Turbine Rotor Platform Cooling Circuit Design
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current turbine blade cooling systems face challenges in efficiently cooling the blade platform with minimal pressure loss, especially under higher operating temperatures, and are prone to compromised structural integrity due to bleeding cooling air from internal cooling circuits.
Innovation Solution
A turbine rotor assembly design featuring a platform cooling circuit independent from the airfoil cooling circuit, with a seal plate forming a cool air cavity to direct cool air to the platform cooling circuit, and strategically located inlets and outlets to maximize cooling efficiency with minimal pressure loss.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is bled from the internal cooling circuit to cool the platform, then the platform cooling effectiveness is improved, but the pressure loss in the cooling system increases
Solution Approach 1:
The cooling system is divided into two independent circuits: an internal cooling circuit for the airfoil and a separate platform cooling circuit. This segmentation allows each circuit to be optimized independently, with the platform cooling circuit drawing air directly from the compressor without bleeding from the internal cooling circuit, thus eliminating the pressure loss associated with air extraction while still achieving effective platform cooling.
Solution Approach 2:
A seal plate is introduced as an intermediary component between the compressor and the platform cooling circuit. The seal plate creates a sealed cavity that directs cool compressor air to the platform cooling circuit inlet, enabling controlled air delivery to the platform while maintaining system pressure integrity and preventing unwanted air leakage.
2Ease of manufacture
If the internal cooling circuit structure is simplified, then the manufacturing complexity is reduced, but the cooling effectiveness may be compromised
Solution Approach 1:
The cooling system is segmented into two independent circuits with distinct functions. The internal cooling circuit maintains its complexity for optimal airfoil cooling, while the platform cooling circuit is simplified as a separate system with direct air supply from the compressor, reducing manufacturing complexity without compromising overall cooling effectiveness.
Solution Approach 2:
The platform cooling function is extracted from the internal cooling circuit and implemented as a separate cooling circuit. This extraction allows the internal cooling circuit to be optimized for airfoil cooling without the added complexity of platform cooling integration, while the separate platform cooling circuit can be independently optimized for simplicity and reliability.
3Use of energy by moving object
If operating temperatures are increased to improve engine efficiency, then the engine efficiency is improved, but the blade structural integrity is compromised
Solution Approach 1:
The cooling circuits continuously supply cool air to the blade surfaces, maintaining thermal protection throughout operation. The independent platform cooling circuit ensures continuous cooling of the platform area, allowing the blade to sustain higher operating temperatures without compromising structural integrity, thus enabling improved engine efficiency.
Solution Approach 2:
The seal plate acts as an intermediary that ensures reliable delivery of cool air to the platform cooling circuit, maintaining consistent cooling effectiveness even at elevated operating temperatures. This reliable air delivery mechanism enables the blade to withstand higher thermal loads while preserving 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 design effectively cools the blade platform with minimal pressure loss, enhancing structural integrity and cooling efficiency, even under increased operating temperatures.
Implementation Method 1
The seal plate is disposed adjacent to the rotor to form a cool air cavity for directing cool air to the inlet of the platform cooling circuit
Implementation Method 2
the platform including a platform cooling circuit independent from the airfoil cooling circuit having an inlet on the leading side edge and an outlet
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
A turbine blade includes an airfoil defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root, and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the interior including an airfoil cooling circuit for directing airflow through the blade, and a platform supporting the airfoil and having a leading side edge, a trailing side edge, suction side edge, a pressure side edge, an airfoil-facing wall, and a root-facing wall, the platform including a platform cooling circuit having an inlet on the leading side edge and an outlet. The turbine blade may be included in a turbine rotor assembly.