Annular Turbine Ring Rotor Radial Locking
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Solution Overview
Problem
Conventional turbofan engines have a complicated elongated structure due to axial flow, which complicates packaging and integration into certain applications, while tip turbine engines aim to provide a more compact design by integrating a turbine onto the outer periphery of the bypass fan, requiring a readily manufacturable and mountable turbine solution.
Innovation Solution
The fan-turbine rotor assembly features one or more turbine ring rotors cast as single integral annular rings, mounted to a diffuser with axial installation and radial locking, minimizing leakage between blade platforms and enhancing engine efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If the turbine is integrated onto the tips of hollow bypass fan blades in a tip turbine engine, then the engine length is significantly reduced and thrust-to-weight ratio is improved, but the turbine becomes difficult to manufacture and mount to the outer periphery of the bypass fan
Solution Approach 1:
The turbine is segmented into multiple individual turbine blades that are mounted onto the outer periphery of the bypass fan blades. Each turbine blade can be manufactured separately and then assembled to the fan assembly, making the overall system easier to manufacture and maintain while achieving the compact tip turbine configuration
Solution Approach 2:
The turbine blades are positioned at the outer periphery (radial dimension) of the bypass fan blades rather than along the axial length. This dimensional change from axial to radial placement achieves compact engine length while providing a practical mounting surface on the fan blade tips for turbine blade attachment
2Use of energy by moving object
If conventional axial flow configuration is used, then efficient gas turbine operation is achieved, but the engine structure becomes complicated and elongated
Solution Approach 1:
The turbine is merged with the bypass fan assembly by integrating turbine blades onto the outer periphery of the fan blades. This combination eliminates the need for a separate axial turbine section, reducing structural complexity while maintaining efficient energy conversion through the combined fan-turbine rotation
Solution Approach 2:
The hollow bypass fan blades are designed to rotate dynamically, serving dual functions as both fans for air intake and as mounting structures for the turbine blades. This dynamic integration allows the same structural element to perform multiple functions, reducing overall system 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 solution allows for a more efficient and compact integration of the turbine onto the bypass fan, improving the thrust-to-weight ratio and reducing the engine's length, while ensuring reliable mounting and operation.
Implementation Method 1
The turbine ring rotors are rotated toward a radial stop in a direction which will maintain the turbine ring rotor against the radial stop during operation of the fan-turbine rotor assembly
Data Source
AI summary
A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring (114) includes axial installation and radial locking of each turbine ring rotor.