Compact Combustor Front Wall for Low-Pressure Helical Mixing

Solution Overview

Problem

Conventional gas turbine engines face inefficiencies and increased complexity due to the need for components like guide vanes and diffusors to redirect air and fuel flows, leading to higher pressure drops and costs.

Innovation Solution

The design incorporates a combustor with a front wall comprising multiple facets with through holes, oriented at an angle offset from the central axis, and a vortex cavity to facilitate a helical flow of the fuel/air mixture, reducing the need for additional components to direct airflow.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If guide vanes and diffusors are used to redirect air and fuel flows, then the flow direction can be controlled, but the device complexity and weight increase

Engineering Contradiction:

Improveflow direction controlVSAvoidcomponent quantity

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

The patent combines multiple flow control functions into a single combustor structure. The front wall with angled facets integrates the flow redirection function that would traditionally require separate guide vanes and diffusors, eliminating these additional components while maintaining flow control capability

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The combustor front wall is designed to perform multiple functions simultaneously: it serves as a structural boundary, a flow redirection surface through its angled facets, and a support for fuel injection. This multi-functionality eliminates the need for dedicated guide vanes and diffusors

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Ease of operation

If guide vanes and diffusors are used to redirect air and fuel flows, then the flow direction can be controlled, but the weight increases

Engineering Contradiction:

Improveflow direction controlVSAvoidengine weight

Core Design Contradiction:

Ease of operationVSWeight of moving object

Solution Approach 1:

The patent combines multiple flow control functions into a single combustor structure. The front wall with angled facets integrates the flow redirection function that would traditionally require separate guide vanes and diffusors, eliminating these additional components while maintaining flow control capability

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The combustor front wall is designed to perform multiple functions simultaneously: it serves as a structural boundary, a flow redirection surface through its angled facets, and a support for fuel injection. This multi-functionality eliminates the need for dedicated guide vanes and diffusors

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Ease of operation

If conventional components are used to redirect flows, then flow direction can be controlled, but pressure drops increase

Engineering Contradiction:

Improveflow direction controlVSAvoidpressure drop

Core Design Contradiction:

Ease of operationVSLoss of energy

Solution Approach 1:

The patent employs curved or angled facets on the combustor front wall that smoothly guide the flow rather than using sharp edges or multiple discrete components. This streamlined geometry reduces flow separation and turbulence, minimizing pressure losses while maintaining effective flow direction control

Inventive Principle:

Principle #14Spheroidality (Curvature)

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 configuration reduces the complexity and weight of the gas turbine engine, minimizes pressure drops, and enhances the efficiency of the fuel/air mixture's mixing and ignition, leading to improved overall engine efficiency.

Implementation Method 1

a vortex cavity to facilitate a helical flow of the fuel/air mixture

Methodology Applied

Scientific EffectVortex flow: Vortex Ring

Data Source

PatentUS12312995B2Ultra compact combustor

Publication Date: 2025.05.27 GENERAL ELECTRIC CO

AI summary

Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.