Turbine Rotor Blade Integrated Airfoil and Platform Cooling
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Solution Overview
Problem
Turbine rotor blades face inefficiencies in cooling due to centrifugal forces and air flow, leading to localized hot spots that reduce blade life and require premature replacement, especially in the forward rotor cooling cavity where hot gas ingestion impairs platform cooling.
Innovation Solution
An integrated airfoil and platform cooling system with serpentine channels and flow turns that direct coolant to impinge on the platform's outer surface, enhancing cooling efficiency and reducing coolant flow requirements by utilizing airfoil coolant for platform cooling, with features like turbulators and film cooling holes for improved heat transfer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional cooling channels are used in turbine rotor blades, then cooling coverage is provided, but centrifugal forces and air flow at boundary layers prevent some areas from being adequately cooled, resulting in localized hot spots
Solution Approach 1:
The patent merges airfoil cooling and platform cooling into a single integrated system. The serpentine cooling channel extends from the airfoil into the platform, allowing a single coolant supply to cool both the airfoil and platform surfaces, eliminating the need for separate cooling systems and improving overall cooling effectiveness
Solution Approach 2:
The cooling channel transitions from a two-dimensional planar path to a three-dimensional serpentine path that winds through the airfoil and extends into the platform. This three-dimensional configuration increases the cooling surface area and improves coolant distribution to previously hard-to-reach areas
2Productivity
If higher temperatures are passed into the turbine section to increase efficiency, then engine efficiency is improved, but turbine rotor blades must be made of materials capable of withstanding such high temperatures and require cooling systems
Solution Approach 1:
The patent combines airfoil cooling and platform cooling functions into a single integrated serpentine channel system, reducing the number of separate cooling components and simplifying the overall cooling system architecture while maintaining effective cooling at high temperatures
Solution Approach 2:
The serpentine cooling channel serves multiple functions: it cools the airfoil surface, cools the platform surface, and provides structural integration between these components. This multi-functionality reduces the need for additional specialized cooling components
3Temperature
If the forward rotor cooling cavity is used for platform cooling, then cooling coverage is provided, but hot gas ingestion results in much warmer air under the blade platform and negatively impacts platform cooling
Solution Approach 1:
The serpentine cooling channel is positioned and configured to deliver cooled air to the platform surface before hot gas ingestion can significantly heat the platform. The channel extends into the platform to ensure cooling air reaches critical areas in advance of thermal exposure
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 integrated cooling system effectively addresses localized hot spots by enhancing backside platform cooling, reducing coolant flow needs, and minimizing stress on the turbine rotor blades, thereby extending their useful life and improving engine efficiency.
Implementation Method 1
The first and second legs conduct a coolant in generally radially inboard and radially outboard directions respectively
Implementation Method 2
a flow passage that extends radially outboard and laterally into the platform, so as to direct a radially outboard flowing coolant to impinge on an inner side of a radially outer surface of the platform
Implementation Method 3
features like turbulators and film cooling holes for improved heat transfer
Data Source
AI summary
An integrated airfoil and platform cooling system (30) for a turbine rotor blade (10) includes an inlet (38, 48) located at the root (24) for receiving a supply of a coolant (K), and at least one cooling leg (32a, 32c, 42a, 42c) fluidly connected to the inlet (38, 48) and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg (32a, 32c, 42a, 42c) is defined at least partially by a span-wise extending internal cavity (26) within a blade airfoil (12). An entrance of the cooling leg (32a, 32c, 42a, 42c) comprises a flow passage (92, 102) that extends radially outboard and laterally into a blade platform (50), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side (60) of a radially outer surface (52) of the blade platform (50), before leading the coolant (K) into the cooling leg (32a, 32c, 42a, 42c).