Combustor-to-Vane Seal Assembly for Rocking and Twist Leakage
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Solution Overview
Problem
Existing sealing arrangements between combustors and turbine sections in gas turbine engines often fail to maintain adequate contact, leading to leakage due to rocking and twisting during operation.
Innovation Solution
A brush seal assembly with a backing plate, retaining ring, and bristles extending axially between the inner shell and the first vane stage, combined with a conformal seal and hard seal, which wear down to form a secure seal with the vane stage, and a single mounting point to accommodate structural movement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional sealing arrangements are used between combustor and turbine section, then the structure is simple, but adequate contact and sealing are not maintained during operation due to rocking and twisting
Solution Approach 1:
The seal assembly is divided into multiple functional segments: a hard seal portion for primary sealing contact, a brush seal portion for secondary sealing and gap filling, and a conformal seal portion for adapting to surface variations. Each segment performs a specific sealing function, allowing the system to maintain reliable sealing under operational movements while keeping each individual component relatively simple in design.
2Reliability
If multiple seal types are combined to improve sealing reliability, then sealing performance is improved, but device complexity increases
Solution Approach 1:
The patent merges three different seal types (hard seal, brush seal, and conformal seal) into a single integrated seal assembly that functions as one unified component. The hard seal portion, brush seal portion, and conformal seal portion are combined in a way that they work together synergistically, providing multiple sealing mechanisms simultaneously while being installed and maintained as a single assembly unit.
Solution Approach 2:
The seal assembly utilizes composite construction by combining different sealing mechanisms (rigid hard seal, flexible brush seal, and adaptive conformal seal) into one hybrid system. Each material type contributes its unique properties: the hard seal provides structural stability and primary contact, the brush seal provides flexibility and gap sealing, and the conformal seal provides surface adaptation, creating a composite sealing solution that overcomes the limitations of individual seal types.
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 provides improved sealing by maintaining contact and accommodating structural movement, reducing leakage and ensuring effective sealing between the combustor and turbine sections.
Implementation Method 1
the conformal seal includes a wearing end portion extending axially aft from the conformal seal and configured to wear down during initial operation of the gas turbine engine to form the first seal with the forward face of the first vane stage
Implementation Method 2
the brush seal includes a brush seal backing plate, retaining ring, and a plurality of bristles retained between the brush seal backing plate and the retaining ring. The plurality of bristles extend axially between the second shell and the forward face of the first vane stage
Data Source
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AI summary
A gas turbine engine (10) includes a turbine section (18) including a first vane stage (74). The gas turbine engine (10) further includes a combustor (50) disposed forward of the first vane stage (74). The combustor (50) includes a combustion chamber (56) in fluid communication with the first vane stage (74). The combustion chamber (56) is radially defined between a first shell (52) and a second shell (54). The first shell (52) includes a first seal assembly (88) at an aft end (60) of the first shell (52). The first seal assembly (88) includes a conformal seal (90) forming a first seal between the first shell (52) and a forward face (78) of the first vane stage (74). The second shell (52) includes a second seal assembly (104) at an aft end (68) of the second shell (54). The second seal assembly (104) includes a brush seal (110) forming a second seal between the second shell (54) and the forward face (82) of the first vane stage (74).