Symmetrical or non-symmetrical luminescent turnstiles based on hydroquinone stators and rotors bearing pyridyl or p-dimethylaminopyridyl coordinating units

2017 ◽  
Vol 46 (43) ◽  
pp. 14897-14906 ◽  
Author(s):  
Bérangère Godde ◽  
Abdelaziz Jouaiti ◽  
Audrey Fluck ◽  
Nathalie Kyritsakas ◽  
Matteo Mauro ◽  
...  
Keyword(s):  
Stators And Rotors

Luminescent symmetrical and non-symmetrical molecular turnstiles based on hydroquinone stators and rotors bearing coordinating units are reported.

scholarly journals Physical Aspects of Deposition From Coal Water Fuels Under Gas Turbine Conditions

1989 ◽  
Author(s):  
Richard A. Wenglarz ◽  
Ralph G. Fox
Keyword(s):  
Gas Turbine ◽  
Combustion Products ◽  
Control Measures ◽  
Unburned Carbon ◽  
Test Results ◽  
Gas Temperature ◽  
Hot Gas ◽  
Stators And Rotors ◽  
Temperature Surface ◽  
Deposition Control

Deposition, erosion, and corrosion (DEC) experiments were conducted using three coal-water fuels (CWF) in a staged subscale turbine combustor operated at conditions of a recuperated turbine. This rich-quench-lean (RQL) combustor appears promising for reducing NOx levels to acceptable levels for future turbines operating with CWF. Specimens were exposed in two test sections to the combustion products from the RQL combustor. The gas and most surface temperatures in the first and second test sections represented temperatures in the first stators and rotors, respectively, of a recuperated turbine. The test results indicate deposition is affected substantially by gas temperature, surface temperature, and unburned carbon due to incomplete combustion. The high rates of deposition observed at first stator conditions showed the need for additional tests to identify CWF coals with lower deposition tendencies and to explore deposition control measures such as hot gas cleanup.

Improved Approach to the Streamline Curvature Method in Turbomachinery

1987 ◽  
Vol 109 (3) ◽  
pp. 213-217 ◽  
Author(s):  
S. Abdallah ◽  
R. E. Henderson
Keyword(s):  
Flow Field ◽  
Velocity Gradient ◽  
Numerical Solutions ◽  
Three Dimensional ◽  
Second Order ◽  
Curvilinear Coordinates ◽  
First Order ◽  
Streamline Curvature ◽  
Stators And Rotors ◽  
Streamline Curvature Method

Quasi three dimensional blade-to-blade solutions for stators and rotors of turbomachines are obtained using the Streamline Curvature Method (SLCM). The first-order velocity gradient equation of the SLCM, traditionally solved for the velocity field, is reformulated as a second-order elliptic differential equation and employed in tracing the streamtubes throughout the flow field. The equation of continuity is then used to calculate the velocity. The present method has the following advantages. First, it preserves the ellipticity of the flow field in the solution of the second-order velocity gradient equation. Second, it eliminates the need for curve fitting and strong smoothing under-relaxation in the classical SLCM. Third, the prediction of the stagnation streamlines is a straightforward matter which does not complicate the present procedure. Finally, body-fitted curvilinear coordinates (streamlines and orthogonals or quasi-orthogonals) are naturally generated in the method. Numerical solutions are obtained for inviscid incompressible flow in rotating and non-rotating passages and the results are compared with experimental data.

Numerical Investigation of Wake-Shock Interactions and Clocking in a Transonic HP Turbine

2003 ◽  
Author(s):  
Michele Marconcini ◽  
Roberto Pacciani
Keyword(s):  
Shock Waves ◽  
Gas Turbine ◽  
Three Dimensional ◽  
Frame Of Reference ◽  
Heavy Duty ◽  
Blade Loading ◽  
Shock Interactions ◽  
Blade Row ◽  
Wake Passing ◽  
Stators And Rotors

A quasi-three-dimensional, blade-to-blade, time-accurate, viscous solver was used for the clocking optimization of a modern transonic heavy-duty, two stage gas turbine. Both stators and rotors operate in a transonic regime with fish-tail shock systems at the blade row exit. These shock systems interact with both stator and rotor wakes. A sensible reduction in the strength of shock waves was observed due to the upstream blade row wake passing. Such wake-shock interactions occur in the inter-blade gap, around locations which are fixed in the frame of reference of the downstream blade-row. The exploitation of such an effect to optimize the axial/circumferential position of blade rows is still compatible with the axial gap values commonly used for these kinds of stages. The results of the clocking investigation will be presented and discussed in terms of unsteady blade loading and efficiency variations.

