Integrated Strut-Vane Nozzle With Uneven Axial Chords
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Solution Overview
Problem
Conventional gas turbine engines with integrated struts and vanes face challenges in adjusting the flow to minimize length and prevent flow separation, leading to longer engine configurations and inefficiencies.
Innovation Solution
The integration of circumferentially spaced struts and vanes with varying axial chords, where at least one vane adjacent to the integrated strut-vane airfoil has a shorter axial chord than others, optimized through flow field analysis to prevent flow constriction and separation, allowing for a more uniform mass flow distribution and reduced engine length.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If struts are axially spaced from vanes to avoid flow separation, then flow separation is prevented, but engine length increases
Solution Approach 1:
The patent integrates the strut and vane into a single combined structure called an integrated strut-vane airfoil. The strut and vane are merged such that the vane is positioned at the trailing edge of the strut, eliminating the need for axial spacing while preventing flow separation through the integrated design. This resolves the contradiction by combining what were previously separate components into one unified structure.
Solution Approach 2:
The patent applies different axial chord lengths to different vanes in the array. Specifically, at least one vane adjacent to the integrated strut-vane airfoil has a shorter axial cord than other vanes. This local variation in geometry optimizes flow distribution and prevents flow constriction in specific areas while maintaining overall engine compactness.
2Length of moving object
If struts are integrated to vanes to reduce engine length, then engine length is reduced, but flow adjustment becomes challenging
Solution Approach 1:
The patent implements non-uniform axial chord distribution among the vanes, where at least one vane adjacent to the integrated strut-vane airfoil has a shorter axial chord than other vanes. This local geometric variation enables optimized flow distribution and prevents flow constriction, maintaining flow adjustment capability despite the integrated structure.
Solution Approach 2:
The patent modifies the geometric parameters of the vanes by varying their axial chord lengths. This parameter change allows optimization of the flow field around the integrated strut-vane airfoil, enabling proper flow adjustment while maintaining the compact integrated structure.
3Ease of manufacture
If uniform axial chord is used for all vanes, then manufacturing is simplified, but flow constriction occurs between vane and integrated strut-vane airfoil
Solution Approach 1:
The patent introduces local variation in vane geometry by making at least one vane adjacent to the integrated strut-vane airfoil have a shorter axial chord. This local modification prevents flow constriction and separation in critical areas while maintaining uniform manufacturing processes for the majority of vanes.
Solution Approach 2:
The patent creates an asymmetric configuration in the vane array by introducing vanes with different axial chord lengths. This asymmetry is strategically applied to prevent flow constriction between specific vanes and the integrated strut-vane airfoil, optimizing the flow field while maintaining manufacturing feasibility.
Data Source
AI summary
An integrated strut and turbine vane nozzle (ISV) comprising: inner and outer duct walls defining a flow passage therebetween, an array of circumferentially spaced-apart struts extending radially across the flow passage, and an array of circumferentially spaced-apart vanes extending radially across the flow passage. At least one of the struts is aligned in the circumferential direction with an associated one of the vanes and forms therewith an integrated strut-vane airfoil. The adjacent vanes on opposed sides of the integrated strut-vane airfoil have uneven axial chords relative to the other vanes.