The removal of unwanted edge contours from gravity datasets

2013 ◽  
Vol 44 (1) ◽  
pp. 42-47 ◽  
Author(s):  
Gordon R. J. Cooper
Keyword(s):  
Edge Contours

Edge contours using multiple scales

1990 ◽  
Vol 50 (3) ◽  
pp. 364
Author(s):  
Donna J Williams ◽  
Mubarak Shah
Keyword(s):  
Multiple Scales ◽  
Edge Contours

4D Measurements and Analysis of Heat Release Rate in a Model Gas Turbine Combustor

2020 ◽  
Author(s):  
Rongxiao Dong ◽  
Qingchun Lei ◽  
Yeqing Chi ◽  
Qun Zhang ◽  
Wei Fan
Keyword(s):  
Heat Release ◽  
Gas Turbine ◽  
Surface Area ◽  
Heat Release Rate ◽  
Release Rate ◽  
Flame Surface ◽  
Global Instability ◽  
Gas Turbine Combustor ◽  
Model Gas Turbine Combustor ◽  
Edge Contours

Abstract Time-resolved volumetric measurements (4D measurements) were performed to study the heat release rate characteristics in a model gas turbine combustor at 10 kHz. For this purpose, a high-speed camera combined with an image intensifier and a set of customized fiber probes were employed to continuously capture the CH* chemiluminescence signals from nine different viewing angles. Based on the measurements, the computed tomography program was performed to reconstruct the shot-to-shot 3D distributions of the CH* signals. Specific focuses have been made to demonstrate the capabilities of the current tomographic technique in applications of a realistic combustor, in which the full optical access was usually not available for every viewing angle. The results showed that the 3D reconstruction can successfully retrieval the flame edge contours rather than the signal intensity. The flame surface area was then calculated based on the reconstructed flame edge contours and used to infer the heat release rate. The fluctuation of global/local flame surface area indicated that there existed distinct difference between the global instability and local instabilities at various locations in the non-symmetric combustor. The global instability appears to be an integration of those local instabilities.

scholarly journals SINGLE PASS CLEAVING OF ULTRAFAST LASER MODIFIED C-SHAPED GLASS EDGES

2021 ◽  
Author(s):  
Daniel Flamm ◽  
Myriam Kaiser ◽  
Jonas Kleiner ◽  
Tim Hesse
Keyword(s):  
Beam Splitter ◽  
Selective Etching ◽  
Ultrafast Laser ◽  
Full Thickness ◽  
Single Pass ◽  
Optical Head ◽  
Single Side ◽  
Transparent Materials ◽  
Shaped Glass ◽  
Edge Contours

We report on single-pass laser cleaving of transparent materials with C-shaped edges that exhibit 45-deg tangential angles to the surface. A holographic 3D beam splitter distributes several foci along the desired edge contours, including C-shaped edges. Single-pass, full thickness laser modifications are achieved requiring single-side access to the workpiece only without inclining the optical head. After having induced laser modifications with feed rates in the order of 100 mm/s actual separation is performed using a selective etching strategy.

Jet Engine Compressor Blade Refurbishment by Application of the Advanced Re-Contouring Process

2003 ◽  
Author(s):  
Herwart T. Hoenen ◽  
Karsten Ellenberger
Keyword(s):  
High Pressure ◽  
Flow Behavior ◽  
Leading Edge ◽  
Compressor Blade ◽  
Tip Clearance ◽  
Jet Propulsion ◽  
High Pressure Compressor ◽  
Leading Edges ◽  
Pressure Compressor ◽  
Edge Contours

In modern jet propulsion Systems the core engine has an essential influence on the total engine performance. Especially the high pressure compressor plays an important role in this scheme. Substantial factors here are losses due to tip clearance effects and aerodynamic airfoil quality. During flight Operation the airfoils are subject to wear and tear on the leading edge. These effects cause a shortening of the chord length and the leading edge profiles become deformed. This results in a deterioration of the engine efficiency performance level and a reduced stall margin. The paper deals with the re-contouring of the leading edges of compressor airfoils. Lufthansa Technik AG in cooperation with the Institute of Jet Propulsion and Turbomachinery (RWTH Aachen University) developed a new method for the profile definition for the blade refurbishment. The common procedure of smoothing out the leading edges manually on a wheel grinding machine can not provide a defined contour nor a reproducible result of the overhaul process. In order to achieve optimized flow conditions in the compressor blade rows, suitable leading edge contours have to be defined for the worn airfoils. In an iterative process the flow behavior of these redesigned profiles is checked by numerical flow simulations and the shape of the profiles is improved. The following machining of the new defined leading edge contours is achieved on a grinding station handled by an appropriately programmed robot. Within this Advanced Re-contouring Process (ARP) the worn blades are precision-measured and then provided with an aerodynamically optimized leading edge profile numerically newly developed under computer control. The application of this process enhances the performance and lowers the fuel consumption while prolonging the blades’ service life by 25%. The performance achievable with ARP has been confirmed both through a long term analysis and by a back-to-back comparison test on the engine test stand. For this purpose the stages 3 through 14 of a CF6-50 high pressure compressor were on the one hand fitted with conventionally overhauled blades and on the other with ARP-optimized blades of the same basic geometry. By installing the optimized blades the EGT margin could be increased by 3° to 4° C. This results in an prolongation of the on-wing time by more than 1000 hours.

A lateral differential confocal microscopy for accurate detection and localization of edge contours

2014 ◽  
Vol 53 ◽  
pp. 12-18 ◽  
Author(s):  
Yifan Wang ◽  
Cuifang Kuang ◽  
Peng Xiu ◽  
Shuai Li ◽  
Xiang Hao ◽  
...  
Keyword(s):  
Confocal Microscopy ◽  
Accurate Detection ◽  
Detection And Localization ◽  
Edge Contours
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