Inter-turbine Casing Segmented Splitter Vanes

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Solution Overview

Problem

Conventional inter-turbine casings for turbomachines, especially those with a multi-profile configuration, are difficult to manufacture and maintain due to complex gas flow deflection requirements and aerodynamic optimization challenges, making them costly and labor-intensive.

Innovation Solution

An inter-turbine casing design featuring an inner and outer shroud with radially extending arms and circumferentially positioned splitter vanes, where the splitter vanes have internal and external platforms that slide into grooves and are locked in place using tenons and ribs, facilitating assembly and maintenance, and allowing for sectorization of the shrouds for easier production.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If a multi-profile configuration is used with splitter vanes and arms for gas flow deflection, then aerodynamic performance is improved, but manufacturing complexity and cost increase

Engineering Contradiction:

Improveaerodynamic optimizationVSAvoidmanufacturing complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The inter-turbine casing is divided into modular components: arms, splitter vanes, inner ferrule, and outer ferrule that can be manufactured separately and assembled. The splitter vanes are further segmented into multiple profiles (first profile, second profile, third profile) along the flow direction, allowing each segment to be optimized independently for aerodynamic performance while simplifying manufacturing of individual parts.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The splitter vanes are designed with variable geometry along the flow direction, transitioning from a first profile near the arms to a second profile in the intermediate section, and finally to a third profile near the downstream end. This dynamic variation in vane geometry allows optimization of gas flow deflection at different stages while maintaining manufacturability through standardized construction methods.

Inventive Principle:

Principle #15Dynamics

2Adaptability or versatility

If complex aerodynamic profiles are integrated into the fairing, then gas flow deflection performance is improved, but ease of manufacture deteriorates

Engineering Contradiction:

Improvegas flow deflectionVSAvoidease of manufacture

Core Design Contradiction:

Adaptability or versatilityVSEase of manufacture

Solution Approach 1:

The complex aerodynamic fairing is segmented into multiple functional components: arms extending radially between inner and outer ferrules, and separate splitter vanes positioned between the arms. Each component can be manufactured using standard casting or fabrication processes, avoiding the need for complex integrated manufacturing while achieving the required gas flow deflection performance.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The arms serve multiple functions: they provide structural support between the inner and outer ferrules, define the flow path geometry, and work in conjunction with the splitter vanes to deflect gas flow. This multi-functionality reduces the need for additional specialized components, simplifying manufacturing while maintaining aerodynamic performance.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Strength

If the inter-turbine casing is designed as a single integrated component, then structural integrity is improved, but ease of repair and maintenance deteriorates

Engineering Contradiction:

Improvestructural integrityVSAvoidease of maintenance

Core Design Contradiction:

StrengthVSEase of repair

Solution Approach 1:

The inter-turbine casing is segmented into removable components including arms and splitter vanes that can be detached from the inner and outer ferrules. The splitter vanes are specifically designed to be removable and replaceable, allowing maintenance personnel to access and repair worn or damaged vanes without replacing the entire casing structure, thus improving ease of repair while maintaining structural integrity through the ferrule-arm-vane assembly design.

Inventive Principle:

Principle #1Segmentation

Data Source

PatentEP3746642B1Mid-turbine frame comprising struts and intermediate guide vanes

Publication Date: 2022.03.02 SAFRAN AIRCRAFT ENGINES SAS

Figure 1~2
Figure 3a~3b
Figure 4~5

AI summary

The invention relates to an inter-turbine casing (1) comprising: an inner shell (10), an outer shell (20), and an assembly of arms (2) extending radially between the inner (10) and outer (20) shells; and an assembly of splitter blades (30) positioned between the arms (2), each splitter blade (30) comprising an inner platform (33) and an outer platform (36). The inner shell (10) comprises at least one inner groove (11) for slidably receiving one or more inner platforms (33). The outer shell (20) comprises at least one outer groove (21) for slidably receiving one or more outer platforms (36). The inter-turbine casing further comprises locking means (4, 5) for locking the splitter blades (30) in the inner (11) and outer (21) grooves. The splitter blades are arranged using multiple tenons (39) that extend in corresponding ribs (12, 22).