Coupled Transition Section and HPC Layout for Non-Uniform Inlet Flow
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing methods for designing and optimizing the transition from-flow aerodynamic layout of a gas turbine compressor have not effectively addressed the complex and changeable incoming flow environment and the significant influence of real structures like the upstream transition section, leading to an increase in the incoming flow resistance and uniformity of the high-pressure compressor, resulting in increased intake resistance and decreased flow capacity.
Innovation Solution
A multi-dimensional coupled design method for the through-flow aerodynamic layout of the gas turbine transition section-high-pressure compressor, involving decomposition of performance indicators, transition section through-flow design and optimization, extraction of coupled parameters, and integrated design of the transition section and high-pressure compressor, using Bezier curves, polynomial airfoils, and genetic algorithms to optimize endwall and strut profiles, and three-dimensional CFD calculations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the transition section is optimized to minimize its impact on high-pressure compressor flow, then the incoming flow conditions improve to a certain extent, but the transition section flow factors are not incorporated into the aerodynamic design of the high-pressure compressor, so the performance is still affected
Solution Approach 1:
The patent merges the transition section design with the high-pressure compressor aerodynamic design into a unified coupled design system. The transition section flow factors are incorporated directly into the compressor blade aerodynamic design through coupled design equations, allowing simultaneous optimization of both components rather than treating them separately.
Solution Approach 2:
The patent performs preliminary action by pre-calculating and incorporating the transition section flow characteristics (pressure distribution, flow angles, velocity vectors) into the compressor design phase. The transition section outlet flow parameters are used as boundary conditions for the compressor inlet, ensuring the compressor is designed to accommodate the actual flow conditions from upstream.
2Reliability
If the high-pressure compressor is aerodynamically designed according to uniform incoming flow and then iteratively optimized through three-dimensional CFD or experimental testing, then the performance improves, but enormous time and resource consumption is required
Solution Approach 1:
The patent segments the design process into distinct but coupled stages: transition section flow calculation, coupled parameter extraction, and compressor aerodynamic design. Each stage produces specific outputs that feed into the next, allowing systematic optimization without requiring exhaustive iterative CFD or experimental testing of the entire system.
Solution Approach 2:
The patent replaces the mechanical iterative optimization process (repeated CFD calculations and experimental testing) with an analytical coupled design method. The coupled design equations directly compute the optimal compressor parameters based on transition section flow characteristics, substituting computational iteration with mathematical solution.
3Reliability
If repeated iterative adjustments with geometric modeling are performed, then the performance improves, but the final scheme differs greatly from the original design, leading to serious deviation of internal load distribution and flow matching
Solution Approach 1:
The patent implements feedback by using the transition section outlet flow parameters (pressure, velocity, flow angles) as direct inputs to the compressor design equations. The coupled design process continuously references the actual upstream flow conditions, ensuring the compressor geometry is optimized for the real flow field rather than idealized uniform flow, thereby maintaining design consistency.
4Ease of manufacture
If the transition section and high-pressure compressor are designed and optimized as independent objects, then the design process is simpler, but the effect of performance improvement is limited and the compressor remains a bottleneck
Solution Approach 1:
The patent merges the transition section design with the high-pressure compressor aerodynamic design into a unified coupled design system. The transition section flow factors are incorporated directly into the compressor blade aerodynamic design through coupled design equations, allowing simultaneous optimization of both components rather than treating them separately.
Data Source
AI summary
The purpose of the present invention is to provide a multi-dimensional coupled design method for the through-flow aerodynamic layout of a gas turbine transition section-high pressure compressor. In the present invention, the transition section and the high-pressure compressor are regarded as a system for integrated coupled design, and full integration with the upstream transition section is achieved in all dimensions and links of the high-pressure compressor's aerodynamic design. This realizes the integrated and collaborative design of the through-flow layout of the transition section and the high-pressure compressor, enabling the aerodynamic design of the transition section-high pressure compressor system in different dimensions to enter a stage of systematization, parameterization and refinement. It effectively improves the aerodynamic performance of the high-pressure compressor, enhances the accuracy of aerodynamic design, saves a large amount of design iteration time, shortens the design cycle, and is highly suitable for engineering design applications. The present invention is not limited to the high-pressure compressor of gas turbines; it is also applicable to the aerodynamic design process of aero-engine high pressure compressors and various industrial axial compressors with transition through-flow structures.