Turbine Rotor Blade Platform Cooling Arrangement
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional platform cooling designs for turbine rotor blades face challenges such as inadequate sealing, limited cooling control, high manufacturing costs, and inflexibility, leading to inefficient cooling and reduced durability, especially in the thin radial profile region.
Innovation Solution
A platform cooling configuration featuring a pocket and manifold system within the shank cavity, with cooling apertures and film cooling apertures that efficiently direct pressurized coolant to the platform, enhancing cooling coverage and flexibility, and allowing for machining-based modifications to optimize cooling performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional platform cooling designs are used, then cooling is provided for the platform region, but sealing is inadequate and cooling control is limited
Solution Approach 1:
The cooling system is segmented into multiple independent cooling channels (first cooling channel, second cooling channel, third cooling channel) with distinct functions. The first channel provides convective cooling, while the second and third channels provide film cooling at different locations. This segmentation allows each channel to be optimized independently for its specific cooling task, improving overall cooling effectiveness without requiring complex integrated sealing systems.
Solution Approach 2:
Different cooling mechanisms are applied to different regions of the platform based on local thermal requirements. Convective cooling is applied in regions requiring high heat removal, while film cooling is applied at specific locations where thermal barrier protection is needed. This local differentiation optimizes cooling effectiveness while simplifying the overall sealing requirements compared to a uniform complex sealing system.
2Reliability
If conventional platform cooling designs are used, then cooling is provided, but manufacturing costs are high and flexibility is reduced
Solution Approach 1:
Cooling apertures are pre-formed within the platform structure during manufacturing, and cooling channels are established beforehand. This preliminary action allows the cooling system to be integrated into the blade manufacturing process itself, avoiding costly post-manufacturing modifications and reducing overall manufacturing costs while maintaining durability.
Solution Approach 2:
The cooling system incorporates adjustable elements that allow the cooling characteristics to be modified after manufacturing. This dynamic capability enables optimization of cooling performance for different operating conditions without requiring expensive re-manufacturing, thereby improving ease of manufacture while maintaining durability.
3Strength
If the platform has a thin radial profile, then structural support is provided, but cooling becomes difficult to implement
Solution Approach 1:
The cooling channels are nested within the thin platform structure, with channels and apertures integrated into the existing radial profile. The first cooling channel extends through the platform thickness, while second and third cooling channels are positioned at specific depths within the platform. This nesting approach allows effective cooling to be implemented within the constrained thin radial profile without compromising structural support.
Solution Approach 2:
Instead of relying solely on radial thickness for cooling, the system utilizes axial and circumferential dimensions by creating channels that extend axially through the platform and circumferentially around it. Cooling apertures are distributed across multiple axial positions and circumferential locations, effectively using three-dimensional space within the thin radial profile to achieve adequate cooling while maintaining structural integrity.
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 provides effective and flexible cooling for the platform region, reducing aerodynamic losses and manufacturing costs, while improving durability and adaptability to varying operating conditions.
Implementation Method 1
a first cooling passage extending from the shank cavity through the platform to a first cooling aperture formed through the platform
Implementation Method 2
cooling the platform and adjacent components
Implementation Method 3
a second cooling passage extending from the shank cavity to a second cooling aperture formed through the platform... a third cooling passage extending from the shank cavity to a third cooling aperture formed through the platform
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A platform cooling arrangement (130) for a turbine rotor blade (100) having a platform (110) at an interface between an airfoil (102) and a root (104), the root (104) including attachment means and a shank (112), wherein the platform (110) comprises a suction side (129) that includes a topside (113) extending from an airfoil base to a suction side slashface (122), and wherein the platform (110) overhangs a shank cavity (119). The platform cooling arrangement (130) may include: a pocket (160) formed in an underside region (114) of the platform (110), the pocket (160) comprising a mouth that fluidly communicates with the shank cavity (119); a manifold (162) extending from the suction side slashface (122) to a pressure side slashface (126), the manifold (162) including a connection to the pocket (160); and cooling apertures (156) that extend from connections made with the pocket (160) and manifold (162) to ports.