Turbine Module Segmented Flow Structures for Mass Flow Uniformity
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Solution Overview
Problem
Turbine modules in turbomachines face challenges in achieving uniform flow and mass flow distribution, leading to non-uniformities in Mach number and mass flow, which affect efficiency, despite efforts to optimize flow structures and guide vanes.
Innovation Solution
The turbine module combines 'thick' and 'thin' deflection blades with varying radial widths and strategically placed elevations/depressions in the hot gas channel, allowing for axial overlap and redistribution of mass flow, thereby optimizing flow uniformity and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If thick flow structures are used to guide hot gas, then structural strength is improved, but flow uniformity deteriorates due to large division areas
Solution Approach 1:
The flow structure is segmented into two distinct components: a thick support strut providing structural strength and thin deflection blades providing flow guidance. This segmentation allows each component to optimize its function independently without compromising the other.
Solution Approach 2:
Different parts of the flow structure have different thickness characteristics - the support strut has large profile thickness for strength, while the deflection blades have small profile thickness for flow uniformity. This local differentiation resolves the contradiction between structural requirements and flow quality requirements.
2Manufacturing precision
If uniform deflection blades are used, then discharge angle uniformity is improved, but mass flow distribution deteriorates due to boundary layer convergence
Solution Approach 1:
The radial width of the hot gas channel is varied along the axial direction to compensate for boundary layer convergence effects. By changing the geometric parameter (channel width) rather than the blade geometry itself, the patent maintains uniform discharge angles while achieving uniform mass flow distribution.
Solution Approach 2:
Instead of modifying the two-dimensional blade geometry to achieve flow uniformity, the patent introduces a third dimension by varying the channel width in the axial direction. This dimensional approach allows mass flow redistribution without affecting the discharge angle uniformity provided by the uniform blades.
3Quantity of substance
If the radial width of the hot gas channel is varied, then mass flow distribution is improved, but device complexity increases
Solution Approach 1:
The variable width section is merged with the existing flow structure components, integrating the mass flow redistribution function into the overall flow path design rather than adding separate adjustment mechanisms. This reduces device complexity while achieving the desired mass flow distribution.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This configuration enhances flow uniformity and efficiency by allowing the hot gas to converge towards the largest cross-sectional area, resolving boundary layer issues and minimizing non-uniformities, thereby improving the overall performance of the turbomachine.
Implementation Method 1
The resulting hot gas, a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process
Implementation Method 2
The second (thin) deflection blades; for example, a uniform discharge angle can be set. This can be advantageous, for example, with regard to the uniformity of the flow to the downstream rotor
Implementation Method 3
the hot gas flow tends towards the largest free cross section, i.e. towards where the radial width is greatest, which allows boundary layer convergence to be resolved and non-uniformities to be avoided
Data Source
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AI summary
The present invention relates to a turbine module (10) for a turbomachine (1), comprising a first flow structure (6) and a second flow structure (21), which flow structures (6, 21) are arranged in a hot gas channel (36) bounded by the turbine module (10) and designed to guide a hot gas, in succession with respect to a longitudinal axis (2) of the turbine module (10) in a direction of rotation (37), wherein the flow structures (6, 21) each have a leading edge (6a, 21a) and a trailing edge (6b, 21b) downstream of the flow in the hot gas channel (36), and the second flow structure (21) is provided as a deflecting blade, wherein the second flow structure (21) has a smaller profile thickness than the first flow structure (6), and wherein the hot gas channel (36) is defined with respect to the longitudinal axis (2) of the The turbine module (10) has a radial width (35) which changes in the direction of rotation (37).