Microstructural Damage Analysis of Service Turbine Blades for an Aero-engine

2019 ◽  
Vol 55 (13) ◽  
pp. 122
Author(s):  
FAN Yongsheng ◽  
HUANG Weiqing ◽  
YANG Xiaoguang ◽  
SHI Duoqi
Keyword(s):  
Turbine Blades ◽  
Damage Analysis ◽  
Microstructural Damage ◽  
Aero Engine

Effect of Periodic Wake Passing on Film Effectiveness of Discrete Cooling Holes Around the Leading Edge of a Blunt Body

1997 ◽  
Vol 119 (2) ◽  
pp. 292-301 ◽  
Author(s):  
K. Funazaki ◽  
M. Yokota ◽  
S. Yamawaki
Keyword(s):  
Blunt Body ◽  
Free Stream ◽  
Turbine Blades ◽  
Density Ratio ◽  
Leading Edge ◽  
Test Model ◽  
Free Stream Turbulence ◽  
Aero Engine ◽  
Secondary Air ◽  
Wake Passing

Detailed studies are conducted on film effectiveness of discrete cooling holes around the leading edge of a blunt body that is subjected to periodically incoming wakes as well as free-stream turbulence with various levels of intensity. The cooling holes have a configuration similar to that of typical turbine blades except for the spanwise inclination angle. Secondary air is heated so that the temperature difference between the mainstream and secondary air is about 20 K. In this case, the air density ratio of the mainstream and secondary air becomes less than unity, therefore the flow condition encountered in an actual aero-engine cannot be simulated in terms of the density ratio. A spoke-wheel type wake generator is used in this study. In addition, three types of turbulence grids are used to elevate the free-stream turbulence intensity. We adopt three blowing ratios of the secondary air to the mainstream. For each of the blowing ratios, wall temperatures around the surface of the test model are measured by thermocouples situated inside the model. The temperature is visualized using liquid crystals in order to obtain qualitative information of film effectiveness distribution.

The Effect of Periodic Wake Passing on Film Effectiveness of Discrete Cooling Holes Around the Leading Edge of a Blunt Body

1995 ◽  
Author(s):  
K. Funazaki ◽  
M. Yokota ◽  
S. Yamawaki
Keyword(s):  
Blunt Body ◽  
Free Stream ◽  
Turbine Blades ◽  
Density Ratio ◽  
Leading Edge ◽  
Test Model ◽  
Free Stream Turbulence ◽  
Aero Engine ◽  
Secondary Air ◽  
Wake Passing

Detailed studies are conducted on film effectiveness of discrete cooling holes around the leading edge of a blunt body that is subjected to periodically incoming wakes as well as free-stream turbulence with various levels of intensity. The cooling holes have a configuration similar to that of typical turbine blades except for the spanwise inclination angle. Secondary air is heated so that the temperature difference between the mainstream and secondary air is about 20K. In this case, air density ratio of the mainstream and secondary air becomes less than unity, therefore the flow condition encountered in an actual aero-engine can not be simulated in terms of the density ratio. A spoke-wheel type wake generator is used in this study. In addition, three types of turbulence grids are used to elevate the free-stream turbulence intensity. We adopt three blowing ratios of the secondary air to the mainstream. For each of the blowing ratios, wall temperature around the surface of the test model are measured by thermocouples situated inside the model. The temperature is visualized using liquid crystals in order to obtain qualitative information of film effectiveness distribution.

scholarly journals Microstructural Damage Evaluation in Ni-based Superalloy Gas Turbine Blades by Fractal Analysis

2013 ◽  
Vol 55 ◽  
pp. 289-294 ◽  
Author(s):  
Mita Tarafder ◽  
M. Sujata ◽  
V.R. Ranganath ◽  
S. Tarafder ◽  
S.K. Bhumik
Keyword(s):  
Gas Turbine ◽  
Fractal Analysis ◽  
Turbine Blades ◽  
Damage Evaluation ◽  
Gas Turbine Blades ◽  
Microstructural Damage

Experimental and Numerical Correlation of Impact of Spherical Projectile for Damage Analysis of Aero Engine Component

2016 ◽  
Vol 66 (2) ◽  
pp. 193 ◽  
Author(s):  
Anuradha Nayak Majila ◽  
Rajeev Jain ◽  
Chandru Fernando D. ◽  
S. Ramachandra
Keyword(s):  
Finite Element ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Metallographic Analysis ◽  
Damage Analysis ◽  
Alloy Plate ◽  
Turbine Engine ◽  
Aero Engine ◽  
Engine Components ◽  
The Impact

<p>Studies the impact response of flat Titanium alloy plate against spherical projectile for damage analysis of aero engine components using experimental and finite element techniques. Compressed gas gun has been used to impart speed to spherical projectile at various impact velocities for damage studies. Crater dimensions (diameter and depth) obtained due to impact have been compared with finite element results using commercially available explicit finite element method code LS-DYNA. Strain hardening, high strain rate and thermal softening effect along with damage parameters have been considered using modified Johnson-Cook material model of LS-DYNA. Metallographic analysis has been performed on the indented specimen. This analysis is useful to study failure analysis of gas turbine engine components subjected to domestic object damage of gas turbine engine. </p><p> </p>

OS6-9 Damage Analysis of TBC and Substrate on Serviced Gas Turbine Blades

2006 ◽  
Vol 2006.11 (0) ◽  
pp. 187-188
Author(s):  
Akihiro ITO ◽  
Yukio KAGIYA ◽  
Taiji TORIGOE ◽  
Yoshitaka UEMURA
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Damage Analysis ◽  
Gas Turbine Blades

scholarly journals Low-Order Modeling of Combustion Noise in an Aero-Engine: The Effect of Entropy Dispersion

