Gas Turbine Rotor Flange Integrating Labyrinth Seal and Balancing
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Solution Overview
Problem
Gas turbine engines face challenges in sealing cavities between turbine rotors and maintaining rotor balance, which affect air pressure distribution and engine performance.
Innovation Solution
The integration of a labyrinth seal assembly and a rotor balancing structure within the same rotor flange of a gas turbine engine, utilizing a balancing flange with counterweights for rotational balance and a labyrinth seal with radially extending seal fins for sealing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate seal assembly and balancing structure are used, then sealing and balancing functions are achieved, but device complexity and axial space increase
Solution Approach 1:
The patent combines the seal assembly and rotor balancing structure into a single integrated rotor flange component. The seal fins are directly formed on the rotor flange, eliminating the need for separate seal assemblies and reducing overall structural complexity while maintaining both sealing and balancing functions.
Solution Approach 2:
The rotor flange is designed to serve multiple functions simultaneously: it provides structural support for the rotor, incorporates seal fins for sealing cavities, and includes balancing elements for rotational balance. This multi-functional design reduces the number of separate components needed in the turbine assembly.
2Reliability
If separate seal assembly and balancing structure are used, then sealing and balancing functions are achieved, but axial space consumption increases
Solution Approach 1:
The seal assembly and balancing structure are merged into a single integrated component on the rotor flange, eliminating the axial space that would be required for separate assemblies. The seal fins and balancing elements are positioned on the same radial plane, minimizing axial dimension requirements.
Solution Approach 2:
The design transitions from axial stacking of separate seal and balancing components to a radial arrangement where both functions are achieved on the same axial plane. The seal fins extend radially from the rotor flange, allowing sealing and balancing to occur simultaneously without increasing axial space consumption.
3Reliability
If traditional seal assembly is used, then sealing is achieved, but radial position optimization is limited
Solution Approach 1:
The seal fins are designed with adjustable positioning capabilities on the rotor flange, allowing their radial position to be optimized for different operating conditions. The number, length, and angular distribution of seal fins can be varied to adapt to different sealing requirements and radial clearance conditions.
Solution Approach 2:
Different sections of the rotor flange can have seal fins with varying properties (length, angle, spacing) to optimize sealing at specific radial locations. This allows targeted sealing effectiveness at different radii while maintaining overall system performance.
Data Source
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AI summary
A rotor (32) of a gas turbine engine (10) includes a rotor hub (38) rotatable about a rotor central axis (22), a plurality of rotor blades (36) extending radially outwardly from the rotor hub, and a rotor flange (42) extending axially from the rotor hub. The rotor flange at least partially defines a seal assembly (44) configured to seal between the rotor and a static structure (50) of the gas turbine engine, and a rotor balancing structure (60) configured to rotationally balance the rotor. A turbine (30) of the gas turbine engine includes a turbine static structure (50) and the rotor, wherein the rotor is a turbine rotor. The gas turbine engine includes a combustor (56) configured to combust a mixture of air and fuel and a turbine assembly comprising the rotor, wherein the rotor is a turbine rotor configured to be driven to rotate about an engine central axis by a flow of combustion gases from the combustor.