady effects are introduced.

Surface Heat Transfer Fluctuations on a Turbine Rotor Blade Due to Upstream Shock Wave Passing

1989 ◽  
Vol 111 (2) ◽  
pp. 105-115 ◽  
Author(s):  
A. B. Johnson ◽  
M. J. Rigby ◽  
M. L. G. Oldfield ◽  
R. W. Ainsworth ◽  
M. J. Oliver
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Shock Waves ◽  
Rotor Blade ◽  
Transfer Rate ◽  
Turbine Rotor ◽  
Surface Heat ◽  
Transfer Rates ◽  
Surface Heat Transfer ◽  
Turbine Rotor Blade

A theoretical model to explain observed rapid large-scale surface heat transfer rate fluctuations associated with the impingement of nozzle guide vane trailing edge shock waves on a transonic turbine rotor blade is described. Experiments were carried out in the Oxford Isentropic Light Piston Cascade Tunnel using an upstream rotating bar system to simulate the shock wave passing. High-frequency surface heat transfer and pressure measurements gave rapidly varying, large, transient signals, which schlieren photography showed to be associated with the impingement of passing shock waves on the surface. Heat transfer rates varying from three times the mean value to negative quantities were measured. A simple first-order perturbation analysis of the boundary layer equations shows that the transient adiabatic heating and cooling of the boundary layer by passing shock waves and rarefactions can give rise to high-temperature gradients near the surface. This in turn leads to large conductive heat transfer rate fluctuations. The application of this theory to measured fluctuating pressure signals gave predictions of fluctuating heat transfer rates that are in good agreement with those measured. It is felt that the underlying physical mechanisms for shock-induced heat transfer fluctuations have been identified. Further work will be necessary to confirm them in rotating experiments.

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