Annular Assembly Sealing for Turbine Deflector Leakage
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Solution Overview
Problem
In turbomachines, particularly low-pressure turbines, existing sealing solutions fail to effectively prevent leakage of hot combustion gases between thermal deflector segments and crown segments, leading to potential damage and inefficiency due to the thinness of current deflector designs, which limits the use of traditional tabs for sealing.
Innovation Solution
An annular assembly with circumferentially segmented rings and sealing members comprising first and second circumferential sealing means, including wall elements and interconnected plates, provides a robust and error-proof seal between deflector and crown segments, preventing gas leakage and facilitating assembly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional tabs are used for sealing between crown segments, then sealing is provided, but the solution is not feasible due to the thinness of the deflector
Solution Approach 1:
The sealing solution transitions from a two-dimensional tab approach to a three-dimensional L-shaped configuration that engages both the crown segment and deflector segment in perpendicular directions, enabling effective sealing without requiring thick deflector structure
Solution Approach 2:
The L-shaped sealing member acts as an intermediary element that bridges the gap between the crown segment and deflector segment, providing a mechanical interface that achieves sealing without directly modifying the thin deflector structure
2Weight of moving object
If the deflector is made thin to reduce weight, then weight reduction is achieved, but sealing capability is compromised
Solution Approach 1:
The sealing system is segmented into distinct functional elements: the L-shaped sealing member that interfaces with both crown and deflector segments, allowing the deflector to remain thin while sealing functionality is distributed to dedicated sealing components
Solution Approach 2:
The sealing capability is concentrated at specific locations where the L-shaped sealing members engage the crown and deflector segments, rather than requiring the entire deflector structure to be thick, achieving local sealing reinforcement without global weight penalty
3Reliability
If sealing members are added between deflector segments, then gas leakage is prevented, but assembly complexity increases
Solution Approach 1:
The L-shaped sealing member merges two sealing functions into a single integrated component: one arm seals against the crown segment while the other arm seals between deflector segments, reducing the number of separate parts and simplifying assembly
Data Source
AI summary
The present document relates to an annular assembly for a turbomachine turbine, in particular of an aircraft, said annular assembly extending about a longitudinal axis X and comprising: a distributor fixed to an external casing; a bladed disc mounted so as to rotate inside the external casing; said bladed disc being surrounded by a circumferentially segmented ring carried by the external casing and formed by a crown arranged radially on the outside of the bladed disc and by an annular deflector that is carried by an upstream edge of the crown and extends radially towards the inside from said upstream edge of the crown; characterized in that it comprises sealing members (56) between two circumferentially adjacent ring segments, these sealing members (56) comprising first circumferential sealing means (58) between two circumferentially consecutive deflector segments.