Gas Turbine Disk Cooling via Segmented Air Supply
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Solution Overview
Problem
Gas turbines face inefficiencies in cooling their turbine disks, leading to potential deformation and damage due to high-temperature operating conditions, as existing cooling methods do not effectively distribute cooling air to each disk individually.
Innovation Solution
A system with multiple cooling air supply passages is implemented, where cooling air is supplied from a compressor through a combustor and torque tube unit to various stages of turbine disks, with different passages having varying pressures and temperatures to optimize cooling based on the disk's position, and swirl chambers are used to change the flow to a turbulent state for enhanced distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If cooling air is supplied to turbine disks using existing cooling methods, then the structure remains simple, but the cooling efficiency is insufficient and thermal deformation occurs
Solution Approach 1:
The cooling air supply system is segmented into multiple independent passages (first cooling air supply passage, second cooling air supply passage, third cooling air supply passage) that individually supply cooling air to different turbine disks. This segmentation enables targeted cooling for each disk, improving cooling efficiency while managing complexity through modular design
Solution Approach 2:
Different cooling air supply passages provide cooling air with varying pressures and temperatures tailored to the specific needs of different turbine disks. The system creates local quality variations in cooling intensity based on the thermal conditions of each disk location, optimizing cooling effectiveness
2Temperature
If cooling air is supplied to all turbine disks uniformly, then the system structure is simple, but disks in high-temperature zones cannot receive adequate cooling
Solution Approach 1:
The system provides differentiated cooling conditions for different turbine disks based on their thermal environments. The first cooling air supply passage supplies cooling air to the first stage turbine disk, the second to the second stage, and the third to the third and fourth stage disks, with each passage having optimized pressure and temperature parameters suitable for its specific location
Solution Approach 2:
The cooling system is divided into multiple independent passages that can be optimized separately for different disk locations. This allows the first, second, and third cooling air supply passages to have different operating parameters (pressure, temperature) tailored to the specific thermal conditions of each disk region
3Productivity
If cooling air flow is laminar, then the flow is stable and easy to control, but the distribution to multiple disks is insufficient
Solution Approach 1:
Swirl chambers are introduced to generate turbulent flow conditions for cooling air distribution. The swirl chambers create rotational motion and turbulence in the cooling air flow, enhancing mixing and distribution effectiveness across multiple turbine disks, thereby improving cooling coverage and 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 system improves cooling efficiency, minimizes thermal deformation and damage to turbine disks, and enhances the overall performance of the gas turbine by ensuring stable cooling of each disk, even in high-temperature environments.
Implementation Method 1
cooling air is supplied from a compressor through a combustor and a torque tube unit to a first stage turbine disk
Implementation Method 2
cooling air is supplied from a compressor through a combustor and a torque tube unit to a first stage turbine disk
Implementation Method 3
cooling air is supplied from an nth unit compressor disk of first to nth unit compressor disks, constituting a compressor disk unit, through the torque tube unit to a second stage turbine disk
Implementation Method 4
cooling air is supplied from an nth unit compressor disk of first to nth unit compressor disks, constituting a compressor disk unit, through the torque tube unit to a second stage turbine disk
Implementation Method 5
cooling air is supplied from the n-αth unit compressor disk of the first to nth unit compressor disks, after axially passing through a tie rod provided in the gas turbine, to third and fourth stage turbine disks
Implementation Method 6
cooling air is supplied from the n-αth unit compressor disk of the first to nth unit compressor disks, after axially passing through a tie rod provided in the gas turbine, to third and fourth stage turbine disks
Implementation Method 7
swirl chambers are used to change the flow to a turbulent state for enhanced distribution
Data Source
AI summary
Disclosed herein is a system for cooling a gas turbine. The system for cooling a gas turbine cools a turbine disk unit by individually supplying cooling air to each of a plurality of turbine disks.