Turbomachine Compressor Module with Overlapping Stator Vanes and Flaps
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Solution Overview
Problem
Existing turbomachine designs are bulky and require significant length to accommodate stator blades, which hinders compactness without degrading airflow efficiency.
Innovation Solution
Incorporation of variable stator vanes and pivotable flaps within the inter-arm spaces of a turbomachine compressor module, allowing for axial overlap with structural arms, with blades and flaps having continuous air guide surfaces and shared trailing edges for homogeneous airflow and reduced turbulence.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If stator blades are arranged downstream of structural arms in conventional turbomachine designs, then the airflow can be directed appropriately, but the overall length of the turbojet increases and compactness is reduced
Solution Approach 1:
The patent merges the stator blades with the structural arms by positioning the blades within the inter-arm spaces and allowing axial overlap. The blades and arms share the same axial space, with the blade trailing edges and arm trailing edges aligned at the same axial position. This integration eliminates the need for separate downstream arrangements, reducing the overall engine length while maintaining both structural support and airflow direction functions.
Solution Approach 2:
The invention transitions from a sequential axial arrangement (arms first, then blades downstream) to a superimposed three-dimensional arrangement where blades and arms occupy the same axial space. The blades are positioned within the inter-arm spaces with axial overlap, utilizing the radial and circumferential dimensions more efficiently to achieve compactness without compromising airflow guidance.
2Length of moving object
If stator blades are integrated within inter-arm spaces with axial overlap, then compactness is improved, but the airflow homogeneity and turbulence control become more challenging
Solution Approach 1:
The patent applies local quality by giving the flaps a specific pivoting capability while the upstream portion remains fixed. The flaps can rotate around their pivot axis to adjust the airflow direction locally at the blade trailing edge, ensuring homogeneous flow distribution in the inter-arm spaces. This localized adjustability maintains airflow stability despite the compact integrated arrangement.
Solution Approach 2:
The invention introduces dynamic elements through the pivoting flaps that can rotate around their pivot axis. This dynamic capability allows the flaps to adjust the airflow direction and distribution in real-time, maintaining flow homogeneity and reducing turbulence. The continuous air guide surface ensures smooth transition during flap pivoting, preserving airflow stability in the compact configuration.
3Stability of the object's composition
If the flap pivot axis is positioned close to the upstream portion, then continuous air guide surface is maintained, but the pivoting range and flow control capability are limited
Solution Approach 1:
The blade structure is segmented into an upstream fixed portion and a downstream pivoting flap. This segmentation allows the upstream portion to maintain the continuous air guide surface and stable flow path, while the downstream flap provides independent pivoting capability for flow control. The division enables both continuity and adaptability to coexist by assigning different functions to different segments.
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 design achieves compactness while maintaining optimal compression ratio and airflow efficiency by integrating stator blades within the structural arms, reducing the overall length of the turbojet engine.
Implementation Method 1
each arm has an upstream, fixed portion and a downstream flap pivotable around a respective axis for each flap
Implementation Method 2
the stator blades are orientable around a respective axis for each blade
Implementation Method 3
The flaps provide a flow at the module outlet that is circumferentially more homogeneous and limit the risk of turbulence at the module outlet
Data Source
Figure 1~2
Figure 3~4
Figure 5
AI summary
The invention relates to a turbomachine compressor module (47), comprising an annular row of structural arms (46) defining inter-arm spaces (56) between two circumferentially adjacent arms (46, 48); and an annular row of stator vanes (39) with variable orientation about an axis (A) and arranged at least partially in the inter-arm spaces (56). The arms (46) are provided with flaps (60) that can be pivoted about an axis (B). The invention also relates to a turbomachine provided with such a module (47) and a row of rotor vanes (40) directly downstream from the module.