Recovered-Cycle Engine Volute Structure to Prevent Deformation
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Solution Overview
Problem
The integration of a recovered-cycle turbine engine with a centrifugal compressor is complicated by the structural limitations of existing volute configurations, which fail to effectively transmit structural forces and are prone to deformation and cracking, leading to degraded performance and reduced service life.
Innovation Solution
The volutes are redesigned with connecting arms extending axially and/or radially through their ports, rigidly connecting annular portions to the diffuser and straightener, allowing for the transmission of structural forces and enhancing structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If conventional volutes are used in a recovered-cycle turbine engine with a centrifugal compressor, then the engine can be assembled with standard components, but the volutes fail to transmit structural forces effectively and are prone to deformation and cracking
Solution Approach 1:
The volute is divided into multiple segments (first volute segment, second volute segment, third volute segment) that are rigidly connected to each other and to the diffuser and straightener components. This segmentation allows each part to be manufactured separately using standard processes while the rigid connections ensure effective transmission of structural forces throughout the assembly, preventing deformation and cracking.
2Volume of moving object
If volutes are positioned close to the centrifugal compressor and combustion chamber to optimize size, then the engine footprint is reduced, but the volutes become more susceptible to deformation and structural failure
Solution Approach 1:
The volute segments are pre-configured with rigid connecting structures (connecting arms) that are integrated into the design before assembly. These connecting arms extend from the volute segments to rigidly connect to the diffuser and straightener, providing structural reinforcement in advance. This preliminary structural preparation ensures that when the volutes are positioned close to the compressor and combustion chamber, they maintain adequate strength and resistance to deformation despite the compact arrangement.
3Reliability
If the volutes are rigidly connected to transmit structural forces, then structural integrity is improved, but the complexity of the volute assembly increases
Solution Approach 1:
The volute segments are rigidly connected to each other and to the diffuser and straightener components through integrating connecting arms that are formed as part of the volute segments themselves. This merging of functions—where the volute segments simultaneously serve as fluid passages and structural force-transmission elements—reduces the need for separate reinforcing structures. The connecting arms are configured to extend from the volute segments and rigidly connect to adjacent components, combining the fluid guidance and structural support functions into a unified assembly that maintains reliability without excessive complexity.
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 ensures effective force transmission, preventing volute deformation and cracking, maintaining rotor/stator clearances, and improving the aerodynamic performance and service life of the turbine engine.
Implementation Method 1
a heat exchanger, this exchanger comprising: a first circuit supplied with combustion gases collected from the outlet of the free turbine (5), and a second circuit comprising an inlet connected by a first volute to the outlet of the diffuser and an outlet connected by a second volute to an inlet of the straightener
Data Source
AI summary
An aircraft turbine engine having a compressor,—an annular combustion chamber, a system for diffusing and straightening an air stream exiting the compressor in order to supply the combustion chamber, and a heat exchanger, this heat exchanger having: a first circuit supplied with exhaust gas from the turbine engine, and a second circuit comprising an inlet (38ba) connected by a first scroll to an outlet of the diffuser, and an outlet connected by a second scroll to an inlet of the straightener, the scrolls including connecting arms that rigidly connect the annular portions of the scrolls which are secured or connected to the diffuser and to the straightener, respectively.