Ceramic Matrix Composite Materials for Engine Exhaust Systems on Next-Generation Vertical Lift Vehicles

Journal of Engineering for Gas Turbines and Power - Tập 140 Số 10 - 2018
Michael Walock1, Vann Heng2, Andy Nieto1, Anindya Ghoshal3, Muthuvel Murugan1, Dan Driemeyer4
1U.S. Army Research Laboratory, Aberdeen Proving Ground, MD 21005 e-mail:
2The Boeing Company, Huntington Beach, CA 92647 e-mail:
3U.S. Army Research Laboratory, Aberdeen Proving Ground, MD 21005 e-mails: ;
4The Boeing Company, St. Louis, MO 63145 e-mail:

Tóm tắt

Future gas turbine engines will operate at significantly higher temperatures (∼1800 °C) than current engines (∼1400 °C) for improved efficiency and power density. As a result, the current set of metallic components (titanium-based and nickel-based superalloys) will be replaced with ceramics and ceramic matrix composites (CMCs). These materials can survive the higher operating temperatures of future engines at significant weight savings over the current metallic components, i.e., advanced ceramic components will facilitate more powerful engines. While oxide-based CMCs may not be suitable candidates for hot-section components, they may be suitable for structural and/or exhaust components. However, a more thorough understanding of the performance under relevant environment of these materials is needed. To this end, this work investigates the high-temperature durability of a family of oxide–oxide CMCs (Ox–Ox CMCs) under an engine-relevant environment. Flat Ox–Ox CMC panels were cyclically exposed to temperatures up to 1150 °C, within 240 m/s (∼0.3 M) gas flows and hot sand impingement. Front and backside surface temperatures were monitored by a single-wavelength (SW) pyrometer and thermocouple, respectively. In addition, an infrared (IR) camera was used to evaluate the damage evolution of the samples during testing. Flash thermography nondestructive evaluation (NDE) was used to elucidate defects present before and after thermal exposure.

Từ khóa


Tài liệu tham khảo

1999, Potential Application of Ceramic Matrix Composites to Aero-Engine Components, Compos. Part A, 30, 489, 10.1016/S1359-835X(98)00139-0

2013, Shaping the Future of Ceramics for Aerospace Applications, Int. J. Appl. Ceram. Technol., 10, 389, 10.1111/ijac.12069

1998, Chapter 7: Ceramic Matrix Composites, Composite Materials, 212, 10.1007/978-1-4757-2966-5_7

2017, Fibre-Reinforced Multifunctional SiC Matrix Composite Materials, Int. Mater. Rev., 62, 117, 10.1080/09506608.2016.1213939

Army Capabilities Integration Center, 2017, The US Army Functional Concept for Movement and Maneuver, 2020-2040, TRADOC PAM 525-3-6

Army Capabilities Integration Center, 2017, The Warfighters' Science and Technology Needs, Report

Army Research Laboratory,, 2002, Composite Materials Handbook, Volume 5. Ceramic Matrix Composites

NASA Aeronautics Research Mission Directorate,, 2017, Strategic Implementation Plan, Report

BusinessWire, 2017, GE Aviation Building U.S. Blueprint to Industrialize CMCs

Aviation Week Network, 2015, GE Details Sixth-Generation Adaptive Fighter Engine Plan

Rolls-Royce, 2016, Rolls-Royce Expands Aerospace Research Center in Southern California

2016, Ceramic Matrix Composites and Carbon Matrix Composities: Technologies and Global Markets

1995, Oxide Ceramic Matrix/Oxide Fibre Woven Fabric Composites Exhibiting Fracture Behavior, Composites, 26, 175, 10.1016/0010-4361(95)91380-N

1998, Processing and Performance of an All-Oxide Ceramic Composite, J. Am. Ceram. Soc., 81, 2077, 10.1111/j.1151-2916.1998.tb02590.x

2017, Microstructure and Mechanical Behavior of a Nextel610/Alumina Weak Matrix Composite Subjected to Tensile and Compressive Loadings, J. Eur. Ceram. Soc., 37, 2919, 10.1016/j.jeurceramsoc.2017.02.042

Kiser, J. D., Bansal, N. P., Szelagowski, J., Sokhey, J., Heffernan, T., Clegg, J., Pierluissi, A., Riedell, J., Wyen, T., Atmur, S., and Ursic, J., 2015, “Oxide/Oxide Ceramic Matrix Composite (CMC) Exhaust Mixer Development in the NASA Environmentally Responsible Aviation (ERA) Project,” ASME Paper No. GT2015-43593.10.1115/GT2015-43593

2015, Assessment of Three Oxide/Oxide Ceramic Matrix Composites: Mechanical Performance and Effects of Heat Treatments, Compos. Part A, 68, 19, 10.1016/j.compositesa.2014.09.013

2015, Mechanical Behavior of a Notched Oxide/Oxide Ceramic Matrix Composite in Combustion Environment: Experiments and Simulations, Compos. Struct., 127, 77, 10.1016/j.compstruct.2015.02.040

2015, Mechanical Characterization of a Fiber Reinforced Oxide/Oxide Ceramic Matrix Composite, J. Eur. Ceram. Soc., 35, 4513, 10.1016/j.jeurceramsoc.2015.08.032

2018, Molten Particulate Impact on Tailored Thermal Barrier Coatings for Gas Turbine Engine, ASME J. Eng. Gas Turbines Power, 140, 022601, 10.1115/1.4037599

Murugan, M., Ghoshal, A., Walock, M., Nieto, A., Bravo, L., Barnett, B., Pepi, M., Swab, J., Pegg, R. T., Rowe, C., Zhu, D., and Kerner, K., 2017, “Microstructure Based Material-Sand Particulate Interactions and Assessment of Coatings for High Temperature Turbine Blades,” ASME Paper No. GT2017-64051.10.1115/GT2017-64051

2017, Failure Mechanisms of Calcium Magnesium Aluminum Silicate Affected Thermal Barrier Coatings, J. Am. Ceram. Soc., 100, 2679, 10.1111/jace.14711

2016, Interaction Between Ceramic Powder and Molten Calcia-Magnesia-Alumino-Silicate (CMAS) Glass, and Its Implication on CMAS-Resistant Thermal Barrier Coatings, Scr. Mater., 112, 118, 10.1016/j.scriptamat.2015.09.027

2011, Jet Engine Coatings for Resisting Volcanic Ash Damage, Adv. Mater., 23, 2419, 10.1002/adma.201004783

1988, The Mechanics of the Coin-Tap Method of Non-Destructive Testing, J. Sound Vib., 122, 299, 10.1016/S0022-460X(88)80356-0

Thông tin
Thông tin xuất bản

Journal of Engineering for Gas Turbines and Power

Tập 140 Số 10

Thông tin tác giả