Gas Turbine Compressor Stage Radius Adjustment
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Solution Overview
Problem
Innovative methods are needed to reduce the compressor flow rate in derivative gas turbines, such as humid air turbines and blast furnace gas firing turbines, while maintaining an equivalent compression ratio to the reference model, as existing approaches like reducing the outer radius of the compressor channel lead to decreased compression ratios and require new turbine designs.
Innovation Solution
A method involving determining specific inner and outer radius increments and decrements for each stage of the compressor channel to match the annulus areas of the derivative gas turbine with the reference model, allowing for the reuse of components and maintaining the compression ratio, including design updates and production based on these calculations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the outer radius of the compressor channel is reduced to decrease the annulus area and reduce the compressor flow rate, then the compressor flow rate decreases, but the compression ratio drops
Solution Approach 1:
The patent applies local quality by differentiating the radius adjustment strategy across different stages of the compressor. The inner radius increment and outer radius decrement are determined differently for the initial stage, intermediate stages, and final stage. Specifically, the inner radius is increased more in upstream stages while the outer radius is decreased more in downstream stages, creating stage-specific geometric modifications that maintain compression ratio while reducing overall flow rate.
Solution Approach 2:
The patent changes geometric parameters (inner radius and outer radius) of the compressor channel in a controlled manner. By determining specific inner radius increments and outer radius decrements for each stage, the patent modifies the annulus area parameters to achieve the desired balance between flow rate reduction and compression ratio maintenance. This involves calculating and applying precise dimensional changes to the compressor geometry.
2Power
If the turbine flow rate is increased to match the requirements of humid air turbines or blast furnace gas firing turbines, then the turbine power output increases, but the compressor flow rate becomes mismatched requiring new compressor design
Solution Approach 1:
The patent changes the geometric parameters of the compressor channel (inner radius and outer radius) to adjust the compressor flow rate to match the increased turbine flow rate. By determining specific radius increments and decrements for each stage, the patent modifies the compressor to handle the higher flow while maintaining compatibility with the existing turbine design, thus preserving component compatibility while adapting to new operational requirements.
Solution Approach 2:
The patent introduces dynamic adaptability by creating a compressor design that can accommodate varying flow rate requirements. The staged radius modification approach allows the compressor to be adapted to different operational conditions while maintaining compatibility with the base design, enabling the system to dynamically adjust to different fuel types and power output requirements.
3Ease of manufacture
If the compressor flow rate is reduced to match the reference model, then component reuse becomes possible, but the turbine flow rate becomes excessive requiring new turbine design
Solution Approach 1:
The patent applies parameter changes by precisely controlling the inner radius and outer radius modifications across different compressor stages. This allows the compressor flow rate to be reduced to match the reference model for component reuse, while the turbine flow rate is maintained at the higher level required for humid air or blast furnace gas applications, thus resolving the contradiction between component reuse and turbine performance requirements.
Data Source
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AI summary
An object is to reduce the compressor flow rate in comparison with the reference model while maintaining a compression ratio equivalent to that in the reference model. Annulus areas required of a compressor 38 of a derivative gas turbine 200 are determined based on a compressor flow rate and a compression ratio required of the compressor 38 of the derivative gas turbine 200. Under the condition that the annulus area of each stage of the compressor 38 becomes equal to the determined annulus area, an inner radius increment and an outer radius decrement of an initial stage 36a are determined, the inner radius increment and the outer radius decrement of each of intermediate stages 36b - 36e are determined so that the inner radius increment is not more than the inner radius increment of the previous stage and the outer radius decrement is not less than the outer radius decrement of the previous stage, and the inner radius increment and the outer radius decrement of a final stage 36f are determined so that the outer radius decrement is not less than the inner radius increment. The compressor 38 is designed by updating design data of components of the reference compressor 15 that deviated from the specifications due to the determination of the inner radius increment and the outer radius decrement so that the updated design data fulfill the specifications in each of the stages 36a - 36f.