Boundary Layer Turbine Simplified Disk Porting

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Solution Overview

Problem

Existing boundary layer gas turbine engines face inefficiencies due to complex construction and turbulence-inducing porting systems, which reduce performance and increase construction costs without significant operational benefits.

Innovation Solution

A novel boundary layer turbine design featuring a stack of alternating disks and spacers with specific diameters and thicknesses, utilizing silicon-based materials and a simplified porting system that eliminates the need for complex couplers, allowing for efficient air and exhaust channeling through lateral openings, and incorporating a platinized surface or LED for ignition.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Device complexity

If complex couplers with multiple channels are used for porting gas flow, then gas flow control is achieved, but device complexity and construction costs increase

Engineering Contradiction:

Improveporting system complexityVSAvoidconstruction costs

Core Design Contradiction:

Device complexityVSEase of manufacture

Solution Approach 1:

The porting system is segmented into simple lateral openings in each disk rather than complex couplers. Each disk has openings that align with adjacent disks to form channels, dividing the complex porting function into simple individual disk components

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Multiple functions are merged into the disk structure itself - the disks provide both structural support and porting functionality through integrated lateral openings, eliminating the need for separate coupler components

Inventive Principle:

Principle #5Merging (Combining)

2Device complexity

If complex couplers are used for porting, then gas flow control is achieved, but turbulence increases reducing efficiency

Engineering Contradiction:

Improveporting system structureVSAvoidturbulence losses

Core Design Contradiction:

Device complexityVSLoss of energy

Solution Approach 1:

Instead of using complex couplers to create channels, the invention inverts the approach by using simple lateral openings in flat disks that align to form channels, creating smoother flow paths that reduce turbulence

Inventive Principle:

Principle #13The other way round (Inversion)

Solution Approach 2:

The porting geometry is changed from complex three-dimensional coupler structures to simple two-dimensional lateral openings, fundamentally altering the flow characteristics and reducing turbulence-induced energy losses

Inventive Principle:

Principle #35Parameter changes

3Strength

If traditional disk stacking with couplers is used, then structural integrity is maintained, but weight and material costs increase

Engineering Contradiction:

Improvestructural integrityVSAvoidturbine rotor weight

Core Design Contradiction:

StrengthVSWeight of moving object

Solution Approach 1:

The heavy coupler components are extracted and eliminated from the design. Structural integrity is maintained through the disk stack configuration and alignment features alone, removing unnecessary weight-bearing components

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

Simple, lightweight disk and spacer components replace expensive, heavy coupler components. The design uses inexpensive materials and simple geometries that achieve sufficient structural integrity without excessive weight

Inventive Principle:

Principle #27Cheap short-living objects (Disposable)

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 enhances turbine efficiency and power output by minimizing turbulence and construction complexity, achieving higher RPMs and improved heat transfer while reducing material costs and weight, with the potential for higher overall system efficiency comparable to other engine types.

Implementation Method 1

exhaust products expand inward between disks imparting torque to the turbine shaft by boundary layer friction

Methodology Applied

Scientific EffectBoundary layer friction: Boundary Layer

Implementation Method 2

the air fuel mixture is ignited

Methodology Applied

Scientific EffectIgnition: Combustion

Data Source

PatentUS11415047B2Bounday layer turbine

Publication Date: 2022.08.16 KIRK JAMES F

AI summary

A boundary layer turbine (BLT) engine has a housing formed by an outer cylinder a first and a second faceplate, a turbine shaft through the faceplates, a stack of alternating disks and spacers with central holes joined to the turbine shaft leaving an outer combustion zone, an air inlet through the first faceplate, an exhaust port through the second faceplate, a fuel port through the outer cylinder, and an ignition device communicating with the combustion zone. The disks and spacers have openings forming separate intake and exhaust channels parallel to the turbine shaft, one channel channeling air from the air inlet port to spaces between disks, and the other channel channeling exhaust from the combustion zone through the exhaust channel to the exhaust port. Fuel is injected into the combustion zone, the air fuel mixture is ignited, and exhaust products impart torque to the turbine shaft by boundary layer friction.