Rotating Vane Seal Cooling Air Passages
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Solution Overview
Problem
Gas turbine engine air cooling systems experience efficiency losses due to thermal losses caused by the rotation of cooling air, which reduces the effectiveness of cooling and increases part temperatures.
Innovation Solution
A rotating inner diameter vane seal ring with angled flow passages and stress relief slots is introduced to create a continuous rotating flow path that minimizes dynamic losses by ensuring cooling air does not pass through alternating rotating and non-rotating components, thereby maintaining efficient cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is routed through rotating components, then cooling effectiveness is improved, but windage losses increase reducing engine efficiency
Solution Approach 1:
The vane seal ring is designed to rotate with the rotor, creating a dynamic sealing interface that moves with the rotating components. This dynamic configuration allows cooling air to be routed through rotating components without causing windage losses, as the seal maintains contact through rotation rather than creating friction against stationary surfaces
Solution Approach 2:
The vane seal ring acts as an intermediary component between the stationary compressor housing and the rotating rotor assembly. It provides a sealing interface that allows cooling air passages to traverse the rotating-stationary interface without causing windage losses, effectively mediating the transfer of cooling air while maintaining sealing integrity
2Productivity
If high pressure ratio compression is increased, then engine performance is improved, but discharge temperature increases requiring additional cooling
Solution Approach 1:
The cooling air passages are nested within the rotor disk and vane seal ring structure, allowing cooling air to be routed through the rotating components themselves. This nested configuration enables the system to handle higher discharge temperatures by providing internal cooling paths without adding external cooling systems that would increase complexity
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 enhances engine efficiency by preventing windage losses and maintaining cooling effectiveness, reducing part temperatures and improving overall performance in high-pressure ratio engines.
Implementation Method 1
US 5,558,496 discloses a gas turbine apparatus in which particulates are removed from the coolant used to cool gas turbines by subjecting the coolant to the centrifugal acceleration of the gas turbine rotor.
Data Source
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AI summary
An inner diameter vane seal (42) for a gas turbine engine (10) comprises an annular, ring-like body having inner and outer diameter rims (56, 54), forward and aft faces (47A, 47B) and an air passage (74). The outer diameter rim (54) extends circumferentially for engaging inner diameter ends (73) of stator vanes (38). The inner diameter rim (56) extends circumferentially and is spaced radially from the outer diameter rim (54). The forward and aft faces (47A, 47B) extend radially between the outer diameter rim (54) and the inner diameter rim (56). The air passage (74) extends from the forward face (47A) to the aft face (47B) between the inner and outer diameter rims (56, 54).