Gas Turbine Seal Protrusions for Disk Heat Transfer
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Solution Overview
Problem
Gas turbine engines face challenges in efficiently managing heat transfer and temperature control within the turbine section, particularly due to high-temperature gases leaking past turbine blades and exposing the disk periphery to harmful temperatures.
Innovation Solution
The implementation of seals with obliquely angled, chevron-shaped, or elongated ridges on the radially inner surface, which turbulate the cooling fluid to enhance heat transfer from the disk periphery, utilizing a cooling fluid passage with controlled protrusion height, pitch spacing, and channel height to create turbulent flow for effective thermal management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If seals with protrusions are used to enhance heat transfer, then thermal management is improved, but device complexity increases
Solution Approach 1:
The seal structure incorporates protrusions only on the radially inner surface that contacts the cooling fluid, while the radially outer surface remains smooth. This localized modification enhances heat transfer where needed without unnecessarily complicating the entire seal structure.
Solution Approach 2:
The seal is divided into distinct functional surfaces: a smooth radially outer surface and a protrusion-equipped radially inner surface. This segmentation allows each surface to be optimized for its specific function while maintaining overall structural integrity.
2Temperature
If cooling fluid passages with protrusions are implemented, then heat transfer efficiency is improved, but manufacturing complexity increases
Solution Approach 1:
The protrusions are defined by specific geometric parameters including height H, pitch spacing S, and channel height CH, with optimized ratios (S/H from 5-25, H/CH from 0.2-0.4). These parameter specifications provide a clear manufacturing target while achieving enhanced heat transfer through controlled turbulence.
3Temperature
If protrusions are added to the seal surface, then thermal management is improved, but seal geometry complexity increases
Solution Approach 1:
The protrusions are confined to the radially inner surface of the seal where they contact the cooling fluid, while the radially outer surface maintains a smooth geometry. This localized geometric modification achieves thermal management benefits without unnecessarily complicating the overall seal shape.
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
This solution effectively maintains the disk at a desired temperature by facilitating enhanced heat transfer through turbulent fluid flow, reducing the risk of damage from high-temperature gases and improving overall thermal management in the gas turbine engine.
Implementation Method 1
The radially inner surface includes a plurality of protrusions... which turbulate the cooling fluid to enhance heat transfer from the disk periphery
Implementation Method 2
enhance heat transfer from the disk periphery... facilitating enhanced heat transfer through turbulent fluid flow
Data Source
AI summary
A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.