Integrated Turbine Frame for Three-Spool Interdigitated Engine
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Solution Overview
Problem
Conventional three-spool gas turbine engines face limitations in interdigitation of turbines due to overhung masses, leading to increased axial length and weight, which restricts the application of interdigitated turbine sections and compromises fuel efficiency, operational efficiency, and power output.
Innovation Solution
A turbine frame design with independently rotatable spools and a bearing system that includes a first, second, and third bearing surface, allowing for interdigitated turbine sections with reduced axial length and weight, enabling further interdigitation and improved efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a plurality of turbine frames are used to support three spool bearing assemblies, then each spool can be properly supported, but the axial length and weight of the engine increase
Solution Approach 1:
The patent combines multiple bearing support functions into a single integrated turbine frame structure. The first turbine frame supports bearing assemblies for all three spools (high pressure, intermediate pressure, and low pressure), merging what would traditionally require separate frames into one unified structure, thereby reducing axial length while maintaining support capability
Solution Approach 2:
The single turbine frame performs multiple functions: it supports bearing assemblies for three different spools, provides structural integration for the turbine section, and enables the interdigitated arrangement. This multi-functional design eliminates the need for multiple specialized frames
2Productivity
If interdigitated turbine sections are implemented, then fuel efficiency and power output improve, but overhung masses limit the quantity of stages that can be interdigitated
Solution Approach 1:
The patent merges the support function for all three spools into a single turbine frame, which provides a stable reference point that reduces overhung masses. This integration allows more turbine stages to be interdigitated without exceeding mass limits, as the combined structure distributes loads more effectively
Solution Approach 2:
The interdigitated arrangement staggers turbine stages in the axial direction, creating a three-dimensional layout that reduces overhung masses. By alternating the radial positions of stages from different spools, the design distributes mass distribution more favorably
3Reliability
If multiple turbine frames are used, then bearing assemblies can be accommodated, but the weight of the engine increases
Solution Approach 1:
The patent merges multiple bearing support functions into a single turbine frame, eliminating the weight of redundant frame structures. The integrated frame uses shared structural elements and common mounting points, reducing overall material requirements and component weight
Data Source
AI summary
The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction. The gas turbine engine defines an upstream end and a downstream end along the longitudinal direction and includes a turbine frame defined around the axial centerline. The turbine frame includes a first bearing surface, a second bearing surface, and a third bearing surface. The first bearing surface corresponds to a first turbine rotor, the second bearing surface corresponds to a second turbine rotor, and the third bearing surface corresponds to a third turbine rotor, and each turbine rotor is independently rotatable.