2017 ◽  
Vol 140 (1) ◽  
Author(s):  
Yasser Mahmoudi ◽  
Andrea Giusti ◽  
Epaminondas Mastorakos ◽  
Ann P. Dowling
Keyword(s):  
Experimental Data ◽  
Turbine Blades ◽  
Wave Dispersion ◽  
Combustion Noise ◽  
Mean Velocity ◽  
Disk Model ◽  
Low Frequencies ◽  
Model Code ◽  
Aero Engine ◽  
Low Order

The present work studies the effect of entropy dispersion on the level of combustion noise at the turbine outlet of the Rolls-Royce ANTLE aero-engine. A new model for the decay of entropy waves, based on modeling dispersion effects, is developed and utilized in a low-order network model of the combustor (i.e., LOTAN code that solves the unsteady Euler equations). The proposed model for the dispersion of entropy waves only requires the mean velocity field as an input, obtained by Reynolds-averaged Navier–Stokes (RANS) computations of the demonstrator combustor. LOTAN is then coupled with a low-order model code (LINEARB) based on the semi-actuator disk model that studies propagation of combustion noise through turbine blades. Thus, by combining LOTAN and LINERAB, the combustion noise and its counterparts, direct and indirect noise, generated at the turbine exit are predicted. In comparison with experimental data, it is found that without the inclusion of entropy dispersion, the level of combustion noise at the turbine exit is overpredicted by almost 2 orders of magnitude. The introduction of entropy dispersion in LOTAN results in a much better agreement with the experimental data, highlighting the importance of entropy wave dispersion for the prediction of combustion noise in real engines. In more detail, the agreement with the experiment for high and low frequencies was very good. At intermediate frequencies, the experimental measurements are still overpredicted; however, the predicted noise is much smaller compared to the case without entropy dispersion. This discrepancy is attributed to (i) the role of turbulent mixing in the overall decay of the entropy fluctuations inside the combustor, not considered in the model developed for the decay of entropy waves, and (ii) the absence of a proper model in LINEARB for the decay of entropy waves as they pass through the turbine blade rows. These are areas that still need further development to improve the prediction of low-order network codes.

Low-Order Modelling of Combustion Noise in an Aero-Engine: The Effect of Entropy Dispersion

2017 ◽  
Author(s):  
Yasser Mahmoudi ◽  
Andrea Giusti ◽  
Epaminondas Mastorakos ◽  
Ann P. Dowling
Keyword(s):  
Experimental Data ◽  
Turbine Blades ◽  
Wave Dispersion ◽  
Combustion Noise ◽  
Mean Velocity ◽  
Disk Model ◽  
Low Frequencies ◽  
Model Code ◽  
Aero Engine ◽  
Low Order

The present work studies the effect of entropy dispersion on the level of combustion noise at the turbine outlet of the Rolls-Royce ANTLE aero-engine. A new model for the decay of entropy waves, based on modelling dispersion effects, is developed and utilised in a low-order network model of the combustor (i.e. LOTAN code that solves the unsteady Euler equations). The proposed model for the dispersion of entropy waves only requires the mean velocity field as an input, obtained by RANS computations of the demonstrator combustor. LOTAN is then coupled with a low order model code (LINEARB) based on the semi-actuator disk model that studies propagation of combustion noise through turbine blades. Thus, by combining LOTAN and LINERAB we predict the combustion noise and its counterparts, direct and indirect noise, generated at the turbine exit. In comparison with experimental data it is found that without the inclusion of entropy dispersion, the level of combustion noise at the turbine exit is over-predicted by almost two orders of magnitude. The introduction of entropy dispersion in LOTAN results in much better agreement with the experimental data, highlighting the importance of entropy wave dispersion for the prediction of combustion noise in real engines. In more detail, the agreement with the experiment for high and low frequencies was very good. At intermediate frequencies the experimental measurements are still over-predicted, however the predicted noise is much smaller compared to the case without entropy dispersion. This discrepancy is attributed to (i) the role of turbulent mixing in the overall decay of the entropy fluctuations inside the combustor, not considered in the model developed for the decay of entropy waves, and (ii) the absence of a proper model in LINEARB for the decay of entropy waves as they pass through the turbine blade rows. These are areas that still need further development to improve the prediction of low-order network codes.

Reliable thermosonic inspection of aero engine turbine blades

2010 ◽  
Vol 52 (9) ◽  
pp. 488-493 ◽  
Author(s):  
G Bolu ◽  
A Gachagan ◽  
G Pierce ◽  
G Harvey
Keyword(s):  
Turbine Blades ◽  
Aero Engine

Advanced Intermetallic TiAl Alloys

2016 ◽  
Vol 879 ◽  
pp. 113-118 ◽  
Author(s):  
Helmut Clemens ◽  
Svea Mayer
Keyword(s):  
Environmental Politics ◽  
Turbine Blades ◽  
Mechanical Processing ◽  
Tial Alloys ◽  
Precision Casting ◽  
Automotive Engines ◽  
High Temperature Mechanical Properties ◽  
Aero Engine ◽  
Novel Approaches ◽  
Multi Phase

Challenging issues concerning energy efficiency and environmental politics require novel approaches to materials design. A recent example with regard to structural materials is the emergence of lightweight intermetallic TiAl alloys. Their excellent high-temperature mechanical properties, low density, and high stiffness constitute a profile perfectly suitable for their application as advanced aero-engine turbine blades or as turbocharger turbine wheels in next-generation automotive engines. Advanced so-called 3rd generation TiAl alloys, such as the TNM alloy described in this paper, are complex multi-phase alloys which can be processed by ingot or powder metallurgy as well as precision casting methods. Each process leads to specific microstructures which can be altered and optimized by thermo-mechanical processing and/or subsequent heat treatments.

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