Double Ring Axial Seal for Gas Turbine Compressor Rotor
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Solution Overview
Problem
Sealing axial blades in gas turbine compressor rotors is challenging, leading to undesired leakage, low compressor efficiency, and higher temperatures due to high compressor discharge temperatures, which threaten the structural life of compressor components.
Innovation Solution
A double ring axial sealing design using two rings, where one ring is loaded into a full hoop slot and clocked tangentially to align with each blade, while the second ring is split and compressed to expand into blade grooves, with anti-rotation blades positioned 180 degrees apart to maximize sealing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of stationary object
If axial blades are used to move disk material away from hot gas path, then structural life of compressor components is improved, but sealing becomes challenging leading to undesired leakage
Solution Approach 1:
The sealing system is divided into two separate rings (first ring and second ring) positioned at different locations. Each ring independently seals specific blade grooves, creating multiple sealing zones that collectively prevent leakage while accommodating the axial blade configuration
Solution Approach 2:
The two rings act as intermediary sealing elements between the axial blades and the rotor structure. These rings fill the gap created by the axial blade attachment method, providing a reliable seal without requiring the blades themselves to provide sealing functionality
2Use of energy by moving object
If higher overall pressure ratios are used to achieve better fuel consumption, then fuel efficiency is improved, but compressor discharge temperatures increase threatening structural life
Solution Approach 1:
By segmenting the sealing system into two rings at different positions, the patent creates multiple sealing barriers that prevent hot gas leakage. This allows the system to maintain higher pressure ratios and temperatures necessary for fuel efficiency while preventing localized overheating that would threaten structural integrity
3Reliability
If double ring axial sealing design is implemented, then sealing efficiency is improved, but device complexity increases
Solution Approach 1:
The sealing function is segmented into two independent rings rather than using a single complex sealing mechanism. Each ring is relatively simple in design but together they provide enhanced sealing efficiency, dividing the complexity into manageable, independent components
Solution Approach 2:
The patent combines two simple ring seals to achieve the sealing performance of a more complex single seal. By merging two independent sealing elements positioned at different locations, the system achieves superior sealing efficiency while keeping individual components simple and易于制造
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 double ring axial sealing design effectively limits complexity, tolerances, and gaps, providing a robust seal that maintains rotor integrity and improves sealing efficiency without the use of pastes or viscous substances, leveraging centrifugal forces for axial clamping.
Implementation Method 1
the second ring, which is split in one location similar to the first, does not have a full-hoop grove in the case to load into. It is simply compressed and pressed onto the disk face, and allowed to expand naturally into the blade groves
Implementation Method 2
leveraging centrifugal forces for axial clamping
Data Source
Figure 1
Figure 2~3
Figure 4~5
AI summary
A double ring axial seal (50) for a disk (30) and blade (34) is provided. The disk (30) includes an array of blade slots (32) at a perimeter (31) of the disk (30) configured to receive a root portion (36) of the blade (34). The blade (34) includes a platform (38) located between the root portion (36) and an airfoil (40) extending from the platform (38) opposite the root portion (36). The platform (38) includes a receiver (56) with an overhang (74) proximate the root portion (36). The platform (38) including a hook (60) opposite the receiver (56) proximate the root portion (36). A disk slot (48) is formed on a first side of the disk (30) proximate the array of blade slots (32). A first axial seal ring (54) is coupled with the disk slot (48) and the receiver (56). The first axial seal ring (54) has a cutout (70) proximate an outer perimeter (72) of the first axial seal ring (54). The cutout (70) is sized to receive the overhang (74) of the blade platform (38). The receiver (56) has a contour (64) configured to redirect the first axial seal ring (54) axially toward the blade (34) and disk (30) for axial sealing. A second axial seal ring (58) is inserted into the hook (60) of the blade platform (38) proximate the array of blade slots (32) adjacent a disk face (62) on a side of the disk (30) opposite the first axial seal ring (54). A gas turbine engine compressor rotor is also provided. A process for sealing a gas turbine engine compressor rotor assembly is also provided.