Thermo-structural design of a Ceramic Matrix Composite wing leading edge for a re-entry vehicle

2019 ◽  
Vol 207 ◽  
pp. 264-272 ◽  
Author(s):  
Michele Ferraiuolo ◽  
Roberto Scigliano ◽  
Aniello Riccio ◽  
Emanuele Bottone ◽  
Marco Rennella
Keyword(s):  
Matrix Composite ◽  
Structural Design ◽  
Ceramic Matrix Composite ◽  
Leading Edge ◽  
Ceramic Matrix ◽  
Composite Wing

scholarly journals Investigating the Thermo-Mechanical Behavior of a Ceramic Matrix Composite Wing Leading Edge by Sub-Modeling Based Numerical Analyses

Computation ◽  
2020 ◽  
Vol 8 (2) ◽  
pp. 22 ◽  
Author(s):  
Michele Ferraiuolo ◽  
Concetta Palumbo ◽  
Andrea Sellitto ◽  
Aniello Riccio
Keyword(s):  
Mechanical Behavior ◽  
Matrix Composite ◽  
Thermal Protection ◽  
Ceramic Matrix Composite ◽  
Leading Edge ◽  
Ceramic Matrix ◽  
Thermal Protection Systems ◽  
Protection Systems ◽  
Very High ◽  
Composite Wing

The thermo-structural design of the wing leading edge of hypersonic vehicles is a very challenging task as high gradients in thermal field, and hence high thermal stresses, are expected. Indeed, when employing passive hot structures based thermal protection systems, very high temperatures (e.g., 1400 °C) are expected on the external surface of the wing leading edge, while the internal structural components are required to not exceed a few hundred degrees Celsius (e.g., 400 °C) at the interface with the internal cold structure. Hence, ceramic matrix composites (CMC) are usually adopted for the manufacturing of the external surface of the wing leading edge since they are characterized by good mechanical properties at very high temperatures (up to 1900 °C) together with an excellent thermal shock resistance. Furthermore, the orthotropic behavior of these materials together with the possibility to tailor their lamination sequence to minimize the heat transferred to internal components, make them very attractive for hot structure based thermal protection systems applications. However, the numerical predictions of the thermo-mechanical behavior of such materials, taking into account the influence of each ply (whose thickness generally ranges between 0.2 and 0.3 mm), can be very expensive from a computational point of view. To overcome this limitation, usually, sub-models are adopted, able to focus on specific and critical areas of the structure where very detailed thermo-mechanical analyses can be performed without significantly affecting the computational efficiency of the global model. In the present work, sub-modeling numerical approaches have been adopted for the analysis of the thermo-mechanical behavior of a ceramic matrix composite wing leading edge of a hypersonic vehicle. The main aim is to investigate the feasibility, in terms of computational efficiency and accuracy of results, in using sub-models for dimensioning complex ceramic matrix components. Hence, a comprehensive study on the size of sub-models and on the choice of their boundaries has been carried out in order to assess the advantages and the limitations in approximating the thermo-mechanical behavior of the investigated global ceramic matrix composite component.

Experimental and Numerical Investigation of Environmental Barrier Coated Ceramic Matrix Composite Turbine Airfoil Erosion

2018 ◽  
Vol 141 (3) ◽  
Author(s):  
Yoji Okita ◽  
Yousuke Mizokami ◽  
Jun Hasegawa
Keyword(s):  
Matrix Composite ◽  
Gas Turbines ◽  
Ceramic Matrix Composite ◽  
Leading Edge ◽  
Ceramic Matrix ◽  
Test Facility ◽  
Surface Erosion ◽  
Erosion Model ◽  
Environmental Barrier ◽  
Higher Temperature

Ceramic matrix composite (CMC) have higher temperature durability and lower density property compared to nickel-based super-alloys which so far have been widely applied to hot section components of aero-engines/gas turbines. One of promising CMC systems, SiC–SiC CMC is able to sustain its mechanical property at higher temperature, though it inherently needs environmental barrier coating (EBC) to avoid oxidation. There are several requirements for EBC. One of such critical requirements is its resistance to particle erosion, whereas this subject has not been well investigated in the past. The present work presents the results of a combined experimental and numerical research to evaluate the erosion characteristics of CMC + EBC material developed by IHI. First, experiments were carried out in an erosion test facility using 50 μm diameter silica as erosion media under typical engine conditions with velocity of 225 m/s, temperature of 1311 K, and impingement angles of 30, 60, and 80 deg. The data displayed brittle erosion mode in that the erosion rate increased with impact angles. Also, it was verified that a typical erosion model, Neilson–Gilchrist model, can reproduce the experimental behavior fairly well if its model constants were properly determined. The numerical method solving particle-laden flow was then applied with the tuned erosion model to compute three dimensional flow field, particle trajectories, and erosion profile around a generic turbine airfoil to assess the erosion characteristics of the proposed CMC + EBC material when applied to airfoil. The trajectories indicated that the particles primarily impacted the airfoil leading edge and the pressure surface. Surface erosion patterns were predicted based on the calculated trajectories and the experimentally based erosion characteristics.

scholarly journals Sustainable Machining of Cf/SiC Ceramic Matrix Composite Using Green Cutting Fluids

Procedia CIRP ◽  
2021 ◽  
Vol 98 ◽  
pp. 151-156
Author(s):  
Shyam ◽  
M. Shanmuka Srinivas ◽  
Kishor Kumar Gajrani ◽  
A. Udayakumar ◽  
M. Ravi Sankar
Keyword(s):  
Matrix Composite ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Cutting Fluids ◽  
Sustainable Machining ◽  
Sic Ceramic

Effect of abrasive waterjet machining on LaPO4/Y2O3 ceramic matrix composite

2017 ◽  
Vol 54 (2) ◽  
pp. 205-214 ◽  
Author(s):  
K. Balamurugan ◽  
M. Uthayakumar ◽  
S. Sankar ◽  
U. S. Hareesh ◽  
K. G. K. Warrier
Keyword(s):  
Matrix Composite ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Abrasive Waterjet ◽  
Abrasive Waterjet Machining ◽  
Waterjet Machining
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