Low-Pressure Compressor Geometric Plane Division
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Solution Overview
Problem
Existing turbomachine compressor designs are not suitable for high-speed operation due to excessive load on downstream blades, particularly in the low-pressure compressor, which limits rotor speed and efficiency.
Innovation Solution
A turbomachine design featuring a low-pressure compressor with a geometric plane dividing it into upstream and downstream sections, where upstream sections have alternating rotor and stator blades and downstream sections only have fixed-orientation stator blades, sharing straightening forces across two or more stator vane rows to reduce load and increase rotor speed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the number of compressor stages is minimized to reduce weight and increase rotational speed, then productivity and efficiency improve, but the load on downstream blades increases excessively
Solution Approach 1:
The compressor is divided into two distinct sections by a geometric plane: an upstream section with alternating rotor and stator blades, and a downstream section with only stator blades. This segmentation allows the downstream stator blades to be specifically designed for flow straightening without the complexity of rotor blade interactions, enabling them to handle higher loads effectively while maintaining high rotational speeds upstream.
Solution Approach 2:
Different blade configurations are applied to different zones of the compressor. The upstream section uses alternating rotor and stator blades optimized for compression, while the downstream section uses solely stator blades optimized for flow straightening. This local differentiation allows each zone to perform its specific function efficiently, with downstream stator blades designed to withstand higher loads while straightening the flow.
2Stability of the object's composition
If at least two rows of stator blades are positioned downstream of the geometric plane with fixed orientation, then flow straightening is improved, but device complexity increases
Solution Approach 1:
Multiple downstream stator blade rows are merged into a single integrated structure fixed to a common internal ferrule. This consolidation achieves the flow straightening function through a unified assembly rather than separate components, reducing device complexity while maintaining the stability and effectiveness of flow straightening across at least two blade rows.
3Speed
If the compressor is configured for high peripheral speed operation, then productivity increases, but the load on blades increases limiting further speed increases
Solution Approach 1:
The compressor is segmented into upstream and downstream sections, allowing the upstream rotor blades to operate at high peripheral speeds while the downstream stator blades are specifically designed to handle the resulting high loads through optimized geometry and positioning. This segmentation enables high-speed operation without compromising blade strength.
Solution Approach 2:
The blade configuration parameters are changed downstream of the geometric plane, where at least two rows of stator blades are positioned with specific spacing and orientation to progressively straighten the flow. This parameter change allows the system to maintain high peripheral speeds while managing blade loads through optimized downstream flow control.
Data Source
Figure 1
Figure 2~3
AI summary
The invention relates to a turbomachine (2) with a low-pressure compressor (24) comprising: a rotor (44) equipped with at most four annular rows of rotor blades (40, 42); a stator (35) equipped with at most four annular rows of stator blades (39, 41, 43, 45); the compressor comprising a geometric plane (P) upstream of which the rows of rotor blades (40, 42) and stator blades (39, 41) are interlaced, and downstream of which are at least two rows (43, 45) of blades, exclusively stator blades. The axial turbomachine (2) comprises a first casing (47) defining a first gooseneck section, a second casing (49) defining a second gooseneck section, and the compressor (24) as defined above is positioned directly between the first and second gooseneck sections.