Measurement of Tip-Clearance Flow in a Multi-Stage, Axial Flow Compressor

1994 ◽  
Author(s):  
Andrew C. Foley ◽  
Paul C. Ivey
Keyword(s):  
Large Scale ◽  
Static Pressure ◽  
Axial Flow ◽  
Tip Clearance ◽  
Suction Surface ◽  
Tip Clearance Flow ◽  
Laser Anemometry ◽  
Two Dimensional Flow ◽  
Inlet Conditions ◽  
Stators And Rotors

Detailed measurements using pneumatic probe traverses, blade static pressure tappings and laser anemometry are made in the third stage of a large scale, low speed, four stage, axial flow, research compressor. Inlet conditions show well ordered ‘two dimensional’ flow from approximately 40 to 85% annulus span. Outside of this region, reduced total pressure due to upstream leakage losses aod endwall effects results in high incidence to the following blade row. As a result, peak suction surface static pressure moves forward along the blade chord for both the huh and tip of stators and rotors. At the blade tip however, the peak suction pressure is maintained with chord due to radial flow on the suction surface being entrained into the tip leakage jet. The extent of rotor chord for which this ‘entrainment’ occurs increases with increasing rotor tip clearance gap. The leakage jet from both stators and rotors is seen to ‘roll up’ into a vortex downstream of their respective blade rows.

Measurement of Tip-Clearance Flow in a Multistage, Axial Flow Compressor

1996 ◽  
Vol 118 (2) ◽  
pp. 211-217 ◽  
Author(s):  
A. C. Foley ◽  
P. C. Ivey
Keyword(s):  
Large Scale ◽  
Static Pressure ◽  
Axial Flow ◽  
Tip Clearance ◽  
Suction Surface ◽  
Tip Clearance Flow ◽  
Laser Anemometry ◽  
Two Dimensional Flow ◽  
Inlet Conditions ◽  
Stators And Rotors

Detailed measurements using pneumatic probe traverses, blade static pressure tappings, and laser anemometry are made in the third stage of a large-scale, low-speed, four-stage, axial flow, research compressor. Inlet conditions show well-ordered “two-dimensional” flow from approximately 40 to 85 percent annulus span. Outside of this region, reduced total pressure due to upstream leakage losses and endwall effects results in high incidence to the following blade row. As a result, peak suction surface static pressure moves forward along the blade chord for both the hub and tip of stators and rotors. At the blade tip, however, the peak suction pressure is maintained with chord due to radial flow on the suction surface being entrained into the tip leakage jet. The extent of rotor chord for which this “entrainment” occurs increases with increasing rotor tip clearance gap. The leakage jet from both stators and rotors is seen to “roll up” into a vortex downstream of their respective blade rows.

Physical Aspects of Deposition From Coal-Water Fuels Under Gas Turbine Conditions

1990 ◽  
Vol 112 (1) ◽  
pp. 9-14 ◽  
Author(s):  
R. A. Wenglarz ◽  
R. G. Fox
Keyword(s):  
Gas Turbine ◽  
Combustion Products ◽  
Control Measures ◽  
Unburned Carbon ◽  
Test Results ◽  
Gas Temperature ◽  
Hot Gas ◽  
Stators And Rotors ◽  
Temperature Surface ◽  
Deposition Control

Deposition, erosion, and corrosion (DEC) experiments were conducted using three coal-water fuels (CWF) in a staged subscale turbine combustor operated at conditions of a recuperated turbine. This rich-quench-lean (RQL) combustor appears promising for reducing NOx levels to acceptable levels for future turbines operating with CWF. Specimens were exposed in two test sections to the combustion products from the RQL combustor. The gas and most surface temperatures in the first and second test sections represented temperatures in the first stators and rotors, respectively, of a recuperated turbine. The test results indicate deposition is affected substantially by gas temperature, surface temperature, and unburned carbon due to incomplete combustion. The high rates of deposition observed at first stator conditions showed the need for additional tests to identify CWF coals with lower deposition tendencies and to explore deposition control measures such as hot gas cleanup.

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