Turbine Blade Platform Plenum Particulate Accumulation
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Solution Overview
Problem
Gas turbine engine blade assemblies face challenges with particulate accumulation in the platform plenum, which reduces fluid flow through cooling conduits and increases thermal stress, leading to potential premature part replacement.
Innovation Solution
The blade assembly incorporates a platform plenum with a reduced feed angle and minimum feed cross-sectional area for the feed conduit, along with an optimized stator rotor seal radius, to minimize particulate accumulation and enhance cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional feed conduit design is used in the blade assembly, then the platform plenum can be supplied with cooling fluid, but particulate accumulation occurs in the platform plenum which reduces cooling efficiency
Solution Approach 1:
The patent changes geometric parameters of the feed conduit, specifically the feed angle (reducing it to between 0-30 degrees from the axial direction) and the minimum feed cross-sectional area (reducing it to between 2.00E-06 to 3.50E-06 m²). These parameter changes modify the flow characteristics to reduce particulate accumulation while maintaining cooling fluid supply to the platform plenum.
2Object-affected harmful factors
If the feed conduit cross-sectional area is reduced to minimize particulate accumulation, then less particulates enter the platform plenum, but the cooling fluid flow capacity may be compromised
Solution Approach 1:
The patent optimizes the feed conduit dimensions by reducing the minimum feed cross-sectional area to a specific range (2.00E-06 to 3.50E-06 m²) and adjusting the feed angle to 0-30 degrees. These parameter changes create a flow regime that limits particulate transport while preserving adequate cooling fluid flow capacity through the optimized geometry.
3Object-affected harmful factors
If the feed angle is reduced to minimize particulate accumulation, then particulates are less likely to enter the platform plenum, but the feed conduit geometry becomes more complex
Solution Approach 1:
The patent simplifies the feed conduit geometry by defining it with specific parameter ranges: feed angle of 0-30 degrees relative to the axial direction, and minimum feed cross-sectional area of 2.00E-06 to 3.50E-06 m². These parameter specifications create a relatively simple conical or tapered geometry that is easier to manufacture while effectively reducing particulate accumulation.
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 design effectively reduces particulate accumulation, improves cooling fluid flow, and increases the durability of the blade assembly by mitigating creep and fatigue, thereby extending the time on wing and reducing maintenance costs.
Implementation Method 1
a feed conduit (71) comprising a passage extending from a feed inlet (72) to a feed outlet (73), the feed inlet and the feed outlet defining a feed centerline therebetween, the feed inlet fluidly coupled to the set of the inlet passages
Implementation Method 2
The blade assembly includes a platform (50) and an airfoil (60) extending radially outward from the platform (50). The airfoil (60) includes a set of cooling conduits (68)... a platform plenum (70) formed below a lower surface of the platform (50)... fluidly coupled to the set of cooling conduits (68)
Data Source
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AI summary
A gas turbine engine having a blade assembly (30) with a platform (50), an airfoil (60), and a shank (40). The airfoil has a plurality of cooling conduits (70), and the shank has a plurality of inlet passages (48) to provide cooling fluid to the cooling conduits in the airfoil. The cooling fluid is vented through a plurality of cooling holes (69) along the trailing edge of the airfoil. The blade assembly has specific geometries that improve durability