Ceramic Matrix Full Hoop Blade Track for Low-Leakage Turbine Sealing
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Solution Overview
Problem
Design and manufacture of blade tracks for gas turbine engines from ceramic-matrix composite materials pose challenges, particularly in creating full hoop configurations that minimize gas leakage and are scalable for larger engine applications.
Innovation Solution
A full hoop blade track assembly using ceramic-matrix composite materials with a joint of woven or braided reinforcement fibers, where segments are coupled via a tube of reinforcement fibers co-infiltrated with ceramic-containing matrix material, and a method involving chemical vapor infiltration and melt infiltration to bond the segments together, forming a continuous radially-inward facing surface.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If blade tracks are made from ceramic-matrix composite materials to minimize gas leakage, then sealing performance is improved, but manufacturing complexity increases
Solution Approach 1:
The blade track is divided into multiple segments that can be manufactured separately and then assembled into a complete hoop structure. This segmentation allows for simpler individual component manufacturing while achieving the overall sealing function through proper assembly of ceramic-matrix composite segments with reinforcement fiber joints.
Solution Approach 2:
The blade track utilizes ceramic-matrix composite materials combined with reinforcement fibers to achieve both the sealing performance and structural integrity required. The composite structure provides the necessary mechanical properties and sealing capability while managing the manufacturing complexity through material-level integration.
2Reliability
If a full hoop blade track configuration is used to minimize gas leakage, then sealing performance is improved, but manufacturing scalability worsens
Solution Approach 1:
The full hoop blade track is constructed from multiple segments that can be manufactured using standard sizing equipment and then assembled. This approach enables scalability to larger engine applications by allowing the use of multiple identical or standardized segment designs that can be replicated and assembled to create larger diameter hoop structures.
Solution Approach 2:
The segmented blade track segments are nested or joined together with reinforcement fiber joints to form the complete hoop structure. This nesting approach allows for modular assembly and scalability, where the same segment design can be used in different configurations to accommodate various engine sizes.
3Reliability
If multiple sealing components are used to minimize gas leakage, then sealing performance is improved, but device complexity increases
Solution Approach 1:
The blade track segments with their integrated reinforcement fiber joints combine multiple sealing and structural functions into a unified assembly. This merging reduces the total number of separate sealing components required, as the segmented hoop structure itself provides the sealing function through proper joint design and material selection.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution effectively minimizes gas leakage, reduces the number of sealing components, and allows for scalable manufacturing of larger engine components by forming a continuous full hoop blade track that maintains structural integrity and reduces potential leakage paths.
Implementation Method 1
The tube of reinforcement fibers may further be co-infiltrated with ceramic-containing matrix material along with the first segment and the second segment in order to couple the first segment to the second segment
Implementation Method 2
slurry infiltrating and melt infiltrating the first segment, the second segment, and the joint to bond the first segment, the second segment, and the joint together
Implementation Method 3
The method may include chemical vapor infiltrating ceramic material preforms with silicon-carbide fibers
Data Source
AI summary
A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.