Nested Vane Platform Sealing for Gas Turbine Engines
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Solution Overview
Problem
Current gas turbine engine designs face challenges in efficiently bounding the flowpath and securing vanes, particularly in terms of sealing and cooling, which affect engine efficiency and stress distribution.
Innovation Solution
The design incorporates a platform assembly with radially opposed platforms, an airfoil section, and spar members that extend between these platforms to form a fairing, with the airfoil section and platforms made of ceramic matrix composite material, and includes a baffle for cooling flow, allowing for secure mounting and improved sealing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional metal platforms and vanes are used in gas turbine engines, then structural strength is maintained, but stress concentrations occur and engine efficiency is reduced
Solution Approach 1:
The patent applies ceramic matrix composite (CMC) materials to manufacture platforms and vanes in the gas turbine engine. These CMC components provide both the necessary structural strength to withstand high-temperature gas paths and reduced weight compared to traditional metals, thereby reducing stress concentrations and improving overall engine efficiency while maintaining structural integrity
2Reliability
If vanes are secured to the engine case, then the flowpath is bounded and engine structure is supported, but sealing effectiveness is reduced and stress concentrations increase
Solution Approach 1:
The patent divides the traditional monolithic vane structure into separate modular components: platforms that attach to the engine case and vanes that attach to the platforms. This segmentation allows each component to be optimized independently, improving sealing at the interfaces while distributing and reducing stress concentrations that would occur in a single integrated structure
Solution Approach 2:
The nested arrangement of vanes within the engine case, with vanes positioned within the flowpath bounded by platforms, creates a hierarchical structure where smaller components are contained within larger structures. This nesting approach improves sealing effectiveness by creating multiple sealing interfaces while distributing mechanical stresses across multiple joints rather than concentrating them in a single attachment point
3Temperature
If cooling flows are managed through traditional structures, then thermal management is provided, but the structure becomes complex and manufacturing difficulty increases
Solution Approach 1:
The platform and vane structures serve multiple functions simultaneously: they bound the hot gas path, provide structural support, and manage cooling flows through integrated coolant passages. This multi-functionality eliminates the need for separate cooling system components, reducing overall structural complexity while maintaining effective thermal management
Data Source
Figure 1
Figure 2
Figure 3~7A
AI summary
An assembly for a gas turbine engine (20) according to an example of the present disclosure includes at least one platform (66B, 66C) having a main body (74) extending between a first mate face (76) and a second mate face (78) to establish a gas path surface (66G). The main body has an internal passage (75) extending circumferentially between a first opening (77) along the first mate face (76) and a second opening (79) along the second mate face (78) relative to an assembly axis (LA). A perimeter of the first mate face (76) establishes a first area, a perimeter of the second opening (79) establishes a second area, and the second area is greater than the first area. An airfoil section (62A) extends radially from the at least one platform (66B, 66C).