Turbomachine Rotor Blade Cooling Passage With Intermediary Inserts
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Solution Overview
Problem
Bleeding compressed air from the compressor section for cooling rotor blades in gas turbine engines reduces the volume of air available for combustion, thereby decreasing engine efficiency.
Innovation Solution
The rotor blade design includes a passage with two tubes and inserts positioned between them, allowing for controlled heat transfer and reduced direct contact between coolant and airfoil, thereby minimizing heat absorption and maintaining coolant temperature for efficient cooling with less coolant volume.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is routed through passages in the rotor blade, then the rotor blade is cooled, but the volume of compressed air available for combustion is reduced
Solution Approach 1:
The cooling passage is segmented into a first passage portion and a second passage portion, with inserts positioned within the first passage portion to create multiple zones. This segmentation allows different regions of the passage to serve different functions, enabling more efficient heat transfer while maintaining lower coolant flow requirements.
Solution Approach 2:
Inserts are positioned within the first passage portion to act as intermediaries between the coolant and the airfoil. These inserts enhance heat transfer from the airfoil to the coolant without requiring direct contact between the coolant and the airfoil surface, improving cooling efficiency while minimizing coolant volume requirements.
2Temperature
If cooling air is bled from the compressor section, then the rotor blade can be cooled, but the efficiency of the gas turbine engine is reduced
Solution Approach 1:
The passage diameter changes along its length, with the first passage portion having a greater diameter than the second passage portion. This parameter change optimizes flow distribution and heat transfer characteristics, allowing for more efficient cooling that reduces the amount of compressor air needed for cooling purposes.
3Productivity
If the passage diameter is reduced in the second passage portion, then the coolant flow is directed more effectively, but the heat transfer area is reduced
Solution Approach 1:
The cooling system transitions from a single passage to a multi-zone system with inserts positioned within the first passage portion. This dimensional change creates additional heat transfer surfaces and flow paths, allowing effective heat transfer to occur even as the passage diameter reduces in the second portion.
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 configuration reduces the heat transfer to the coolant, allowing it to remain cooler and maintain efficiency, requiring less coolant than conventional designs, thus enhancing the overall efficiency of the gas turbine engine.
Implementation Method 1
The plurality of inserts is positioned between and in contact with the first and second tubes
Data Source
AI summary
The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a passage extending from a root to a tip of the airfoil. The passage includes a first passage portion and a second passage portion. The first passage portion has a greater diameter than the second passage portion. The rotor blade also includes a first tube positioned within the first passage portion. The first tube is spaced apart from the airfoil. The rotor blade further includes a second tube positioned within the first passage portion. The second tube is positioned between the airfoil and the first tube. Furthermore, the rotor blade includes a plurality of inserts positioned within the first passage portion. The plurality of inserts is positioned between and in contact with the first and second tubes.