Rotating Detonation Augmentor Geometry for Compact Gas Turbine Thrust
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing gas turbine engines with augmentors face challenges of increased axial length, volume, and weight, leading to higher fuel consumption, which are exacerbated by traditional rotating detonation architectures that result in high pressure losses and are not suitable for flight-worthy systems.
Innovation Solution
Incorporating a rotating detonation architecture that allows detonation waves to propagate radially and incorporates a stabilization geometry to guide the waves, eliminating the centerbody and reducing the axial length and volume of the exhaust system, thereby enhancing combustion efficiency and thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If an augmentor is incorporated into a gas turbine engine to provide additional heat to exhaust airflow, then engine thrust is increased, but axial length and volume of the exhaust system increase
Solution Approach 1:
The patent employs a rotating detonation wave mechanism where the detonation front rotates around the combustor perimeter, dynamically interacting with the exhaust flow. This rotating combustion process enables more compact axial packaging compared to traditional linear augmentor designs, reducing the axial length while maintaining thrust enhancement capability
Solution Approach 2:
The invention transitions from subsonic deflagration combustion to supersonic detonation combustion, fundamentally changing the combustion parameter regime. This parameter change enables more efficient energy release in a shorter axial distance, thereby reducing the required axial length of the exhaust system while achieving the desired thrust increase
2Force
If an augmentor is incorporated into a gas turbine engine to provide additional heat to exhaust airflow, then engine thrust is increased, but volume of the exhaust system increases
Solution Approach 1:
The rotating detonation wave mechanism utilizes circumferential rotation around a compact combustor volume, enabling efficient heat addition without requiring large axial or radial extensions. This dynamic combustion approach achieves thrust enhancement in a more compact volume compared to traditional augmentor configurations
Solution Approach 2:
The invention moves the combustion process from a primarily axial dimension to include significant circumferential rotation. By utilizing the circumferential dimension for the detonation wave propagation, the system achieves efficient combustion in a smaller overall volume, reducing the exhaust system volume while maintaining thrust capability
3Productivity
If traditional rotating detonation architecture is used, then combustion efficiency is improved, but pressure losses increase making the system unsuitable for flight-worthy applications
Solution Approach 1:
The patent implements different geometric features at different locations within the detonation chamber. The inwardly directed steps create localized flow control zones that manage pressure distribution, while the outwardly directed steps at the exit provide controlled expansion. This local quality differentiation maintains high combustion efficiency while minimizing overall pressure losses
Solution Approach 2:
The invention converts the potentially harmful pressure losses into beneficial flow control mechanisms. The stepped geometry features are designed to create controlled pressure gradients that enhance combustion stability while recovering pressure, effectively transforming what would be losses into performance-enhancing features
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
The solution results in a more compact, efficient combustion process, reducing the exhaust system's size by up to 75% and weight by up to 25%, improving fuel consumption and enabling strategic advantages in military applications with a smaller infrared signature.
Implementation Method 1
a rotating detonation wave is generated. The rotating detonation wave consumes the core air-fuel mixture to support a combustion reaction within the detonation chamber
Implementation Method 2
The rotating detonation wave consumes the core air-fuel mixture to support a combustion reaction within the detonation chamber
Implementation Method 3
The rotating detonation architecture 1b may facilitate a more efficient and compact combustion reaction
Data Source
AI summary
Systems and methods are provided herein useful to thrust augmentation in a gas turbine engine. In some embodiments, the systems include augmentors that incorporate a rotating detonation architecture. An exhaust system of a gas turbine engine includes an augmentor and a peripheral wall surrounding an exhaust system core. The augmentor comprises a detonation chamber disposed within the exhaust system core. The detonation chamber includes a channel formed in the peripheral wall. A core inlet path delivers a core air-fuel mixture and a pilot inlet path delivers a pilot air-fuel mixture to the detonation chamber. The core air-fuel mixture combusts in the detonation chamber along the midline the detonation chamber. The pilot air-fuel mixture detonates in the detonation chamber adjacent the peripheral wall to create a rotating detonation wave that supports the combustion reaction occurring along the midline of the detonation chamber.