Gas Turbine Ring Segment Cooling System with Variable Pitch Openings
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Solution Overview
Problem
In gas turbines, the pressure of combustion gas decreases as it flows through the turbine section, leading to an increase in the differential pressure between combustion gas and cooling air, resulting in excessive cooling air flow and inefficiency in cooling the ring segment, which affects thermal efficiency.
Innovation Solution
The cooling system for the ring segment is designed with cooling passages where the arrangement pitch and opening area of openings are adjusted along the flow direction to optimize cooling air flow, reducing the amount of cooling air blown into the combustion gas, particularly by increasing pitch or decreasing area downstream, to match the changing pressure conditions and blade shape.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is supplied to cool the ring segment, then the cooling performance is improved, but the thermal efficiency deteriorates due to excessive cooling air flow
Solution Approach 1:
The patent applies local quality by varying the opening area and arrangement pitch of cooling air openings along the axial direction of the ring segment. Different sections of the ring segment receive different amounts of cooling air based on their specific thermal conditions, rather than uniform cooling throughout. This optimized local distribution reduces overall cooling air consumption while maintaining effective cooling where needed.
Solution Approach 2:
The patent changes parameters of the cooling system by adjusting the opening area and arrangement pitch of cooling air openings along the axial direction. These parameter variations are designed to match the changing pressure conditions and thermal loads at different axial positions, reducing excessive cooling air flow while maintaining adequate cooling performance.
2Quantity of substance
If the opening area of cooling air openings is increased, then the cooling air flow is improved, but the thermal efficiency deteriorates due to excessive cooling air consumption
Solution Approach 1:
The patent applies local quality by making the opening area of cooling air openings non-uniform along the axial direction. Specific sections have larger opening areas where greater cooling air flow is needed, while other sections have smaller opening areas to reduce overall cooling air consumption and improve thermal efficiency.
Solution Approach 2:
The patent changes the parameter of opening area along the axial direction to optimize cooling air flow distribution. This parameter variation ensures adequate cooling air supply where needed while reducing excessive cooling air consumption overall, thereby improving thermal efficiency.
3Stability of the object's composition
If the arrangement pitch of cooling air openings is decreased, then the cooling air distribution is improved, but the thermal efficiency deteriorates due to increased cooling air consumption
Solution Approach 1:
The patent applies local quality by varying the arrangement pitch of cooling air openings along the axial direction. Different axial positions have different opening densities matched to their specific thermal conditions, providing optimized cooling air distribution without excessive overall cooling air consumption.
Solution Approach 2:
The patent changes the parameter of arrangement pitch along the axial direction to optimize cooling air distribution. This parameter variation ensures proper cooling air supply distribution while reducing excessive cooling air consumption, thereby improving thermal efficiency.
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 optimization reduces the cooling air amount, enhancing the thermal efficiency of the gas turbine by ensuring the right amount of cooling air is used, preventing thermal damage, and improving overall cooling performance.
Implementation Method 1
cooling air that is supplied from outside of the casing to be blown out and performs impingement cooling of the main body of the segment body
Implementation Method 2
blows out the cooling air from an opening that is arranged in the side end portions into combustion gas
Data Source
AI summary
In a cooling system of ring segment that cools a ring segment of a gas turbine, the segment body of the ring segment is constituted from a collision plate that has a small hole that blows out cooling air, a cooling space that is enclosed by the collision plate and the main body of the segment body; a first cavity that receives the cooling air from the cooling space; and a first cooling passage, of which one end communicates with the first cavity, and the other end blows out the cooling air from openings that are arranged in the side end portion into combustion gas; the openings of the first cooling passages being arranged so that the arrangement pitch of the openings becomes smaller or the opening area of the openings becomes larger on the upstream in the flow direction of the combustion gas than the openings on the downstream, and are arranged so that the arrangement pitch of the openings becomes larger or the opening area of the openings becomes smaller on the downstream in the flow direction of the combustion gas than the openings on the upstream.