Oxide Ceramic Matrix Composite Materials for Aero-Engine Applications: A Literature Review

Abstract

The development of aircraft gas turbine engines has extensively been required for the development of advanced materials. This complex development process is however justified by the system-level benefits in terms of reduced weight, higher temperature capability, and/or reduced cooling, each of which increases efficiency. This is where high-temperature ceramics have made considerable progress and ceramic matrix composites (CMCs) are in the foreground. CMCs are classified into non-oxide and oxide-based ones. Both families have material types that have a high potential for use in high-temperature propulsion applications. Typical oxide-based ones are based on an oxide fiber and oxide matrix (Ox-Ox). Some of the most common oxide subcategories, are alumina, beryllia, ceria, and zirconia ceramics. Such matrix composites are used for example in combustion liners of gas turbine engines and exhaust nozzles. However, until now a thorough study on the available oxide-based CMCs for such applications has not been presented. This paper focus on assessing a literature survey of the available oxide ceramic matrix composite materials in terms of mechanical and thermal properties.

Mechanical and Thermal Performance of Ceramic and Nickel Superalloys Composites for Gas Turbine Blade Applications

“…These materials can operate with no additional cooling at temperatures of up to 1200°C, which is slightly higher than what coated nickel alloy systems can achieve. To sustain long-term stability at the highest temperatures in an oxidizing atmosphere, uncooled turbine applications will require an oxide-oxide ceramic material system [13]. Alumina fibres in an alumina matrix are an early example of such a system.…”

“…Two oxide and one non-oxide CMC materials have been selected for the present study (Table 1). They were selected based on the approach presented by the authors in [12,13]. The criteria for the material selection considered the aerospace applications' material requirements with regards to their mechanical, physical, and chemical properties, such as high strength, stiffness, fatigue durability, damage tolerance, low density, high thermal stability, high corrosion, and oxide resistance.…”

“…The criteria for the material selection considered the aerospace applications' material requirements with regards to their mechanical, physical, and chemical properties, such as high strength, stiffness, fatigue durability, damage tolerance, low density, high thermal stability, high corrosion, and oxide resistance. Commercial criteria such as cost, servicing, and manufacturability were also considered [13,14].…”

Literature Review of Fatigue Life Performance of Ceramic Materials

“…Ceramic materials are known for their high temperature, corrosion, and oxidation resistance, but are also known for their low toughness and strength when high loads are applied. That is why further development has been researched and achieved for ceramic materials by reinforcing them with different kinds of fibres and substrates, enhancing their toughness, strength, and hardness [29,44].…”

Ceramic Matrix Composites: Classifications, Manufacturing, Properties, and Applications

“…This restriction is attributed to the degradation of mechanical performance in the oxide reinforcing fibers, leading to reduced tensile strength values in the composite [40]. As illustrated in Figure 3, O-CMCs show a range of pairings; these mixtures fall into two categories: oxide/oxide matrices, in which the base material and filler/reinforcement are both oxides, and oxide/non-oxide matrices, in which the base material is an oxide but the filler/reinforcement is a non-oxide [38,41].…”