Gas Turbine Vane Ring Arrangement for Axial Length Reduction
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Solution Overview
Problem
Existing gas turbine engine vane arrangements lack effective reinforcement and sealing mechanisms, particularly in the mid-turbine frame, which can lead to reduced engine compactness and power density due to the need for multiple rings and discrete vanes.
Innovation Solution
An annular vane pack arrangement with a ring secured around the vanes, extending proud of their axial end, provides structural reinforcement and sealing through mechanical elements like brazing, welding, or interference fits, and interlocking features to prevent axial movement and ensure a seal with adjacent rotating components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If multiple discrete rings are used to secure vanes in the mid-turbine frame, then the vanes are reinforced and secured, but the axial length of the turbine section increases and power density decreases
Solution Approach 1:
The patent combines multiple discrete rings into a single integrated ring structure that performs both reinforcement and sealing functions. The ring is configured with an inner diameter less than the outer diameter of the vane pack, allowing it to extend radially outward from the vanes while maintaining structural integrity and providing sealing surfaces, thereby eliminating the need for multiple separate rings and reducing axial length.
2Ease of manufacture
If discrete vanes are used in the mid-turbine frame, then the vane pack can be assembled, but the structural integrity and sealing efficiency are reduced
Solution Approach 1:
The patent employs a composite structure where discrete vanes are secured to a continuous ring structure. The ring provides a unified structural backbone that enhances overall integrity, while the vanes maintain their individual functional characteristics. This composite arrangement combines the advantages of modular assembly with the strength of a continuous structure.
3Ease of manufacture
If the ring is spaced from the rotating blade pocket, then assembly is simplified, but sealing efficiency at the inner flow path is reduced
Solution Approach 1:
The ring structure serves as an intermediary element that bridges the static vane pack and the rotating blade pocket. By positioning the ring such that its outer surface defines an inner flow path pocket that receives the rotating blade platform, the patent creates a sealing interface without requiring the ring to be directly spaced from the pocket, thereby maintaining both assembly simplicity and sealing efficiency.
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
This configuration enhances the structural integrity and sealing efficiency of the vane pack, reducing the axial length of the turbine section and increasing power density while maintaining engine compactness.
Implementation Method 1
The ring is secured to the vanes by mechanical elements. The mechanical elements include at least one of a braze, a weld and fasteners.
Implementation Method 2
The ring is secured to the vanes by mechanical elements. The mechanical elements include at least one of a braze, a weld and fasteners.
Implementation Method 3
The ring is secured to the vanes by an interference fit.
Data Source
AI summary
A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.