Radial Tip Turbine Clusters with Axial Locking

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Solution Overview

Problem

Conventional turbofan gas turbine engines have a complex elongated structure due to axial flow, making them difficult to package in certain applications, and integrating a turbine onto the tips of hollow bypass fan blades poses a design challenge for the fan-turbine rotor assembly.

Innovation Solution

The fan-turbine rotor assembly features turbine ring rotors with multiple turbine blade clusters mounted to a diffuser, utilizing axial installation and radial locking to minimize leakage and facilitate manufacturing and mounting on the outer periphery of a bypass fan, thereby enhancing engine efficiency and reducing thermal contrast.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Device complexity

If turbine blades are arranged in conventional axial flow configuration, then engine structure is simplified, but engine length becomes excessively long and packaging becomes difficult

Engineering Contradiction:

Improveengine structureVSAvoidengine length

Core Design Contradiction:

Device complexityVSLength of moving object

Solution Approach 1:

The patent transitions from conventional axial flow arrangement to a radial flow configuration where turbine blades are arranged radially around the fan blade tips. This dimensional change allows the engine to achieve compact packaging by utilizing the radial space around the fan tips rather than extending the engine length axially, thus resolving the contradiction between structural simplicity and engine length.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

Solution Approach 2:

The turbine blades are nested within the hollow fan blade structure, with the turbine flow path integrated inside the fan blade cavity. This nesting arrangement allows the turbine components to be accommodated within the existing fan blade volume, eliminating the need for separate external turbine housing and significantly reducing the overall engine length while maintaining structural integrity.

Inventive Principle:

Principle #7Nested doll (Nesting)

2Volume of moving object

If turbine is integrated onto fan blade tips, then engine packaging is improved, but manufacturing and assembly complexity increases

Engineering Contradiction:

Improveengine package volumeVSAvoidturbine assembly ease

Core Design Contradiction:

Volume of moving objectVSEase of manufacture

Solution Approach 1:

The turbine assembly is segmented into modular components including separate turbine blades, hub, and mounting structures that can be manufactured independently and then assembled. The turbine blades are designed as discrete elements that can be attached to the fan blade tips through standardized mounting interfaces, facilitating easier manufacturing and assembly while maintaining the compact integrated configuration.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent introduces an intermediary mounting structure or adapter component that facilitates the connection between the turbine blades and the fan blade tips. This intermediary element simplifies the assembly process by providing a standardized interface, allowing the turbine components to be easily attached to the fan blades without requiring complex direct integration, thus resolving the contradiction between compact packaging and ease of assembly.

Inventive Principle:

Principle #24Intermediary (Mediator)

3Ease of manufacture

If turbine blade platforms are spaced apart, then manufacturing is easier, but leakage between platforms increases and efficiency decreases

Engineering Contradiction:

Improveblade manufacturing easeVSAvoidleakage loss

Core Design Contradiction:

Ease of manufactureVSLoss of energy

Solution Approach 1:

The patent employs flexible sealing elements or thin film barriers between the turbine blade platforms that can accommodate manufacturing tolerances while preventing leakage. These sealing elements are designed to be compliant enough to bridge small gaps between blade platforms yet rigid enough to maintain the structural integrity and prevent harmful leakage, thus resolving the contradiction between ease of manufacture and energy efficiency.

Inventive Principle:

Principle #30Flexible shells and thin films

Solution Approach 2:

The patent optimizes the spacing and positioning parameters of the turbine blade platforms to minimize leakage while maintaining manufacturability. By carefully adjusting the radial and axial positions of the blade platforms, the design achieves optimal sealing characteristics without requiring extremely tight tolerances, thus resolving the contradiction between ease of manufacture and energy loss prevention.

Inventive Principle:

Principle #35Parameter changes

Data Source

PatentUS7878762B2Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor

Publication Date: 2011.02.01 RTX CORP

AI summary

A tip-turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. By forming the turbine blades in clusters, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine blade clusters to a diffuser surface includes axial installation and radial locking of each turbine blade cluster. This is accomplished by attachment lugs protruding from the underside of the arcuate base of the turbine blade clusters. Torque load surfaces are also integrated into the arcuate base.