Rotor Blade Cooling Deflector for Swirl-Reduced Air Distribution
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Solution Overview
Problem
Existing mounting and cooling arrangements for rotor blades in gas turbine engines are in need of improvement to enhance efficiency and effectiveness.
Innovation Solution
A rotor blade design featuring a cooling air passage and deflector that directs cooling air efficiently into the blade, utilizing a cooling air aperture and deflector geometry to minimize swirling and enhance cooling air distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional cooling air passages are used without deflectors, then the structure is simpler, but cooling air distribution is less effective and swirling occurs
Solution Approach 1:
A cooling air deflector is introduced as an intermediary component between the cooling air passage and the blade interior. The deflector includes a deflector surface that directs cooling air flow and reduces swirling, while a cooling air aperture provides a controlled passage for air. This intermediary structure improves cooling air distribution effectiveness without requiring complete redesign of the entire cooling system.
2Reliability
If heavier cooling components are added to improve cooling distribution, then cooling effectiveness increases, but rotating weight increases
Solution Approach 1:
The cooling air deflector is designed with localized functionality where the deflector surface is positioned specifically at the cooling air passage outlet to address swirling only where it occurs. The cooling air aperture is strategically placed to provide targeted cooling air flow to critical areas of the blade. This localized approach improves cooling air distribution effectiveness while minimizing the amount of material and overall weight of the rotating component.
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 design improves cooling efficiency and reduces rotating weight, while maintaining structural integrity and enhancing the performance of the turbine engine.
Implementation Method 1
The cooling air deflector is configured to direct a first portion of cooling air flowing within the plenum towards the passage inlet and a second portion of cooling air flowing within the plenum away from the passage inlet
Data Source
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AI summary
A rotor blade (72) includes an airfoil (86), a root (90), a cooling air passage (122) and a cooling air deflector (94). The root (90) extends axially along an axis (24) between a first end (114) and a second end (116). The root (90) extends laterally between a first side (118A) and a second side (118B). The root (90) projects radially inward and away from the airfoil (86) to an inner end (112) of the root (90). The cooling air passage (122) includes a passage inlet (124) disposed at the inner end (112). The cooling air passage (122) projects radially into the rotor blade (72) from the passage inlet (124). The cooling air deflector (94) projects radially inward from the inner end (112) of the root (90) to an inner end (130) of the cooling air deflector (94). The cooling air deflector (94) is disposed at the second side (118B) and is spaced laterally from the first side (118A). The cooling air deflector (94) includes a cooling air aperture (150).