Turbomachine Blade Guide Profile for Flow Loss Reduction
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Solution Overview
Problem
Turbomachines, particularly gas turbines, face significant flow losses due to viscous effects, boundary layer interactions, and leakage flows, which reduce efficiency, especially in low-pressure turbines where profile losses dominate.
Innovation Solution
Incorporating a guide profile that extends partially in the axial and circumferential directions at the blade ends to influence and redirect leakage and boundary layer flows, aligning them with the main flow direction to minimize losses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If traditional blade design without additional guide profiles is used, then the blade structure is simple and easy to manufacture, but flow losses in the blade tip area are significant due to uncontrolled leakage and boundary layer flows
Solution Approach 1:
The blade is segmented into a main profile section and one or more secondary profile sections, with additional guide profiles separating different flow regions. This segmentation allows independent optimization of main flow and secondary flows (leakage and boundary layer flows), reducing overall flow losses while maintaining manageable structural complexity through modular design
Solution Approach 2:
Additional guide profiles act as intermediary elements between the main profile and the blade tip, actively controlling and redirecting leakage flows and boundary layer flows. These intermediary guide profiles mediate the flow transitions, aligning secondary flows with the main flow direction to reduce mixing losses and improve overall efficiency
2Power
If the blade operates at high speeds typical of turbomachines, then power output is increased, but viscous effects and turbulence at blade ends increase flow losses
Solution Approach 1:
Different sections of the blade are given different geometric qualities optimized for their specific functions. The main profile section has geometry optimized for power generation, while secondary profile sections and additional guide profiles have geometries specifically designed to control leakage and boundary layer flows, reducing viscous losses locally without compromising overall power output
Solution Approach 2:
The additional guide profiles and secondary profile sections incorporate curved and streamlined geometries that promote smooth flow transitions. These curved surfaces reduce flow separation and turbulence at high speeds, minimizing viscous effects and energy losses while maintaining the high power output required for turbomachine operation
Data Source
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AI summary
The invention relates to a blade (33), a blade segment and an assembly for a turbomachine (10), in particular for a gas turbine, as well as a turbomachine (10), wherein the blade (33) has a blade (13) with a blade profile and a radially inner blade end (EI) and a radially outer blade end (EA), and wherein, in addition to the blade profile, the blade has at least one first guide profile (LP1) arranged in the region of the radially inner (EI) and/or the radially outer blade end (EA) and spaced radially apart from the associated blade end (EI, EA) and extending at least partially in the axial direction (x) and at least partially in the circumferential direction and/or at least partially in the tangential direction.