Measurement of Turbine Rotor Blade Flows

1981 ◽  
Vol 103 (2) ◽  
pp. 400-405 ◽  
Author(s):  
R. P. Dring ◽  
H. D. Joslyn
Keyword(s):  
Rotor Blade ◽  
Static Pressure ◽  
Turbine Rotor ◽  
Measurement Methods ◽  
Incident Flow ◽  
Airfoil Surface ◽  
Turbine Rotor Blade ◽  
Pressure Distributions ◽  
Different Types ◽  
Flow Phenomena

Measurement methods for obtaining various types of experimental data on a turbine rotor blade are discussed in this paper. A variety of different types of measurements have been taken in the rotating frame of reference, including: airfoil surface static pressure distributions, the radial distribution of total pressure in the incident flow, flow visualization of surface streamlines, and radial-circumferential traversing of a pneumatic probe aft of the rotor. Typical results are presented/showing interesting flow phenomena present on the rotor. In particular, results are shown which demonstrate the various viscous and inviscid mechanisms that give rise to strong radial flows.

Turbine Rotor Generated Forcing Functions for Flow Induced Vibrations

1994 ◽  
Author(s):  
Matthew M. Weaver ◽  
Stanford Fleeter
Keyword(s):  
Rotor Blade ◽  
Static Pressure ◽  
Turbine Rotor ◽  
Blade Loading ◽  
Turbine Rotor Blade ◽  
Forcing Functions ◽  
Force Direction ◽  
Flow Induced Vibrations ◽  
Series Of Experiments ◽  
First Time

A series of experiments are performed to investigate the effect of steady loading on the unsteady aerodynamic gust forcing functions generated by turbine rotor blade rows and the validity of the vortical and potential gust splitting techniques. Both the downstream vortical-potential gusts and, for the first time, the upstream generated potential gust are considered. Note that these upstream gusts are in fact the potential field of the rotor and not the nozzle wakes. This is accomplished by measuring the downstream and upstream unsteady forcing functions generated by the first stage rotor of the low speed research turbine over a range of steady loading levels. These forcing functions are then split into vortical and potential gusts utilizing both the V-Method using only velocity data and the P-Method which also incorporates unsteady static pressure data. The results clearly show an increase in potential effects for the downstream gust forcing functions with increased blade loading. The rotor blade gusts upstream of the first rotor are theoretically purely potential gusts since no vorticity can be conducted upstream. These potential disturbances do not appear to be a function of the blade loading. The results of the linear theory splitting show that both splitting methods have discrepancies in their recombined forcing functions. The V-Method either under or over estimates the unsteady static pressure and has trouble duplicating the phase. The P-Method tends to skew the recombined velocity in the lift force direction. The upstream potential gusts posed a particular problem for the splitting, with neither method able to fully reconcile the measured pressure and velocity perturbations.

scholarly journals Heat Transfer and Pressure Distributions on a Gas Turbine Blade Tip

2000 ◽  
Vol 122 (4) ◽  
pp. 717-724 ◽  
Author(s):  
Gm. S. Azad ◽  
Je-Chin Han ◽  
Shuye Teng ◽  
Robert J. Boyle
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Turbulence Intensity ◽  
Rotor Blade ◽  
Static Pressure ◽  
Pressure Distributions ◽  
Blade Tip

Heat transfer coefficient and static pressure distributions are experimentally investigated on a gas turbine blade tip in a five-bladed stationary linear cascade. The blade is a two-dimensional model of a first-stage gas turbine rotor blade with a blade tip profile of a GE-E3 aircraft gas turbine engine rotor blade. The flow condition in the test cascade corresponds to an overall pressure ratio of 1.32 and exit Reynolds number based on axial chord of 1.1×106. The middle 3-blade has a variable tip gap clearance. All measurements are made at three different tip gap clearances of about 1, 1.5, and 2.5 percent of the blade span. Heat transfer measurements are also made at two different turbulence intensity levels of 6.1 and 9.7 percent at the cascade inlet. Static pressure measurements are made in the midspan and the near-tip regions as well as on the shroud surface, opposite the blade tip surface. Detailed heat transfer coefficient distributions on the plane tip surface are measured using a transient liquid crystal technique. Results show various regions of high and low heat transfer coefficient on the tip surface. Tip clearance has a significant influence on local tip heat transfer coefficient distribution. Heat transfer coefficient also increases about 15–20 percent along the leakage flow path at higher turbulence intensity level of 9.7 over 6.1 percent. [S0889-504X(00)00404-9]

Implementation of bending-torsion coupling in the design of a wind-turbine rotor-blade

1999 ◽  
Vol 63 (3) ◽  
pp. 191-207 ◽  
Author(s):  
W.C. de Goeij ◽  
M.J.L. van Tooren ◽  
A. Beukers
Keyword(s):  
Wind Turbine ◽  
Rotor Blade ◽  
Turbine Rotor ◽  
Turbine Rotor Blade ◽  
Wind Turbine Rotor

scholarly journals Paint it black: Efficacy of increased wind turbine rotor blade visibility to reduce avian fatalities

2020 ◽  
Vol 10 (16) ◽  
pp. 8927-8935
Author(s):  
Roel May ◽  
Torgeir Nygård ◽  
Ulla Falkdalen ◽  
Jens Åström ◽  
Øyvind Hamre ◽  
...  
Keyword(s):  
Wind Turbine ◽  
Rotor Blade ◽  
Turbine Rotor ◽  
Turbine Rotor Blade ◽  
Wind Turbine Rotor
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