Compressor Reinforcing Disk Passage for Pressure Drop Reduction
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Solution Overview
Problem
Gas turbines face limitations in reducing internal extraction pressure drop and achieving structural stability in compressor disks, particularly due to the vulnerability of existing vortex reducer structures and limited cooling efficiency.
Innovation Solution
The design incorporates a compressor with multiple main disks and a reinforcing disk featuring a passage system that reduces circumferential velocity and enhances structural stability, including a mount part, swelling part, and inclined passages to facilitate smooth airflow and improved cooling, thereby improving internal extraction pressure drop reduction and cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If a tube type vortex reducer structure is applied to the compressor disk, then the pressure drop reduction is improved, but the structural strength deteriorates
Solution Approach 1:
The vortex reducer is divided into multiple segments: a hub portion, multiple blade portions radially arranged around the hub, and a rim portion connecting the blade portions. This segmentation allows each component to be optimized independently - the blades can effectively reduce pressure drop while the rim and hub provide structural support, resolving the contradiction between pressure drop reduction and structural strength.
2Temperature
If the number of compressor disks is increased, then the cooling effect is improved, but the structural stability deteriorates
Solution Approach 1:
Multiple compressor disks are integrated onto a single rotating shaft, sharing common structural support. The disks are positioned at different axial locations and connected through the shaft and bearing structure, allowing them to work together for enhanced cooling while maintaining structural stability through their shared mounting system.
3Manufacturing precision
If the surface roughness of the contact surface is reduced to a predetermined range, then the manufacturing precision is improved, but the ease of manufacture deteriorates
Solution Approach 1:
High precision surface finishing is applied only to the critical contact surfaces between the compressor disk and the shaft, as well as the bearing contact surfaces. Other non-critical surfaces maintain standard finishing, balancing manufacturing precision requirements with ease of manufacture by focusing resources only where necessary.
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 configuration significantly enhances the structural stability and cooling effect on compressor disks, leading to improved internal extraction pressure drop reduction and increased efficiency in gas turbines.
Implementation Method 1
a de-swirler type vortex reducer structure using a vane may be applied to the compressor disk of a gas turbine. In this case, only the circumferential velocity component of the cooling air is reduced
Implementation Method 2
the inclined surface may be provided at a location facing a rotation direction of the reinforcing disk to reduce a circumferential velocity component of the compressed air flowing toward the rotation shaft
Implementation Method 3
a cooling passage is formed inside the stator and the rotor blades, and a cooling medium such as air or steam flows in the cooling passage to cool these stator and rotor blades
Data Source
AI summary
A compressor, which is mounted to a gas turbine and generates high temperature and high pressure compressed air and supplies the compressed air to a combustor, the compressor including: a plurality of main disks provided on an outer circumferential surface of a rotation shaft along a circumferential direction, and spaced apart from each other at predetermined intervals such that a portion of the compressed air flows toward the rotation shaft; and a reinforcing disk mounted to each space defined by the plurality of main disks spaced apart from each other, the reinforcing disk having the rotation shaft in common with the main disks, and being provided with a passage formed in a direction from an outer circumferential surface thereof toward the rotation shaft.