Turbomachine Compressor Asymmetric Contoured Wall Ring
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Solution Overview
Problem
Existing compressor designs in turbine engines face limitations in optimizing flow rate and compression ratio due to flow separations and pumping phenomena in the inter-blade passages, particularly in the corners of blades, which affect efficiency and reliability.
Innovation Solution
An axial turbomachine compressor with an annular stream, featuring a guide surface with an axisymmetric or substantially planar zone that crosses the inter-blade passage, including a main bump and hollow, where the bump is convex and the hollow is concave, optimizing the flow by reducing corner separations and vortices through specific geometric configurations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a non-axisymmetric geometry with hump and trough is used in the guide surface, then flow control is improved, but flow separations occur in the blade corners and pumping phenomena arise
Solution Approach 1:
The guide surface is divided into distinct zones with different geometric characteristics: an axisymmetric zone and a non-axisymmetric zone with hump and trough. Each zone serves a specific function - the axisymmetric zone prevents flow separation while the non-axisymmetric zone controls the flow pattern, allowing local optimization of different surface regions
Solution Approach 2:
The guide surface geometry is segmented into multiple functional zones including an upstream zone, an axisymmetric zone, and a downstream zone. This segmentation allows each zone to address specific flow control requirements independently, preventing adverse interactions between different flow control mechanisms
2Productivity
If the bump height and hollow depth are increased to improve flow control, then the geometric complexity increases
Solution Approach 1:
The invention optimizes specific geometric parameters of the hump and trough features, including their heights, depths, lengths, and positions relative to the blade chord. By carefully controlling these parameters within specific ranges, the invention achieves effective flow control while limiting excessive geometric complexity
Data Source
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AI summary
The invention relates to a low-pressure compressor for an axial turbomachine. The compressor, or booster, comprises: a first blade (26A) with an intrados surface (38); a second blade (26B) with an extrados surface (40); an inter-blade passage with a guide surface (44) that connects the intrados surface to the extrados surface, defining the annular groove, and which has a ridge (58) and a trough (54) forming a geometry known as "3D contouring," or a non-axissymmetric surface. The guide surface includes an axisymmetric or substantially flat area (42) that axially traverses the inter-blade passage so as to separate the trough (54) from the ridge (58).