Turbine Engine Seal Support Assembly for Dynamic Rotor Clearance
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing seal systems in gas turbine engines face challenges in maintaining a positive radial clearance between seal members and the rotor shaft under varying operating conditions, leading to wear and potential rubs during low delta pressure conditions and transients.
Innovation Solution
A seal support assembly utilizing a spring arrangement and a lip assembly with angled seal segments that accommodate radial movement, allowing for dynamic adjustment of clearance based on pressure differentials to prevent airflow leakage and minimize rubs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a fixed seal system is used, then the structure is simple, but the seal cannot accommodate radial movement and pressure changes, leading to wear and rubs
Solution Approach 1:
The seal support assembly incorporates a spring arrangement that enables dynamic adjustment of seal member position in response to pressure differentials. The spring allows the seal support to move radially, accommodating rotor shaft vibrations and radial movements while maintaining consistent sealing contact, thereby preventing wear and rubs without requiring an overly complex system.
Solution Approach 2:
The spring arrangement changes the physical state of the seal support assembly from static to dynamically adjustable. By utilizing elastic deformation of the spring, the system adapts its radial position based on operating conditions (pressure differentials), allowing the seal to maintain optimal clearance and contact pressure across varying operational scenarios.
2Reliability
If the seal members are kept at a fixed distance from the rotor shaft, then the manufacturing is simple, but wear and rubs occur during low delta pressure conditions and transients
Solution Approach 1:
The spring arrangement enables the seal support assembly to dynamically adjust its radial position based on pressure differentials. During low delta pressure conditions and transients, the spring allows greater radial movement, maintaining positive clearance and preventing seal members from contacting the rotor shaft, thereby eliminating wear and rubs while remaining manufacturable.
3Loss of energy
If the seal members are positioned close to the rotor shaft to prevent airflow leakage, then the sealing efficiency is improved, but the risk of rubs increases during vibrations and transients
Solution Approach 1:
The spring arrangement creates a dynamic sealing system that maintains optimal clearance between seal members and the rotor shaft. During vibrations and transients, the spring allows radial movement that prevents contact and rubs, while under normal operating conditions, the seal members remain positioned close enough to the rotor shaft to effectively prevent airflow leakage, thus resolving the contradiction between sealing efficiency and rub prevention.
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 effectively maintains a tight clearance with the rotor shaft, reducing wear and preventing airflow leakage while accommodating vibrations and pressure changes, enhancing the operational efficiency and durability of the seal system.
Implementation Method 1
A seal support assembly utilizing a spring arrangement and a lip assembly with angled seal segments that accommodate radial movement
Implementation Method 2
the first seal segment having a seal face configured to form a fluid bearing with the rotor
Data Source
AI summary
A turbine engine is provided. The turbine engine includes: a rotor; a stator having a carrier; a seal support assembly coupled to the carrier; and a seal assembly disposed between the rotor and the stator and supported by the seal support assembly, the seal assembly defining a high pressure side and a low pressure side and including a plurality of seal segments, the plurality of seal segments having a first seal segment, the first seal segment having a seal face configured to form a fluid bearing with the rotor, a lip assembly, and a body, the lip assembly positioned on the high pressure side, the lip assembly including a seal lip having a high pressure surface defining a first angle with an axial direction and a low pressure surface defining a second angle with the axial direction, the second angle being greater than the first angle.