Hybrid CMC Metallic Nozzle Segment Assembly for Gas Turbine
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Solution Overview
Problem
Gas turbine engine nozzle vanes made from ceramic matrix composite (CMC) materials face durability challenges due to low mechanical loading capabilities, which existing designs have not adequately addressed.
Innovation Solution
A hybrid nozzle segment assembly featuring a CMC fairing with a metallic strut and secondary vanes, providing increased mechanical support and reduced cooling flow requirements, while maintaining high temperature capabilities and reducing weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If CMC materials are used for nozzle vanes to increase high temperature capabilities, then temperature resistance is improved, but mechanical loading capability deteriorates
Solution Approach 1:
The nozzle vane assembly uses a hybrid composite structure combining CMC material for the fairing (providing high temperature resistance) with metallic materials for struts and secondary vanes (providing mechanical strength). This composite approach allows each material to contribute its superior properties, resolving the contradiction between temperature resistance and mechanical loading capability.
2Weight of moving object
If CMC-based nozzle vanes are used to reduce weight, then weight is reduced, but durability under mechanical loading deteriorates
Solution Approach 1:
The design applies different materials to different parts of the nozzle vane assembly based on local requirements: CMC material is used for the fairing where weight reduction and heat resistance are critical, while metallic materials are used for struts and secondary vanes where mechanical strength and durability are paramount. This localized material selection optimizes both weight and durability.
3Strength
If conventional metallic nozzle vanes are used, then mechanical loading capability is maintained, but weight increases and cooling flow requirements increase
Solution Approach 1:
The hybrid CMC-metallic composite structure maintains the mechanical loading capability of conventional metallic vanes through the metallic struts and secondary vanes, while simultaneously reducing overall weight through the use of lighter CMC fairing material, thus resolving both weight and strength requirements.
Data Source
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AI summary
A nozzle segment assembly 102 for a gas turbine engine 10 may generally include inner and outer ring support segments 116 and a nozzle fairing 104 positioned between the inner and outer ring support segments 114, 116. The nozzle fairing may be formed from a ceramic matrix composite (CMC) material and may include both an outer endwall 110 and an inner endwall 108. In addition, the nozzle fairing may include a strut vane 106 extending between the inner and outer endwalls 108, 110. The nozzle segment assembly may also include a metallic strut extending through the strut vane between the outer and inner ring supports and at least one secondary vane 112 configured to be received through at least one of the outer endwall 110 or the inner endwall 108 of the nozzle fairing 104 such that the at least one secondary vane extends between the inner and outer endwalls at a location adjacent to the strut vane.